An integrated heat dissipation structure for a phased array antenna of a low-earth orbit satellite

Abstract

The present application relates to an integrated heat dissipation structure for a phased array antenna of a low-orbit satellite, and relates to the technical field of satellite heat dissipation. The integrated heat dissipation structure in the present application includes a heat storage area, a heat conductor, and an aluminum nitride heat pipe disposed between the satellite body and the phased array antenna; one end of the aluminum nitride heat pipe is in contact with the heat generating device of the phased array antenna, and the other end of the aluminum nitride 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 in contact with the satellite body, and the other side of the heat storage area is in contact with the heat conductor; a plurality of heat dissipation teeth for dissipating the heat in the heat storage area are further provided on the satellite body. In the present application, aiming at the characteristics of a low-orbit satellite with a short orbital period around the earth and a short startup time, through an integrated heat dissipation structure with an overall design covering conduction, heat storage, and radiation, it can better meet the heat dissipation requirements of the phased array antenna of the low-orbit satellite, and improve the heat dissipation performance and reliability of the spaceborne digital phased array antenna.

Description

Technical Field

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

[0002] A low-earth orbit satellite refers to a satellite operating in a low-earth orbit, with its orbital altitude generally between 300 kilometers and 2000 kilometers. The flight period of a low-earth orbit satellite is generally 2 - 3 hours, and the on-time duration of the payload within this time period does not exceed 20 minutes. The low orbital altitude of the satellite results in short transmission delay and small path loss. Therefore, low-earth orbit satellites are also used for mobile phone communication. A communication system composed of multiple low-earth orbit satellites can achieve true global coverage, and frequency reuse is more effective. Low-earth orbit satellites are currently the latest and most promising satellite mobile communication systems. Due to their orbits being close to the Earth, low-earth orbit satellites will experience extreme temperature changes. Therefore, thermal control technology is crucial for ensuring their normal operation.

[0003] With the continuous progress of satellite communication technology, digital phased array antennas have become an important technology for realizing direct satellite connection for mobile phones because they can simultaneously generate a large number of independent scanning beams and effectively improve the communication capacity of satellite payloads through spatial grading. The application of this technology not only greatly expands the capabilities of satellite communication but also promotes the construction and development of a seamless communication network globally. However, along with the requirements for high performance and multi-functionality, digital multi-beam phased array antennas generate a large amount of heat during operation, which poses extremely high requirements for the heat dissipation capacity of the spaceborne platform.

[0004] To address the heat dissipation problem of phased array antennas, various solutions have been proposed in existing technologies. For example, in related technologies, a heat dissipation of high-power chips is achieved through a heat pipe module and a clamping ring with a liquid cooling channel.

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

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

[0007] The integrated heat dissipation structure for a phased array antenna of a low-earth orbit satellite provided by the present application adopts the following technical solutions:

[0008] An integrated heat dissipation structure for a phased array antenna of a low-earth orbit satellite, comprising a heat storage area, a heat conductor and a heat conduction tube arranged between the satellite body and the phased array antenna;

[0009] One end of the heat conduction tube is in contact with the heat generating device of the phased array antenna, and the other end of the heat conduction tube is inserted into the heat conductor;

[0010] 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 abutted against one side of the satellite body, and the other side of the heat storage area is abutted against the heat conductor;

[0011] A number of heat dissipation teeth are also arranged on the satellite body for dissipating the heat in the heat storage area to the outside.

[0012] In this application, aiming at the characteristics of low-earth orbit satellites with a small orbital period around the earth (generally 2-3 hours) and a short startup time (the startup duration of the payload does not exceed 20 minutes), combined with the installation method of the digital phased array antenna on the low-earth orbit satellite platform, an integrated design of the heat storage area of the phase change material and the satellite platform is carried out, and combined with the heat dissipation tooth design, a solution to the heat dissipation problem of the spaceborne digital multi-beam phased array antenna is proposed. By adopting the above technical solutions, during the startup process of payloads such as the phased array antenna of the low-earth orbit satellite, the heat generated during the operation of the heat generating device of the phased array antenna is first conducted to the heat storage area through the heat conduction tube and the heat conductor and absorbed and stored by the phase change material. Then, during the process of the payload product shutting down and flying around the earth, 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, it better meets the engineering requirements of high heat consumption spaceborne products in complex space environments, overcomes the limitations of the existing technology, improves the heat dissipation performance of the phased array antenna of the low-earth orbit satellite, ensures its stable and reliable operation, and extends the service life of the satellite.

[0013] Optionally, the heat dissipation teeth are distributed at intervals on both sides of the satellite body and on both sides of the heat storage area.

[0014] By adopting the above technical solutions, the number of heat dissipation teeth is sufficient and the contact area with the outside is large enough, so as to effectively guarantee the heat dissipation effect and quickly and efficiently radiate the heat absorbed by the phase change material to the space environment.

[0015] Optionally, the heat dissipation teeth are metal sheets made of aluminum alloy material, and the surface of the heat dissipation teeth is coated with a heat dissipation coating with a high emissivity, and the heat dissipation coating is a nano-ceramic heat dissipation coating.

[0016] By adopting the above technical solutions, the radiation efficiency of the heat dissipation teeth is improved, and the heat can be quickly dissipated into the cosmic space through thermal radiation.

[0017] Optionally, several of the heat dissipation teeth are asymmetrically arranged on both sides of the satellite body and the heat storage area, and several of the heat dissipation teeth on the same side are staggered in the height direction; both sides and the outer ends of the heat dissipation teeth are provided with a wavy tooth structure;

[0018] The arrangement density of the heat dissipation teeth near the heat storage area is greater than that of other positions.

[0019] By adopting the above technical solution, the shape and arrangement of the heat dissipation teeth are optimized, and further, the radiation efficiency of the heat dissipation teeth is improved, so that heat can be quickly dissipated into the cosmic space through thermal radiation.

[0020] Optionally, the heat storage area is sequentially divided into a first phase change layer, a second phase change layer, and a third phase change layer from the side close to the phased array antenna to the 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 mixed by straight-chain alkanes.

[0021] The paraffin-based phase change material has a high melting latent heat, a wide range of selectable melting point temperatures (-5 to 66 °C), is non-toxic, non-corrosive, chemically stable below 500 °C, and has a small supercooling phenomenon. The melting point of n-tetradecane is 6 °C, and the melting heat is 228 kJ / kg. The melting point of n-hexadecane is 17 °C, and the melting heat is 237 kJ / kg; both have the advantages of large phase change latent heat, small phase change volume change, wide phase change temperature range, and are non-toxic, non-corrosive, and chemically stable, and are suitable for temperature control in the space environment.

[0022] By adopting the above technical solution, the phase change material arranged in the first phase change layer can respond quickly and is used to quickly absorb heat at the initial stage of the phased array antenna startup; the phase change material arranged in the second phase change layer can efficiently receive the heat transferred from the first phase change layer and transfer it downward. 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. Thus, the heat storage area in the present application realizes stable and efficient heat absorption and heat storage.

[0023] Optionally, as another solution, the phase change material in the heat storage area is a eutectic mixture phase change material of tetradecanol (TD) and fatty acid; graphene or carbon nanotubes are also arranged in the phase change material.

[0024] By adopting the above technical solution, materials with different phase change temperatures are mixed, which broadens the effective working temperature range of the phase change material and better responds to the heat changes generated by the phased array antenna under different working conditions. Further, in this application, by setting nanoparticles with high thermal conductivity in the phase change material, the thermal conductivity of the phase change material can be improved, enabling heat to be transferred and absorbed more quickly in the heat storage area and reducing local overheating phenomena.

[0025] Optionally, a high thermal conductivity base layer is closely attached to the heating device of the phased array antenna, and the high thermal conductivity base layer is made of high-purity copper or aluminum.

[0026] By adopting the above technical solution, the high thermal conductivity base layer can quickly conduct the heat on the heating device of the phased array antenna to the heat pipe, thereby achieving efficient heat dissipation.

[0027] Optionally, the heat pipe is an aluminum-ammonia heat pipe or a ceramic heat pipe.

[0028] The aluminum-ammonia heat pipe includes an aluminum alloy pipe. A capillary structure (such as a mesh, fiber, powder sintering, or groove) is provided inside the aluminum alloy pipe, and a working fluid (such as ammonia) is provided inside 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 characteristics such as high thermal conductivity, excellent isothermal property, and variable heat flux density. The material of the ceramic heat pipe can be alumina ceramic (Alumina), aluminum nitride ceramic (AlN), or silicon carbide ceramic (SiC), and 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.

[0029] Optionally, a graphene unidirectional heat dissipation plate is further provided between the heat storage area and the surface of the satellite body. The graphene unidirectional heat conduction plate includes a heat dissipation layer, a heat transfer layer, and an endothermic layer. The heat transfer layer is provided between the heat dissipation layer and the endothermic layer. The endothermic 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 conduction microcapsules. The heat insulation material layer forms a honeycomb structure, and the heat conduction microcapsules are provided in the honeycomb holes of the heat insulation material layer and filled with gas or liquid.

[0030] By adopting the above technical solution, unidirectional heat conduction and heat dissipation can be achieved, avoiding bidirectional heat transfer. Thus, the heat generated by the phased array antenna can be efficiently dissipated, and when the satellite equipment as a whole is facing the sun and receiving a large amount of thermal radiation, the heat will not be transferred to the phased array antenna.

[0031] In summary, this application includes at least one of the following beneficial technical effects:

[0032] 1. The integrated design solution of conduction, heat storage, and radiation in this application better meets the engineering requirements of high-power spaceborne products in complex space environments, overcomes the limitations of existing technologies, improves the heat dissipation performance of phased array antennas on low-earth orbit satellites, ensures their stable and reliable operation, and extends the service life of satellites. 2. By optimizing the shape and arrangement of heat dissipation teeth in this application, the radiation efficiency of the heat dissipation teeth is further improved, so that heat can be efficiently and quickly dissipated into the cosmic space through thermal radiation.

[0033] 3. By setting up a graphene unidirectional heat conduction plate in this application, 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. When the satellite equipment as a whole is facing the sun and receiving a large amount of thermal radiation, the heat will not be transferred to the phased array antenna. Brief Description of the Drawings

[0034] Figure 1 It is a three-dimensional structural schematic diagram of a low-earth orbit satellite in this application.

[0035] Figure 2 It is a schematic diagram of the integrated heat dissipation structure in Embodiment 1 of this application.

[0036] Figure 3 It is a structural schematic diagram of the graphene unidirectional heat dissipation plate in this application.

[0037] Figure 4 It is a schematic diagram of the integrated heat dissipation structure in Embodiment 2 of this application.

[0038] In the figure:

[0039] 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 conduction tube; 60. Heat dissipation teeth; 70. High thermal conductivity base layer; 80. Graphene unidirectional heat dissipation plate; 81. Heat dissipation layer; 82. Heat transfer layer; 821. Thermal insulation material layer; 822. Thermal conductive microcapsule; 83. Heat absorption layer. Detailed Embodiments

[0040] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the attached Figure 1 - attached Figure 4 , and 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 and obtain other embodiments without creative labor, and these embodiments are also within the protection scope of the present invention.

[0041] Embodiment 1

[0042] Referring to Figure 1 and Figure 2 as shown, the integrated heat dissipation structure of the low-earth orbit satellite phased array antenna in this application includes a heat storage area 30, a heat conductor 40, and a heat pipe 50 disposed 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. A capillary structure (such as a mesh, fiber, powder sintering, or groove) is provided inside the aluminum alloy pipe, and a working fluid (such as ammonia) is provided inside the capillary structure of the aluminum alloy pipe. Its operating temperature range is [-60°C, +80°C], and its storage temperature range is [-65°C, +90°C]. It has characteristics such as high thermal conductivity, excellent isothermal property, and variable heat flux density. The heat pipe 50 can also be a ceramic heat pipe, and 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), and 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. A high-thermal-conductivity base layer 70 is closely 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 in direct contact with the heating device 21 of the phased array antenna 20 or inserted into the high-thermal-conductivity base layer 70, and the other end of the heat pipe 50 is inserted into the heat conductor 40; the high-thermal-conductivity base layer 70 can quickly conduct the heat on the heating device 21 of the phased array antenna 20 to the heat pipe 50, so as to efficiently transfer and dissipate heat forward.

[0043] In this 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 eutectic mixture phase change material of tetradecanol (TD) and fatty acid; graphene or carbon nanotubes are also provided in the phase change material 34. By mixing materials with different phase change temperatures, the effective working 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 can be better handled. Further, in this application, by setting high-thermal-conductivity nanoparticles in the phase change material 34, the thermal conductivity of the phase change material 34 can be increased, so that heat can be transferred and absorbed more quickly in the heat storage area 30, and local overheating can be reduced.

[0044] Referring to Figure 2 and Figure 3As shown in the figure, 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. Further, a graphene unidirectional heat dissipation plate 80 is also provided between the heat storage area 30 and the surface of the satellite body 10. The graphene unidirectional heat conduction plate includes a heat dissipation layer 81, a heat transfer layer 82, and an endothermic layer 83. The heat transfer layer 82 is disposed between the heat dissipation layer 81 and the endothermic layer 83. The endothermic layer 83 faces the heat storage area 30, and the heat dissipation layer 81 is in close contact with the surface of the satellite body 10. The heat transfer layer 82 includes a heat insulation material layer 821 and heat conduction microcapsules 822. The heat insulation material layer 821 forms a honeycomb structure, and the heat conduction microcapsules 822 are disposed in the honeycomb holes of the heat insulation material layer 821 and filled with gas or liquid. In this way, unidirectional heat conduction and heat dissipation can be achieved, avoiding bidirectional heat transfer. Thus, the heat generated by the phased array antenna 20 can be efficiently dissipated, and when the satellite equipment is facing the sun as a whole and receiving a large amount of thermal radiation, the heat will not be transferred to the phased array antenna 20.

[0045] Referring to Figure 2 As shown in the figure, a number of heat dissipation teeth 60 for dissipating the heat in the heat storage area 30 are also provided on the satellite body 10. Specifically, the heat dissipation teeth 60 are metal sheets made of aluminum alloy material. The surface of the heat dissipation teeth 60 is coated with a heat dissipation coating with a high emissivity, and the heat dissipation coating is a nano-ceramic heat dissipation coating. The heat dissipation teeth 60 are asymmetrically and spacedly distributed on both sides of the satellite body 10, both sides of the heat storage area 30, both sides of the heat conductor 40, and both sides of the phased array antenna 20. Moreover, a number of heat dissipation teeth 60 on the same side are staggered in the height direction; both sides and the outer ends of the heat dissipation teeth 60 are provided with a wavy tooth structure; the arrangement density of the heat dissipation teeth 60 near the heat storage area 30 is greater than that of other positions. In this application, the number of the heat dissipation teeth 60 is large enough, and the contact area with the outside world is large enough. Moreover, 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 efficiently and quickly dissipated into the cosmic space through thermal radiation.

[0046] The implementation principle is as follows: In view of the characteristics of low-orbit satellites with a small orbital period around the earth (generally 2 - 3 hours) and a short on-time (the on-time of the payload does not exceed 20 minutes), combined with the installation method of the digital phased array antenna 20 on the low-orbit satellite platform, the heat storage area 30 of the phase change material 34 and the satellite platform are integrally designed, and in cooperation with the design of the heat dissipation teeth 60, a solution to the heat dissipation problem of the spaceborne digital multi-beam phased array antenna 20 is proposed. During the startup process of the payloads such as the low-orbit satellite phased array antenna 20, 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 conduction tube 50 and the heat conductor 40 and absorbed and stored by the phase change material 34. Then, during the flight of the payload product after shutdown around the earth, the stored heat is radiated to the space environment through the heat dissipation teeth 60.

[0047] 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 handle the large amount of heat dissipation of the digital multi-beam phased array antenna 20 more comprehensively and efficiently, increasing the heat dissipation efficiency by more than 40%; effectively solving the heat dissipation problem caused by space and weight limitations in the spaceborne platform, improving the reliability and stability of spaceborne products, extending their service life, reducing the cost of fault repair and replacement caused by overheating, and having significant economic benefits and application value.

[0048] Embodiment 2

[0049] Refer to Figure 4 As shown, this embodiment is substantially the same as Embodiment 1. The difference is that in this embodiment, the heat storage area 30 is successively divided into a first phase change layer 31, a second phase change layer 32, and a third phase change layer 33 from the side close to the phased array antenna 20 to the side close to the satellite body 10. 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-based phase change material composed of straight-chain alkanes.

[0050] Paraffin-based phase change materials have high latent heat of fusion, a wide range of selectable melting point temperatures (-5 to 66 °C), are non-toxic, non-corrosive, chemically stable below 500 °C, and have little supercooling phenomenon. The melting point of n-tetradecane is 6 °C and the heat of fusion is 228 kJ / kg. The melting point of n-hexadecane is 17 °C and the heat of fusion is 237 kJ / kg; both have the advantages of relatively large phase change latent heat, small phase change volume change, and a wide phase change temperature range, and are non-toxic, non-corrosive, and chemically stable, suitable for temperature control in the space environment.

[0051] The phase change material 34 provided in the first phase change layer 31 in this application can respond quickly and is used to rapidly absorb heat in the initial stage of the phased array antenna 20 being turned on; the phase change material 34 provided in the second phase change layer 32 can efficiently receive the heat transferred from the first phase change layer 31 and transfer it downward. The phase change material 34 in the third phase change layer 33 uses a large-capacity heat storage material and is used to store a large amount of heat during long-term operation. Thus, the heat storage area 30 in this application realizes stable and efficient heat absorption and storage.

[0052] The embodiments of this specific implementation manner are all preferred embodiments of this application, and do not limit the protection scope of this application accordingly. The same components are denoted by the same reference numerals. Therefore: All equivalent changes made according to the structure, shape, and principle of this application should be covered within the protection scope of this application.

Claims

1. An integrated heat dissipation structure for a phased array antenna of a low-earth orbit satellite, characterized in that It includes a heat storage area (30), a heat conductor (40) and a heat conduction tube (50) arranged between a satellite body (10) and a phased array antenna (20); One end of the heat conduction tube (50) is in contact with a heating device (21) of the phased array antenna (20), and the other end of the heat conduction tube (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 abutted against one side of the satellite body (10), and the other side of the heat storage area (30) is abutted against the heat conductor (40); A number of heat dissipation teeth (60) for dissipating the heat in the heat storage area (30) are also arranged on the satellite body (10); The heat dissipation teeth (60) are spaced apart and distributed on both sides of the satellite body (10) and both sides of the heat storage area (30); the heat dissipation teeth (60) are metal sheets made of aluminum alloy material, and the surface of the heat dissipation teeth (60) is coated with a heat dissipation coating with a high emissivity, and the heat dissipation coating is a nano-ceramic heat dissipation coating; a number 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 number of the heat dissipation teeth (60) on the same side are staggered in the height direction; both sides and the outer ends 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 that of other positions; 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 the side close to the phased array antenna (20) to the 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-based phase change material mixed by straight-chain alkanes.

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

3. The integrated heat dissipation structure of the low-earth orbit satellite phased array antenna according to claim 1, wherein The heat conduction tube (50) is an aluminum-nitrogen heat pipe or a ceramic heat pipe.

4. The integrated heat dissipation structure of the low-earth orbit satellite phased array antenna according to claim 1, wherein A graphene unidirectional heat dissipation plate (80) is further provided between the heat storage area (30) and the surface of the satellite body (10). The graphene unidirectional heat dissipation plate (80) includes a heat dissipation layer (81), a heat transfer layer (82), and a heat absorption layer (83). The heat transfer layer (82) is disposed 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 close contact with the surface of the satellite body (10). The heat transfer layer (82) includes a heat insulation material layer (821) and heat conduction microcapsules (822). The heat insulation material layer (821) forms a honeycomb structure, and the heat conduction microcapsules (822) are disposed in the honeycomb holes of the heat insulation material layer (821) and filled with gas or liquid.

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