Integrated heat dissipation structure of low-orbit satellite phased-array antenna

Abstract

The invention relates to an integrated heat dissipation structure of a low-orbit satellite phased-array antenna, and relates to the technical field of satellite heat dissipation. The integrated heat dissipation structure comprises a heat storage area, a heat conductor and an aluminum ammonia heat pipe which are arranged between a satellite body and a phased-array antenna, one end of the aluminum ammonia heat pipe is in contact with a heating device of the phased-array antenna, and the other end of the aluminum ammonia heat pipe is inserted into the heat conductor; the heat storage area is filled with a phase change material used for absorbing and storing heat, one side of the heat storage area is attached to a satellite body, and the other side of the heat storage area is attached to the heat conductor; the satellite body is further provided with a plurality of heat dissipation teeth used for dissipating heat in the heat storage area. Aiming at the characteristics that a low-orbit satellite is small in ground winding period and short in starting time, through the heat dissipation structure which comprehensively covers conduction, heat storage and radiation and is integrally designed, the heat dissipation requirement of the low-orbit satellite phased-array antenna can be better met, and the heat dissipation performance and reliability of the satellite-borne digital phased-array antenna are improved.

Description

Technical Field

[0001] The present application relates to the field of satellite heat dissipation technology, and in particular to an integrated heat dissipation structure of a low-orbit satellite phased array antenna. Background Art

[0002] Low-orbit satellites refer to satellites operating in low earth orbits, and their orbital altitudes are generally between 300 km and 2,000 km. The flight cycle of a low-orbit satellite is generally 2 to 3 hours, and the payload is powered on for no more than 20 minutes during this period. The low orbital altitude of the satellite results in short transmission delays and small path losses. Therefore, low-orbit satellites are also used for mobile phone communications. A communication system consisting of multiple low-orbit satellites can achieve true global coverage, and frequency reuse is more efficient. Low-orbit satellites are currently the newest and most promising satellite mobile communication system. Because their orbits are close to the earth, low-orbit satellites experience extreme temperature changes, so thermal control technology is essential to ensure their normal operation.

[0003] With the continuous advancement of satellite communication technology, digital phased array antennas have become an important technology for realizing direct connection between mobile phones and satellites because they can generate a large number of independent scanning beams at the same time and effectively improve the communication capacity of satellite payloads through space classification. The application of this technology has not only greatly expanded the capabilities of satellite communications, but also promoted the construction and development of seamless communication networks around the world. However, with the demand for high performance and multi-functions, digital multi-beam phased array antennas will generate a lot of heat during operation, which puts extremely high demands on the heat dissipation capacity of the satellite-borne platform.

[0004] In order to solve the heat dissipation problem of phased array antennas, the existing technology has proposed a variety of solutions. For example, in the related technology, a temperature plate module and a clamping ring with a liquid cooling channel are used to achieve heat dissipation of high-power chips.

[0005] Although the above technologies have alleviated the heat dissipation problem of phased array antennas in satellite communication systems to a certain extent, they can usually only solve the heat dissipation needs of a certain aspect and cannot take into account the comprehensive heat dissipation needs of high-heat-consuming satellite-borne products in complex space environments. That is, there is still a lack of an integrated heat dissipation structure that can fully cover conduction, heat storage, and radiation. Summary of the invention

[0006] In order to improve the heat dissipation effect of a low-orbit satellite phased array antenna and thereby ensure the stability, reliability and service life of its operation, the present application provides an integrated heat dissipation structure of a low-orbit satellite phased array antenna.

[0007] The integrated heat dissipation structure of a low-orbit satellite phased array antenna provided in this application adopts the following technical solution: An integrated heat dissipation structure of a low-orbit satellite phased array antenna, comprising a heat storage area, a heat conductor and a heat pipe arranged between a satellite body and the phased array antenna; One end of the heat pipe is in contact with the heating element of the phased array antenna, and the other end of the heat pipe is inserted into the heat conductor; The heat storage area is filled with a phase change material for absorbing and storing heat, one side of the heat storage area is directly or indirectly attached to one side of the satellite body, and the other side of the heat storage area is attached to the heat conductor; The satellite body is also provided with a plurality of heat dissipation teeth for dissipating the heat in the heat storage area.

[0008] In view of the characteristics of low-orbit satellites with short orbiting periods (generally 2 to 3 hours) and short startup time (the startup time of the payload does not exceed 20 minutes), this application combines the installation method of digital phased array antennas on low-orbit satellite platforms, integrates the heat storage area of ​​the phase change material and the satellite platform, and cooperates with the heat dissipation tooth design to propose a solution to the heat dissipation problem of satellite-borne digital multi-beam phased array antennas. By adopting the above technical solution, during the startup process of payloads such as low-orbit satellite phased array antennas, the heat generated during the operation of the heating device of the phased array antenna is first conducted to the heat storage area through the heat pipe and the heat conductor and absorbed and stored by the phase change material. Then, during the shutdown and orbiting process of the payload product, the stored heat is radiated to the space environment through the heat dissipation teeth. Through the integrated design scheme of conduction, heat storage, and radiation in this application, the engineering requirements of high-heat-consuming satellite-borne products in complex space environments are better met, the limitations of the existing technology are overcome, the heat dissipation performance of low-orbit satellite phased array antennas is improved, and it is ensured that it can operate stably and reliably, extending the service life of the satellite.

[0009] Optionally, the heat dissipation teeth are spaced apart and distributed on both sides of the satellite body and on both sides of the heat storage area.

[0010] By adopting the above technical solution, the number of heat dissipation teeth is sufficient and the contact area with the outside world is large enough, thereby effectively ensuring the heat dissipation effect and radiating the heat absorbed by the phase change material to the space environment quickly and efficiently.

[0011] Optionally, the heat dissipation teeth are metal sheets made of aluminum alloy, and the surface of the heat dissipation teeth is coated with a heat dissipation coating with high emissivity, and the heat dissipation coating is a nano-ceramic heat dissipation coating.

[0012] By adopting the above technical solution, the radiation efficiency of the heat dissipation teeth is improved, and heat can be quickly dissipated into the outer space through thermal radiation.

[0013] Optionally, a plurality of the heat dissipation teeth are asymmetrically arranged on both sides of the satellite body and the heat storage area, and a plurality of the heat dissipation teeth on the same side are staggered in the height direction; the two sides and the outer ends of the heat dissipation teeth are arranged in a wave tooth structure; The arrangement density of the heat dissipation teeth near the heat storage area is greater than that at other positions.

[0014] By adopting the above technical solution, the shape and arrangement of the heat dissipation teeth are optimized, and the radiation efficiency of the heat dissipation teeth is further improved, so that heat can be quickly dissipated into the outer space through thermal radiation.

[0015] Optionally, the heat storage area is divided into a first phase change layer, a second phase change layer and a third phase change layer in sequence from a side close to the phased array antenna to a side close to the satellite body. Phase change materials are arranged in the first phase change layer, the second phase change layer and the third phase change layer. The phase change material in the first phase change layer is n-tetradecane, the phase change material in the second phase change layer is n-hexadecane, and the phase change material in the third phase change layer is a paraffin-based phase change material formed by a mixture of straight-chain alkanes.

[0016] Paraffin phase change materials have high latent heat of fusion, a wide range of melting point temperatures (-5 to 66°C), are non-toxic and non-corrosive, have stable chemical properties below 500°C, and have little supercooling. The melting point of n-tetradecane is 6°C, the heat of fusion is 228 kJ / kg, and the melting point of n-hexadecane is 17°C, the heat of fusion is 237 kJ / kg; both have the advantages of large latent heat of phase change, small volume change of phase change, and a wide range of phase change temperature. They are non-toxic, non-corrosive, and have stable chemical properties, making them suitable for temperature control in space environments.

[0017] By adopting the above technical solution, the phase change material set in the first phase change layer can respond quickly and absorb heat quickly at the initial stage of the phased array antenna startup; the phase change material set in the second phase change layer can efficiently receive the heat transferred from the first phase change layer and transfer it downward, and the phase change material in the third phase change layer uses a large-capacity heat storage material to store a large amount of heat during long-term operation. As a result, the heat storage area in this application achieves stable and efficient heat absorption and storage.

[0018] Optionally, as another solution, the phase change material in the heat storage area is a phase change material of a eutectic mixture of tetradecanol (TD) and fatty acid; and graphene or carbon nanotubes are also provided in the phase change material.

[0019] By adopting the above technical solution, materials with different phase change temperatures are mixed, the effective operating temperature range of the phase change material is broadened, and the heat changes generated by the phased array antenna under different working conditions are better handled. Furthermore, in this application, by setting high thermal conductivity nanoparticles in the phase change material, the thermal conductivity of the phase change material can be improved, so that heat can be transferred and absorbed more quickly in the heat storage area, reducing local overheating.

[0020] Optionally, a high thermal conductivity base layer is tightly attached to the heating element of the phased array antenna, and the high thermal conductivity base layer is made of high-purity copper or aluminum.

[0021] By adopting the above technical solution, the heat on the heating device of the phased array antenna can be quickly transferred to the heat pipe by using the high thermal conductivity base layer, thereby dissipating heat efficiently.

[0022] Optionally, the heat pipe is an aluminum-ammonia heat pipe or a ceramic heat pipe.

[0023] Aluminum-ammonia heat pipes include aluminum alloy pipes, and capillary structures (such as mesh, fiber, powder sintering, grooves) are arranged inside the aluminum alloy pipes. Working fluids (such as ammonia) are arranged inside the capillary structures of the aluminum alloy pipes. Its operating temperature range is [-60℃, +80℃], and its storage temperature range is [-65℃, +90℃]. It has the characteristics of high thermal conductivity, excellent isothermal properties, and heat flux density variability. The material of ceramic heat pipes can be alumina ceramics (Alumina), aluminum nitride ceramics (AlN) or silicon carbide ceramics (SiC). The thermal conductivity can reach 80-120 W / (m·K). It also has high mechanical properties and excellent wear resistance, and can operate stably in high temperature environments.

[0024] Optionally, a graphene one-way heat sink is further arranged between the heat storage area and the surface of the satellite body, and the graphene one-way heat conduction plate includes a heat dissipation layer, a heat transfer layer and a heat absorption layer, the heat transfer layer is arranged between the heat dissipation layer and the heat absorption layer, the heat absorption layer faces the heat storage area, and the heat dissipation layer is closely attached to the surface of the satellite body; the heat transfer layer includes a heat insulation material layer and heat conductive microcapsules, the heat insulation material layer forms a honeycomb structure, and the heat conductive microcapsules are arranged in the honeycomb holes of the heat insulation material layer and are filled with gas or liquid.

[0025] By adopting the above technical solution, unidirectional heat conduction and heat dissipation can be achieved, avoiding bidirectional heat transfer, so that the heat generated by the phased array antenna can be efficiently dissipated, and when the satellite equipment as a whole faces the sun and is subject to greater heat radiation, the heat will not be transferred to the phased array antenna.

[0026] In summary, the present application includes at least one of the following beneficial technical effects: 1. The integrated design scheme of conduction, heat storage and radiation in this application better meets the engineering requirements of high heat consumption satellite-borne products in complex space environments, overcomes the limitations of existing technologies, improves the heat dissipation performance of low-orbit satellite phased array antennas, ensures that they can operate stably and reliably, and extends the service life of satellites. 2. In this application, by optimizing the shape and arrangement of the heat dissipation teeth, the radiation efficiency of the heat dissipation teeth is further improved, so that heat can be efficiently and quickly dissipated into space through thermal radiation.

[0027] 3. In this application, by setting a graphene unidirectional heat conduction plate, unidirectional heat conduction and heat dissipation can be achieved, avoiding two-way heat transfer, so that the heat generated by the phased array antenna can be efficiently dissipated. When the satellite equipment as a whole faces the sun and is subject to greater thermal radiation, the heat will not be transferred to the phased array antenna. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of the three-dimensional structure of the low-orbit satellite in this application.

[0029] Figure 2 It is a schematic diagram of the integrated heat dissipation structure in Example 1 of the present application.

[0030] Figure 3 It is a structural schematic diagram of the graphene one-way heat dissipation plate in this application.

[0031] Figure 4 It is a schematic diagram of the integrated heat dissipation structure in Example 2 of the present application.

[0032] In the figure: 10. Satellite body; 20. Phased array antenna; 21. Heating device; 30. Heat storage area; 31. First phase change layer; 32. Second phase change layer; 33. Third phase change layer; 34. Phase change material; 40. Heat conductor; 50. Heat pipe; 60. Heat dissipation teeth; 70. High thermal conductivity base layer; 80. Graphene one-way heat dissipation plate; 81. Heat dissipation layer; 82. Heat transfer layer; 821. Heat insulation material layer; 822. Heat conductive microcapsule; 83. Heat absorption layer. DETAILED DESCRIPTION

[0033] The following will be combined with the attached Figure 1 -Attached Figure 4 , the technical solutions in the embodiments of the present invention are clearly and completely described. The described embodiments are only possible technical implementations of the present invention, not all possible implementations. Those skilled in the art can completely combine the embodiments of the present invention to obtain other embodiments without creative work, and these embodiments are also within the scope of protection of the present invention.

[0034] Example 1 Reference Figure 1 and Figure 2As shown, the integrated heat dissipation structure of the low-orbit satellite phased array antenna in the present application includes a heat storage area 30, a heat conductor 40 and a heat pipe 50 arranged between the satellite body 10 and the phased array antenna 20. The heat pipe 50 can be an aluminum-ammonia heat pipe, which includes an aluminum alloy pipe, and a capillary structure (such as mesh, fiber, powder sintering, groove) is arranged in the aluminum alloy pipe, and a working fluid (such as ammonia) is arranged in the capillary structure of the aluminum alloy pipe. Its operating temperature range is [-60°C, +80°C], and the storage temperature range is [-65°C, +90°C]. It has the characteristics of high thermal conductivity, excellent isothermal property, and heat flux density variability. The heat pipe 50 can also be a ceramic heat pipe. The material of the ceramic heat pipe can be alumina ceramic (Alumina), aluminum nitride ceramic (AlN) or silicon carbide ceramic (SiC). Its thermal conductivity can reach 80-120 W / (m·K). It also has high mechanical properties and excellent wear resistance, and can operate stably in a high temperature environment. The heat conductor 40 can be a copper plate, and a high thermal conductivity base layer 70 is tightly attached to the heating device 21 of the phased array antenna 20. The high thermal conductivity base layer 70 is made of high-purity copper or aluminum. One end of the heat pipe 50 is directly in contact with the heating device 21 of the phased array antenna 20 or inserted in the high thermal conductivity base layer 70, and the other end of the heat pipe 50 is inserted in the heat conductor 40; the high thermal conductivity base layer 70 can quickly transfer the heat on the heating device 21 of the phased array antenna 20 to the heat pipe 50, thereby efficiently transferring heat forward.

[0035] In the present application, the heat storage area 30 is filled with a phase change material 34 for absorbing and storing heat. The phase change material 34 in the heat storage area 30 is a phase change material using a eutectic mixture of tetradecanol (TD) and fatty acids; graphene or carbon nanotubes are also provided in the phase change material 34. By mixing materials with different phase change temperatures, the effective operating temperature range of the phase change material 34 is broadened, and the heat changes generated by the phased array antenna 20 under different working conditions are better coped with. Furthermore, in the present application, by providing high thermal conductivity nanoparticles in the phase change material 34, the thermal conductivity of the phase change material 34 can be improved, so that heat can be transferred and absorbed more quickly in the heat storage area 30, reducing local overheating.

[0036] Reference Figure 2 and Figure 3As shown, one side of the heat storage area 30 faces the surface of the satellite body 10, and the other side of the heat storage area 30 is in contact with the heat conductor 40. Furthermore, a graphene one-way heat sink 80 is arranged between the heat storage area 30 and the surface of the satellite body 10. The graphene one-way heat conduction plate includes a heat dissipation layer 81, a heat transfer layer 82 and a heat absorption layer 83. The heat transfer layer 82 is arranged between the heat dissipation layer 81 and the heat absorption layer 83. The heat absorption layer 83 faces the heat storage area 30, and the heat dissipation layer 81 is in contact with the surface of the satellite body 10; the heat transfer layer 82 includes a heat insulation material layer 821 and a heat conductive microcapsule 822. The heat insulation material layer 821 forms a honeycomb structure, and the heat conductive microcapsule 822 is arranged in the honeycomb holes of the heat insulation material layer 821 and filled with gas or liquid; in this way, one-way heat conduction and heat dissipation can be achieved, and two-way heat transfer can be avoided. Thereby, the heat generated by the phased array antenna 20 can be efficiently dissipated, and when the satellite equipment as a whole faces the sun and is subjected to greater heat radiation, the heat will not be transferred to the phased array antenna 20.

[0037] Reference Figure 2 As shown, the satellite body 10 is also provided with a number of heat dissipation teeth 60 for dissipating the heat in the heat storage area 30. Specifically, the heat dissipation teeth 60 are metal sheets made of aluminum alloy, and the surface of the heat dissipation teeth 60 is coated with a heat dissipation coating with high emissivity, and the heat dissipation coating is a nano-ceramic heat dissipation coating. The heat dissipation teeth 60 are distributed asymmetrically at intervals on both sides of the satellite body 10, on both sides of the heat storage area 30, on both sides of the heat conductor 40, and on both sides of the phased array antenna 20. Moreover, several heat dissipation teeth 60 on the same side are staggered in the height direction; the two sides and the outer end of the heat dissipation teeth 60 are arranged in a wavy tooth structure; the arrangement density of the heat dissipation teeth 60 near the heat storage area 30 is greater than the arrangement density at other positions. In the present application, the number of heat dissipation teeth 60 is sufficient, the contact area with the outside world is large enough, and by optimizing the shape and arrangement of the heat dissipation teeth 60, the radiation efficiency of the heat dissipation teeth 60 is greatly improved, so that the heat can be quickly and efficiently dissipated into the universe through thermal radiation.

[0038] The implementation principle is as follows: This application aims at the characteristics of low-orbit satellites with short orbiting periods (generally 2 to 3 hours) and short startup time (the startup time of the payload does not exceed 20 minutes), and combines the installation method of the digital phased array antenna 20 on the low-orbit satellite platform to integrate the heat storage area 30 of the phase change material 34 and the satellite platform, and cooperates with the design of the heat dissipation teeth 60 to propose a solution to the heat dissipation problem of the satellite-borne digital multi-beam phased array antenna 20. During the startup process of the low-orbit satellite phased array antenna 20 and other payloads, the heat generated during the operation of the heating device 21 of the phased array antenna 20 is first conducted to the heat storage area 30 through the heat pipe 50 and the heat conductor 40 and absorbed and stored by the phase change material 34. Then, when the payload product is shut down and flies around the earth, the stored heat is radiated to the space environment through the heat dissipation teeth 60.

[0039] This technical solution realizes the integrated integration of conduction, heat storage and radiation heat dissipation functions. Compared with the existing single heat dissipation method or non-integrated heat dissipation structure, it can more comprehensively and efficiently handle the large amount of heat consumption of the digital multi-beam phased array antenna 20, and improve the heat dissipation efficiency by more than 40%; it effectively solves the heat dissipation problem caused by space and weight limitations of the satellite platform, improves the reliability and stability of satellite-borne products, extends their service life, and reduces the cost of fault repair and replacement caused by overheating, and has significant economic benefits and application value.

[0040] Example 2 Reference Figure 4 As shown, this embodiment is substantially the same as embodiment 1, except that, in this embodiment, the heat storage area 30 is sequentially divided into a first phase change layer 31, a second phase change layer 32 and a third phase change layer 33 from a side close to the phased array antenna 20 to a side close to the satellite body 10, and phase change materials 34 are provided in the first phase change layer 31, the second phase change layer 32 and the third phase change layer 33. The phase change material 34 in the first phase change layer 31 is n-tetradecane, the phase change material 34 in the second phase change layer 32 is n-hexadecane, and the phase change material 34 in the third phase change layer 33 is a paraffin phase change material formed by a mixture of straight-chain alkanes.

[0041] Paraffin phase change materials have high latent heat of fusion, a wide range of melting point temperatures (-5 to 66°C), are non-toxic and non-corrosive, have stable chemical properties below 500°C, and have little supercooling. The melting point of n-tetradecane is 6°C, the heat of fusion is 228 kJ / kg, and the melting point of n-hexadecane is 17°C, the heat of fusion is 237 kJ / kg; both have the advantages of large latent heat of phase change, small volume change of phase change, and a wide range of phase change temperature. They are non-toxic, non-corrosive, and have stable chemical properties, making them suitable for temperature control in space environments.

[0042] The phase change material 34 set in the first phase change layer 31 of the present application can respond quickly and is used to quickly absorb heat at the initial startup of the phased array antenna 20; the phase change material 34 set in the second phase change layer 32 can efficiently receive the heat transferred from the first phase change layer 31 and transfer it downward, and the phase change material 34 in the third phase change layer 33 uses a large-capacity heat storage material to store a large amount of heat during long-term operation. As a result, the heat storage area 30 in the present application achieves stable and efficient heat absorption and heat storage.

[0043] The embodiments of this specific implementation are all preferred embodiments of the present application, and are not intended to limit the protection scope of the present application. The same components are represented by the same figure marks. Therefore, any equivalent changes made based on the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. An integrated heat dissipation structure for a low-orbit satellite phased array antenna, characterized in that: It comprises a heat storage area (30), a heat conductor (40) and a heat pipe (50) arranged between a satellite body (10) and a phased array antenna (20); One end of the heat pipe (50) is in contact with the heating element (21) of the phased array antenna (20), and the other end of the heat pipe (50) is inserted into the heat conductor (40); The heat storage area (30) is filled with a phase change material (34) for absorbing and storing heat, one side of the heat storage area (30) is directly or indirectly attached to one side of the satellite body (10), and the other side of the heat storage area (30) is attached to the heat conductor (40); The satellite body (10) is also provided with a plurality of heat dissipation teeth (60) for dissipating the heat in the heat storage area (30).

2. The integrated heat dissipation structure of the low-orbit satellite phased array antenna according to claim 1, characterized in that: The heat dissipation teeth (60) are distributed at intervals on both sides of the satellite body (10) and on both sides of the heat storage area (30).

3. The integrated heat dissipation structure of the low-orbit satellite phased array antenna according to claim 2, characterized in that: The heat dissipation teeth (60) are metal sheets made of aluminum alloy, and the surfaces of the heat dissipation teeth (60) are coated with a heat dissipation coating with a high emissivity, wherein the heat dissipation coating is a nano-ceramic heat dissipation coating.

4. The integrated heat dissipation structure of the low-orbit satellite phased array antenna according to claim 2 or 3, characterized in that: A plurality of the heat dissipation teeth (60) are asymmetrically arranged on both sides of the satellite body (10) and the heat storage area (30), and a plurality of the heat dissipation teeth (60) on the same side are staggered in the height direction; both sides and outer ends of the heat dissipation teeth (60) are arranged in a wave tooth structure; The arrangement density of the heat dissipation teeth (60) at positions close to the heat storage area (30) is greater than the arrangement density at other positions.

5. The integrated heat dissipation structure of the low-orbit satellite phased array antenna according to claim 1, 2 or 3, characterized in that: The heat storage area (30) is divided into a first phase change layer (31), a second phase change layer (32) and a third phase change layer (33) in sequence from a side close to the phased array antenna (20) to a side close to the satellite body (10). Phase change materials (34) are arranged in the first phase change layer (31), the second phase change layer (32) and the third phase change layer (33). The phase change material (34) in the first phase change layer (31) is n-tetradecane, the phase change material (34) in the second phase change layer (32) is n-hexadecane, and the phase change material (34) in the third phase change layer (33) is a paraffin phase change material formed by a mixture of straight-chain alkanes.

6. The integrated heat dissipation structure of the low-orbit satellite phased array antenna according to claim 1, 2 or 3, characterized in that: The phase change material (34) in the heat storage area (30) is a phase change material of a tetradecanol (TD) and fatty acid eutectic mixture; graphene or carbon nanotubes are also arranged in the phase change material (34).

7. The integrated heat dissipation structure of the low-orbit satellite phased array antenna according to claim 1, 2 or 3, characterized in that: A high thermal conductivity base layer (70) is tightly attached to the heating element (21) of the phased array antenna (20), and the high thermal conductivity base layer (70) is made of high-purity copper or aluminum.

8. The integrated heat dissipation structure of the low-orbit satellite phased array antenna according to claim 1, 2 or 3, characterized in that: The heat conducting pipe (50) is an aluminum-ammonia heat pipe or a ceramic heat pipe.

9. The integrated heat dissipation structure of the low-orbit satellite phased array antenna according to claim 1, 2 or 3, characterized in that: A graphene one-way heat dissipation plate (80) is also arranged between the heat storage area (30) and the surface of the satellite body (10). The graphene one-way heat conduction plate comprises a heat dissipation layer (81), a heat transfer layer (82) and a heat absorption layer (83). The heat transfer layer (82) is arranged between the heat dissipation layer (81) and the heat absorption layer (83). The heat absorption layer (83) faces the heat storage area (30). The heat dissipation layer (81) is in close contact with the surface of the satellite body (10). The heat transfer layer (82) comprises a heat insulation material layer (821) and heat conductive microcapsules (822). The heat insulation material layer (821) forms a honeycomb structure. The heat conductive microcapsules (822) are arranged in the honeycomb holes of the heat insulation material layer (821) and are filled with gas or liquid.

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