Space satellite thermal control system based on self-adaptive thermal transport

Abstract

The invention relates to the technical field of space satellite thermal control, in particular to a space satellite thermal control system based on self-adaptive thermal transport, which comprises a thermochromic intelligent thermal control coating coated on the whole outer surface of a space satellite, the variable-direction active heat compensation pump loop is arranged in the space satellite; the variable-direction active heat compensation pump loop is arranged between the satellite main illuminated face and the satellite main nightside and used for conducting heat transfer between the satellite main illuminated face and the satellite main nightside. The structure is simple, a basic frame of a heat control system is built, through cooperation of coating covering and a heat pump loop, regulation and transfer of satellite surface heat are preliminarily achieved, the temperature difference of the satellite outer surface is effectively reduced, the temperature uniformity of the outer surface is improved, effective guarantee is provided for a space satellite to avoid detection of an infrared detector, and the application range is wide. And the space satellite is safer and more hidden.

Description

Technical Field

[0001] This invention relates to the field of space satellite thermal control technology, and in particular to a space satellite thermal control system based on adaptive heat transport. Background Technology

[0002] In the modern information age, artificial satellites play a crucial role in outer space, and their safety is of paramount importance. During their orbit around the Earth, satellites are affected by the external environment and heat generated by internal instruments, resulting in uneven surface temperature distribution and significant temperature differences. This is especially pronounced during periods of sunlight, with a significant temperature difference between the primarily sun-exposed and shaded sides. Furthermore, changes in satellite position altering solar illumination can cause rapid temperature fluctuations in some areas, making satellites more susceptible to detection by infrared detectors and compromising their stealth capabilities. Therefore, developing new, reliable satellite thermal control systems that do not compromise other stealth requirements to achieve infrared stealth is of great significance.

[0003] Traditional methods for achieving infrared stealth on satellites involve applying a specific coating material to the satellite surface. This material has low emissivity in the infrared detection band to avoid detection and high emissivity in non-detection bands to dissipate heat. However, this conflicts with the high solar absorption requirements for visible light stealth, making it impossible to achieve infrared stealth without compromising optical stealth. Against this backdrop, thermochromic smart thermal control materials, which change their optical properties in response to temperature variations, have attracted attention. They possess high emissivity at high temperatures and low emissivity at low temperatures, and require no energy drive. Applying them to satellite surfaces enables adaptive surface temperature control. Simultaneously, research on the application of active heat pump technology on satellites is increasing. This technology absorbs heat on the absorbing surface and transports it to the radiating surface for dissipation, reducing surface temperature differences when applied inside the satellite.

[0004] Based on this, the present invention combines thermochromic intelligent thermal control coating and active heat pump technology to propose a space satellite thermal control system based on adaptive heat transport to solve the above technical problems. Summary of the Invention

[0005] The purpose of this invention is to provide a space satellite thermal control system based on adaptive heat transport to solve the problems existing in the prior art.

[0006] To achieve the above objectives, the present invention provides the following solution: The present invention provides a space satellite thermal control system based on adaptive heat transport, comprising:

[0007] A thermochromic intelligent thermal control coating is applied to the entire outer surface of a space satellite. The space satellite is divided into a main sun-receiving surface and a main shaded surface according to the degree of irradiation. The thermochromic intelligent thermal control coating can be divided into a thermochromic coating for the sun-receiving surface and a thermochromic coating for the shaded surface according to the degree of irradiation. The thermochromic coating for the sun-receiving surface is applied to the main sun-receiving surface of the satellite, and the thermochromic coating for the shaded surface is applied to the main shaded surface of the satellite.

[0008] A variable-direction active heat pump loop is disposed inside the space satellite; the variable-direction active heat pump loop is disposed between the main sun-receiving surface and the main shaded surface of the satellite, and is used to transfer heat between the main sun-receiving surface and the main shaded surface of the satellite.

[0009] Preferably, the main sunlit side and the main shadowed side of the satellite are switched according to the operation of the space satellite.

[0010] Preferably, the variable-direction active heat pump circuit includes a compressor and an expansion valve. A heat transfer component is connected between the compressor and the expansion valve. The heat transfer component is fitted inside the main sun-receiving surface of the satellite and inside the main shaded surface of the satellite. The heat-conducting medium is driven by the compressor to be transferred between the heat transfer components for heat transfer between the main sun-receiving surface and the main shaded surface of the satellite.

[0011] Preferably, the heat transfer assembly includes a first condenser, a first evaporator, a second condenser, and a second evaporator. The first condenser and the first evaporator are fitted together on the inner wall of the main sun-receiving side of the satellite, and the second condenser and the second evaporator are disposed on the inner wall of the main shaded side of the satellite. The first condenser, the first evaporator, the second condenser, and the second evaporator are respectively connected to the compressor and the expansion valve.

[0012] Preferably, the heat transfer assembly further includes a first three-way valve and a second three-way valve. The medium inlet of the first three-way valve is connected to the medium outlet of the compressor, and the two medium outlets of the first three-way valve are respectively connected to the medium inlets of the first condenser and the second condenser. The medium inlet of the second three-way valve is connected to the medium outlet of the expansion valve, and the two medium outlets of the second three-way valve are respectively connected to the medium inlets of the first evaporator and the second evaporator.

[0013] Preferably, the medium outlets of the first condenser and the second condenser are respectively connected to the two medium inlets of the compressor, and the medium outlets of the first evaporator and the second evaporator are respectively connected to the two medium inlets of the expansion valve.

[0014] Preferably, the thermochromic intelligent thermal control coating includes a highly reflective aluminum metal layer disposed on a transferable film, the surface of the highly reflective aluminum metal layer is provided with a dielectric flat-top cubic cone array, and the surface of the dielectric flat-top cubic cone array is coated with a surface layer.

[0015] Preferably, the surface layer includes a vanadium dioxide phase change layer coated on the surface of the medium flat-top cubic pyramid array, and a top protective layer is applied to the surface of the vanadium dioxide phase change layer.

[0016] Preferably, after the thermochromic intelligent thermal control coating is prepared on the transferable film, it is transferred and bonded to the outer surface of the space satellite for fixation.

[0017] Preferably, the high-reflectivity aluminum metal layer is deposited on the transferable thin film by magnetron sputtering, and the dielectric flat-top cubic pyramid array is prepared on the high-reflectivity aluminum metal layer by nanoimprinting.

[0018] Compared with existing technologies, this invention has the following advantages and technical effects: This invention discloses a space satellite thermal control system based on adaptive heat transport. A variable-direction active heat pump loop installed inside the satellite can transfer heat received on the sunlit side of the satellite to the shaded side. Simultaneously, the direction of heat transfer can be changed according to the periodic transition between the sunlit and shaded sides of the satellite, reducing the temperature difference on the satellite surface and avoiding extreme temperatures. This invention covers the surface of the space satellite with a thermochromic intelligent thermal control coating. Utilizing the difference in infrared emissivity before and after the phase transition temperature, the infrared emissivity of the satellite's outer surface is adjusted to achieve high emissivity at high temperatures and low emissivity at low temperatures. This allows the temperature of the satellite's outer surface, which is not exposed to sunlight for extended periods or is in the shade, to adaptively approach the phase transition temperature of the thermal control coating. Simultaneously, it assists the variable-direction active heat pump loop inside the satellite in adjusting the temperature of the main sunlit and shaded sides of the satellite, improving the temperature uniformity of the satellite's outer surface and providing a reliable guarantee for the space satellite to avoid detection by infrared detectors. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly described below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. In the drawings:

[0020] Fig. 1 This is a schematic diagram of the space satellite thermal control system based on adaptive heat transport according to the present invention;

[0021] Fig. 2 This is an axial view of the thermochromic intelligent thermal control coating of the present invention;

[0022] Fig. 3 This is a schematic diagram of the thermochromic intelligent thermal control coating structure of the present invention;

[0023] In the diagram: 1. Compressor; 2. Expansion valve; 3. First three-way valve; 4. Second three-way valve; 5. First condenser; 6. Second condenser; 7. First evaporator; 8. Second evaporator; 9. Main sun-exposed surface of the satellite; 10. Main shadowed surface of the satellite; 11. Thermochromic coating on the sun-exposed surface; 12. Thermochromic coating on the shadowed surface; 13. High-reflectivity aluminum layer; 14. Vanadium dioxide phase change layer; 15. Top protective layer; 16. Medium flat-top cubic pyramid array. Detailed Implementation

[0024] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0025] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0026] Reference Figs. 1 to 3 As shown, this embodiment provides a space satellite thermal control system based on adaptive heat transport, including:

[0027] Thermochromic intelligent thermal control coating is applied to the entire outer surface of the space satellite. The space satellite is divided into the main sun-receiving surface 9 and the main shaded surface 10 according to the degree of irradiation. The thermochromic intelligent thermal control coating can be divided into the sun-receiving surface thermochromic coating 11 and the shaded surface thermochromic coating 12 according to the degree of irradiation. The sun-receiving surface thermochromic coating 11 is applied to the main sun-receiving surface 9 of the satellite, and the shaded surface thermochromic coating 12 is applied to the main shaded surface 10 of the satellite.

[0028] A variable-direction active heat pump loop is installed inside the space satellite. The variable-direction active heat pump loop is located between the main sun-receiving surface 9 and the main shaded surface 10 of the satellite, and is used to transfer heat between the main sun-receiving surface 9 and the main shaded surface 10 of the satellite.

[0029] This invention discloses a space satellite thermal control system based on adaptive heat transport. A variable-direction active heat pump loop installed inside the satellite transfers heat received on the sunlit side to the shaded side. Simultaneously, the direction of heat transfer is changed according to the periodic transition between the sunlit and shaded sides, reducing the temperature difference on the satellite surface and avoiding extreme temperatures. This invention also utilizes a thermochromic intelligent thermal control coating on the satellite surface, leveraging the difference in infrared emissivity before and after the phase transition temperature. This adjusts the infrared emissivity of the satellite's outer surface, achieving high emissivity at high temperatures and low emissivity at low temperatures. This allows the satellite's outer surface temperature, whether exposed to sunlight or shade for extended periods, to adaptively approach the phase transition temperature of the thermal control coating. Simultaneously, it assists the variable-direction active heat pump loop inside the satellite in regulating the temperature of the main sunlit and shaded sides, improving the temperature uniformity of the satellite's outer surface and providing a reliable guarantee for the space satellite to avoid detection by infrared detectors. This invention has a simple structure and establishes the basic framework of a thermal control system. Through coating coverage and heat pump circuit, it initially realizes the regulation and transfer of heat on the satellite surface, effectively reduces the temperature difference on the outer surface of the satellite, improves the temperature uniformity of the outer surface, and provides effective protection for space satellites to avoid detection by infrared detectors, making space satellites safer and more covert.

[0030] The scheme was further optimized so that the satellite's main illuminated surface 9 and main shaded surface 10 can be switched according to the satellite's operation. The satellite's main illuminated surface 9 and main shaded surface 10 are not fixed and can be switched according to the satellite's operation. This can adapt to changes in the satellite's position and attitude in space, avoid coating function mismatch caused by the switching between the illuminated and shaded surfaces, and ensure that the coating can always effectively regulate the temperature of the corresponding surfaces.

[0031] Further optimization of the scheme involves a variable-direction active heat pump loop comprising a compressor 1 and an expansion valve 2. A heat transfer assembly connects the compressor 1 and the expansion valve 2, and the heat transfer assembly is fitted into the inner sides of the satellite's main sun-exposed surface 9 and the main shaded surface 10. The heat transfer medium is driven by the compressor 1 to be transferred between the heat transfer assemblies, facilitating heat transfer between the satellite's main sun-exposed surface 9 and the main shaded surface 10. The medium, driven by the compressor 1, is transferred between the heat transfer assemblies, achieving heat transfer on both sides, improving heat transfer efficiency, and enabling heat transfer from the sunlit side to the shaded side of the satellite. This reduces surface temperature differences, avoids extreme temperatures, further enhances the ability to regulate the temperature of the main sun-exposed and main shaded surfaces, and improves the flexibility and effectiveness of satellite surface temperature control.

[0032] The design further optimizes the heat transfer components, which include a first condenser 5, a first evaporator 7, a second condenser 6, and a second evaporator 8. The first condenser 5 and the first evaporator 7 are fitted together on the inner wall of the satellite's main sun-receiving surface 9, while the second condenser 6 and the second evaporator 8 are installed on the inner wall of the satellite's main shaded surface 10. These components are connected to the compressor 1 and the expansion valve 2, respectively. The design of the first condenser 5, the first evaporator 7, the second condenser 6, and the second evaporator 8 refines the specific structure and installation location of the heat transfer components, allowing heat transfer to occur systematically within specific devices. This improves the accuracy of heat transfer, more efficiently transferring heat between the satellite's main sun-receiving surface 9 and the main shaded surface, optimizing the heat transfer process, and facilitating targeted temperature adjustment of the main sun-receiving and main shaded surfaces.

[0033] Further optimization of the scheme includes a first three-way valve 3 and a second three-way valve 4 in the heat transfer assembly. The medium inlet of the first three-way valve 3 is connected to the medium outlet of the compressor 1, and the two medium outlets of the first three-way valve 3 are connected to the medium inlets of the first condenser 5 and the second condenser 6, respectively. The medium inlet of the second three-way valve 4 is connected to the medium outlet of the expansion valve 2, and the two medium outlets of the second three-way valve 4 are connected to the medium inlets of the first evaporator 7 and the second evaporator 8, respectively. The first three-way valve 3 and the second three-way valve 4 are used to switch the flow direction of the medium. According to the changes in solar radiation on the satellite's surface during the illumination period, the flow direction of the medium in the active heat pump loop can be flexibly adjusted, thereby adjusting the temperature changes between the main sunlit surface 9 and the main shaded surface of the satellite. This provides structural support for subsequent adjustments to the heat transfer direction based on the switching between the sunlit and shaded surfaces of the satellite, enhancing the flexibility of the heat pump loop.

[0034] The scheme is further optimized so that the medium outlet of the first condenser 5 and the medium outlet of the second condenser 6 are respectively connected to the two medium inlets of the compressor 1, and the medium outlets of the first evaporator 7 and the second evaporator 8 are respectively connected to the two medium inlets of the expansion valve 2. The medium circulates between the condensers and evaporators, forming a complete and bidirectional switchable circulation system, realizing a stable heat transfer function, ensuring that the medium can circulate smoothly under different irradiation conditions, and ensuring continuous and stable heat transfer.

[0035] Further optimization of the scheme reveals that the thermochromic intelligent thermal control coating includes a highly reflective aluminum layer 13 disposed on a transferable thin film. A dielectric flat-topped cubic pyramid array 16 is disposed on the surface of the highly reflective aluminum layer 13, and a surface layer is applied to the surface of the dielectric flat-topped cubic pyramid array 16. The surface layer includes a vanadium dioxide phase change layer 14 coated on the surface of the dielectric flat-topped cubic pyramid array 16, and a top protective layer 15 is applied to the surface of the vanadium dioxide phase change layer 14. After the thermochromic intelligent thermal control coating is prepared on the transferable thin film, it is transferred and bonded to the outer surface of the space satellite for fixation. The highly reflective aluminum layer 13 is deposited on the transferable thin film using magnetron sputtering technology, and the dielectric flat-topped cubic pyramid array 16 is prepared onto the highly reflective aluminum layer 13 using nanoimprinting technology. The process of preparing the thermochromic intelligent thermal control coating on the transferable thin film and then transferring and bonding it to the outer surface of the space satellite facilitates coating preparation and installation, improves the bonding strength between the coating and the satellite surface, and ensures that the thermochromic intelligent thermal control coating can stably perform its thermal control function. The thermochromic intelligent thermal control coating includes a highly reflective aluminum layer 13 disposed on a transferable thin film as the bottom layer of the resonant cavity. A dielectric flat-top cubic pyramid array 16 is disposed on the surface of the highly reflective aluminum layer 13, enabling special optical response and thermal conductivity properties, which helps regulate the satellite surface temperature. A surface layer is coated on the surface of the dielectric flat-top cubic pyramid array 16. A vanadium dioxide phase change layer 14 utilizes its phase change characteristics to achieve wide-range control of infrared emissivity. A top protective layer 15 protects the coating material from corrosion and damage caused by space environmental factors, extending the coating's service life. The highly reflective aluminum layer 13 is deposited on the transferable thin film using magnetron sputtering technology, allowing for precise control of the deposition of the highly reflective aluminum layer 13 and ensuring its quality and performance. The dielectric flat-top cubic pyramid array 16 is prepared onto the highly reflective aluminum layer 13 using nanoimprint technology, achieving special optical structure and thermal control performance.

[0036] In one embodiment of the present invention, since vanadium dioxide undergoes a reversible metal-insulator phase transition at its phase transition temperature of 68°C, the optical properties of the thin film formed therefrom will also change. The thermal control coating formed by depositing the vanadium dioxide thin film on the infrared high reflectivity aluminum metal layer 13 can achieve low infrared emissivity at low temperature and high infrared emissivity at high temperature. Based on this, a special optical structure can be constructed to achieve high emissivity at high temperature and low emissivity at low temperature.

[0037] In one embodiment of the present invention, the vanadium dioxide-based thermochromic intelligent thermal control coating material adopts a structure combining an asymmetric Fabry-Perot resonance of a vanadium dioxide phase change layer 14 / dielectric layer / high reflectivity layer with a micro cubic flat-top cone array, and its outer surface is covered with a protective layer to adapt to the space environment, such as... Fig. 2 and Fig. 3As shown, the infrared emissivity can be controlled over a wide range by turning the Fabry-Perot resonance on and off through the vanadium dioxide phase transition. Furthermore, the response bandwidth of the resonance structure is widened by the array structure, resulting in a more uniform optical response and achieving high emissivity at high temperatures and low emissivity at low temperatures.

[0038] In one embodiment of the present invention, the high-reflectivity aluminum metal layer 13 is made of aluminum, a metal material with high solar reflectivity, and serves as the bottom layer of the resonant cavity; the dielectric layer is a dielectric flat-top cubic pyramid array 16, which can be made of materials such as BaF2, CaF2, and HfO2.

[0039] In one embodiment of the present invention, a vanadium dioxide phase change layer 14 is covered on the surface of the cone array. Further doping of tungsten into the vanadium dioxide can reduce its phase change temperature to 30~40°C, which is close to the midpoint between the lowest and highest temperatures on the outer surface of the satellite, thereby improving the speed of temperature regulation.

[0040] In one embodiment of the present invention, in order to protect the coating material and extend its service life, a transparent top protective layer 15, such as Al2O3, is also required to cover the top of the coating to protect the coating from corrosion and damage caused by factors such as atomic oxygen and ultraviolet rays.

[0041] In one embodiment of the present invention, the thickness of the high-reflectivity layer, the phase change layer and the protective layer is in the nanometer range, while the size of the cone array dielectric layer can reach the micrometer range.

[0042] In one embodiment of the present invention, the thermochromic intelligent thermal control coating material, after preparation, is installed on the outer surface panel of the satellite. Due to its thermochromic properties, which change its optical properties in response to temperature changes, it exhibits high emissivity when the satellite's outer surface temperature exceeds the phase transition temperature of the thermal control coating; and low emissivity when the satellite's outer surface temperature is below the phase transition temperature of the thermal control coating. For the satellite's main sun-exposed surface 9 and the satellite's main shaded surface 10, due to the high temperature of the sun-exposed surface and the low temperature of the shaded surface, the thermochromic intelligent thermal control coating can dissipate heat through high emissivity, accelerating the cooling of the sun-exposed surface; and slow down the cooling rate of the shaded surface through low emissivity. For the other four outer surfaces of the satellite, since they are intermittently exposed to sunlight during illumination, covering them with the thermochromic intelligent thermal control coating allows their temperature to fluctuate around the coating's phase transition temperature, improving the uniformity of the satellite's outer surface temperature and reducing temperature differences.

[0043] Workflow:

[0044] The satellite is based on a CubeSat that rotates on a fixed axis around the Earth. Due to its fixed-axis rotation, two of its surfaces along the spin axis are primarily illuminated during the sunlit period, one being the primary sun-exposed surface and the other the primary shaded surface. The other four surfaces are intermittently and briefly exposed to sunlight. The lowest temperature recorded on the outer surface during the satellite's operation is 10°C, and the highest temperature is 80°C. Therefore, a variable-direction active heat pump loop is positioned between the two surfaces along the satellite's spin axis, while a thermochromic intelligent thermal control coating covers all six outer surfaces of the satellite.

[0045] See attached document Fig. 1 As shown, when the satellite is operating during its sunshine period, if the satellite's main illuminated side 9 is the sunlit side and the satellite's main shaded side 10 is the shaded side, the first three-way valve 3 closes port A, and the second three-way valve 4 closes port B, causing the medium in the active heat pump circuit to flow along the attached... Fig. 1 The medium flows in the direction of the solid line, passing through the first evaporator 7 on the main sun-receiving surface 9 of the satellite and the second condenser 6 on the main sun-receiving surface 10 of the satellite, forming a complete heat pump loop with the compressor 1, the second condenser 6, the expansion valve 2, and the first evaporator 7. At this time, the low-temperature medium, after being throttled by the expansion valve 2, flows through the first evaporator 7 through the main sun-receiving surface 9 of the satellite, absorbing the solar radiation heat received by that surface, slowing down the temperature rise until it cools down. Subsequently, the high-temperature, high-pressure medium, after being compressed by the compressor 1, flows through the second condenser 6 through the main sun-receiving surface 10 of the satellite, radiating the heat contained in the medium through that surface, slowing down the temperature drop until it warms up.

[0046] If, due to changes in the satellite's position and attitude, the main illuminated side becomes shaded and the main shadowed side becomes sunlit, then the first three-way valve 3 closes port B, and the second three-way valve 4 closes port A, allowing the medium in the active heat pump circuit to flow along the... Fig. 1 The fluid flows in the direction of the dotted line, passing through the second evaporator 8 on the satellite's main shaded side 10 and the first condenser 5 on the satellite's main illuminated side 9, forming a complete heat pump loop with the compressor 1, the first condenser 5, the expansion valve 2, and the second evaporator 8. At this time, the low-temperature medium, after being throttled by the expansion valve 2, flows through the second evaporator 8 through the satellite's main shaded side, absorbing the solar radiation heat received by that side, slowing down the surface's temperature rise until it cools down. Subsequently, the high-temperature, high-pressure medium, compressed by the compressor 1, flows through the first condenser 5 through the satellite's main illuminated side 9, radiating the heat contained in the medium through that side, slowing down the surface's temperature drop until it warms up.

[0047] The variable-direction active heat pump loop adjusts the temperature difference between the main sun-exposed surface (9) and the main shaded surface of the satellite based on the changes in solar radiation on the satellite's surface during the illumination period. Combined with the effect of the thermochromic intelligent thermal control coating, this can effectively reduce the temperature difference between the two sides. The other four sides of the satellite are only intermittently exposed to sunlight, and their temperature is regulated solely by the thermochromic intelligent thermal control coating.

[0048] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0049] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A space satellite thermal control system based on adaptive heat transport, characterized in that, include: A thermochromic intelligent thermal control coating is applied to the entire outer surface of a space satellite. The space satellite is divided into a main sun-receiving surface (9) and a main shaded surface (10) according to the degree of irradiation. The thermochromic intelligent thermal control coating can be divided into a thermochromic coating (11) for the sun-receiving surface and a thermochromic coating (12) for the shaded surface according to the degree of irradiation. The thermochromic coating (11) for the sun-receiving surface is applied to the main sun-receiving surface (9) of the satellite, and the thermochromic coating (12) for the shaded surface is applied to the main shaded surface (10) of the satellite. A variable-direction active heat pump circuit is provided inside the space satellite. The variable-direction active heat pump circuit is provided between the main sun-receiving surface (9) and the main shaded surface (10) of the satellite, and is used to transfer heat between the main sun-receiving surface (9) and the main shaded surface (10) of the satellite.

2. The space satellite thermal control system based on adaptive heat transport according to claim 1, characterized in that: The main sunlit side (9) and the main shadow side (10) of the satellite are switched according to the operation of the space satellite.

3. The space satellite thermal control system based on adaptive heat transport according to claim 1, characterized in that: The variable-direction active heat pump circuit includes a compressor (1) and an expansion valve (2). A heat transfer component is connected between the compressor (1) and the expansion valve (2). The heat transfer component is fitted inside the main sun-receiving surface (9) and the main shaded surface (10) of the satellite. The heat transfer medium is driven by the compressor (1) to be transferred between the heat transfer components for heat transfer between the main sun-receiving surface (9) and the main shaded surface (10) of the satellite.

4. The space satellite thermal control system based on adaptive heat transport according to claim 3, characterized in that: The heat transfer assembly includes a first condenser (5), a first evaporator (7), a second condenser (6), and a second evaporator (8). The first condenser (5) and the first evaporator (7) are attached to the inner wall of the main sunlit side (9) of the satellite, and the second condenser (6) and the second evaporator (8) are disposed on the inner wall of the main shaded side (10) of the satellite. The first condenser (5), the first evaporator (7), the second condenser (6), and the second evaporator (8) are respectively connected to the compressor (1) and the expansion valve (2).

5. The space satellite thermal control system based on adaptive heat transport according to claim 4, characterized in that: The heat transfer assembly also includes a first three-way valve (3) and a second three-way valve (4). The medium inlet of the first three-way valve (3) is connected to the medium outlet of the compressor (1), and the two medium outlets of the first three-way valve (3) are connected to the medium inlets of the first condenser (5) and the second condenser (6), respectively. The medium inlet of the second three-way valve (4) is connected to the medium outlet of the expansion valve (2), and the two medium outlets of the second three-way valve (4) are connected to the medium inlets of the first evaporator (7) and the second evaporator (8), respectively.

6. The space satellite thermal control system based on adaptive heat transport according to claim 5, characterized in that: The medium outlet of the first condenser (5) and the medium outlet of the second condenser (6) are respectively connected to the two medium inlets of the compressor (1), and the medium outlets of the first evaporator (7) and the second evaporator (8) are respectively connected to the two medium inlets of the expansion valve (2).

7. The space satellite thermal control system based on adaptive heat transport according to claim 1, characterized in that: The thermochromic intelligent thermal control coating includes a highly reflective aluminum metal layer (13) disposed on a transferable film, and a dielectric flat-top cubic cone array (16) is disposed on the surface of the highly reflective aluminum metal layer (13), and a surface layer is applied to the surface of the dielectric flat-top cubic cone array (16).

8. The space satellite thermal control system based on adaptive heat transport according to claim 7, characterized in that: The surface layer includes a vanadium dioxide phase change layer (14) coated on the surface of the medium flat-top cubic pyramid array (16), and a top protective layer (15) is applied to the surface of the vanadium dioxide phase change layer (14).

9. The space satellite thermal control system based on adaptive heat transport according to claim 7, characterized in that: After the thermochromic intelligent thermal control coating is prepared on the transferable film, it is transferred and bonded to the outer surface of the space satellite for fixation.

10. The space satellite thermal control system based on adaptive heat transport according to claim 7, characterized in that: The highly reflective aluminum metal layer (13) is deposited on the transferable film by magnetron sputtering, and the dielectric flat-top cubic pyramid array (16) is prepared on the highly reflective aluminum metal layer (13) by nanoimprinting.

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