Heat-conducting and radiating integrated thermal control film for satellite

Abstract

The application provides a high-thermal-conductivity heat dissipation integrated composite heat control film for satellites, which comprises a protective layer, a nano heat control film and a graphite film. The nano heat control film comprises a protective layer based on the surface of the film and a three-dimensional micro-nano structure, the graphite film is packaged by hot melt adhesive and is pasted together with the nano heat control film by the hot melt adhesive to form a new high-thermal-conductivity heat dissipation integrated composite heat control film. The application is pasted on the outer surface of a satellite cabin plate or an antenna and the like by silicone rubber, so that the outer surface of the satellite has the characteristics of high reflectivity to the solar spectrum, high emissivity to the infrared spectrum and high thermal conductivity, the uniformity of the temperature field of the whole satellite is improved, the reliability of the single machine in the cabin is improved, the production cycle of the product is short and the product is convenient to implement. The application solves the problems of high heat flux density, complex illumination components and rapid development of future low-orbit satellite constellations, the production cost is significantly reduced, and the commercial batch production of the satellite constellations is facilitated.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of satellite thermal control, and particularly relates to a heat-conducting and heat-dissipating integrated thermal control film for satellites. BACKGROUND

[0002] With the development of commercial space technology, new requirements are put forward for the satellite heat dissipation capacity, manufacturing cost and development cycle. The satellite external heat flux changes greatly under different orbits, the heat is more concentrated with higher single machine integration, and the thermal design difficulty is increased.

[0003] Patent document CN106799872A discloses a thermal control film with controllable emissivity, which can realize the adjustment and control of different emissivity by adjusting the thickness of the reflection layer. The infrared emissivity can be adjusted between 0.3 and 0.7. The thermal control material in the patent document has relatively high absorption and limited heat dissipation capacity, and does not have lateral heat conduction capacity.

[0004] Patent document CN104561897A discloses a film for changing the temperature control capacity of intelligent thermal control material and a preparation method thereof. A material with high infrared transmittance and low solar absorptivity is plated on the surface of the intelligent thermal control material to reduce the solar absorptivity, improve the self-temperature control capacity and expand the application range. In the patent document, the solar absorptivity is reduced, but there is still room for reduction. The heat dissipation capacity needs to be further improved, and the lateral heat conduction capacity is also not provided.

[0005] Patent document CN106756797A discloses an achromatic transparent polyimide film plated with an aluminum thermal control coating and a preparation method thereof. The ratio of the solar absorptivity to the infrared emissivity of the thermal control coating is 0.3, which belongs to a middle-absorption-ratio secondary surface mirror thermal control coating material, enriches the variety of flexible thermal control coating materials and fills the gap between 0.1 and 0.6. The absorption-emission ratio of the patent document is moderate, and the heat dissipation capacity is limited.

[0006] Patent document CN116648043A discloses a graphene film skin thermal control device. The device provides a rapid heat diffusion device through a graphene skin radiator and a paraffin phase change material. The device has a certain energy storage capacity. The present application has stronger heat dissipation capacity in outer space. The thickness of the graphene film is thicker than that of graphene, and the heat transfer capacity is stronger.

[0007] Patent document CN106255388A discloses an external single machine expansion heat dissipation device. The device uses a conventional thermal control product U-shaped aluminum plate to expand heat and a thermal control coating S781 to dissipate heat. In the present application, the lightweight high-thermal-conductivity graphite film has a weight of only 1 / 10 of the aluminum plate under the same heat conduction capacity. The absorption ratio of the new nano thermal control film is much lower than that of the S781 thermal control coating, and the heat dissipation and heat expansion performance is better.

[0008] For future low-orbit satellite constellation, through new type of integrated thermal control film, facing high heat flux density, complex light condition, the satellite low cost and batch production, it is the first time in China. The conventional satellite thermal implementation adopts spraying thermal control coating method, the conventional thermal control coating mainly solves the satellite with small change of whole satellite heat consumption and external heat flow, the thermal control coating needs to be baked after spraying, which needs a long development cycle, resulting in high development cost, which is not conducive to batch production. In order to meet the demand of satellite constellation commercialization batch production and high heat flux density, it is urgent to shorten the satellite development cycle and improve the whole satellite heat dissipation capacity. SUMMARY

[0009] In view of the defects in the prior art, the purpose of the present application is to provide a satellite integrated thermal control film for heat conduction and heat dissipation.

[0010] According to the satellite integrated thermal control film for heat conduction and heat dissipation provided by the present application, the satellite integrated thermal control film for heat conduction and heat dissipation comprises: a protective layer 1, a nano thermal control film 2 and a graphite film 3.

[0011] The nano thermal control film 2 is located on the outer surface, and the graphite film 3 is located on the inner surface. The nano thermal control film 2 and the graphite film 3 are pasted as a whole by means of hot melt adhesive.

[0012] The satellite integrated thermal control film for heat conduction and heat dissipation comprises, from inside to outside, the graphite film 3, the nano thermal control film 2 and the protective layer 1.

[0013] Preferably, the core layer of the nano thermal control film 2 is a three-dimensional micro-nano structure comprising micro-nano particles 6.

[0014] Preferably, the three-dimensional micro-nano structure comprises, in sequence, a conductive layer 4, an ultraviolet reflection enhancement layer 5, an infrared regulation layer 7, a reflection layer 8 and a protective layer 9. The infrared regulation layer 7 has micro-nano particles 6 therein. The protective layer 9 is closer to the graphite film 3 than the conductive layer 4.

[0015] Preferably, the nano thermal control film 2 has a solar absorption ratio of 0.06±0.02 in the solar spectrum band and a hemispherical emissivity of 0.90±0.02 in the infrared spectrum band.

[0016] Preferably, the graphite film 3 is packaged by means of hot melt adhesive, and the thermal conductivity coefficient is more than 1000W / mK.

[0017] Preferably, the integrated thermal control film is pasted to the side plate of the satellite by means of silicone rubber. Further, the nano thermal control film 2 is located on the outer side and does not directly contact the side plate of the satellite, and the graphite film 3 is located on the inner side and is pasted to the side plate of the satellite by means of silicone rubber.

[0018] Preferably, the material of the integrated thermal control film is polyimide and graphite film material, and the three-dimensional micro-nano structure is made by means of nano particle modification processing and integrated melting method.

[0019] Preferably, the nano-thermal control film 2 is on the outer side, and the graphite film 3 is on the inner side.

[0020] Preferably, the nano-thermal control film 2 reflects ≥ 94% of sunlight by using the three-dimensional micro-nano structure.

[0021] According to the satellite provided by the application, the satellite is provided with the integrated thermal control film for heat conduction and heat dissipation.

[0022] Compared with the prior art, the application has the following beneficial effects:

[0023] 1. The nano-thermal control film has strong heat dissipation capacity, and the same heat dissipation area can improve the heat dissipation capacity of the whole satellite, thereby improving the thermal environment adaptability of the whole satellite, and being suitable for different orbits, attitudes and payloads.

[0024] 2. The graphite film enhances the heat transfer capacity, improves the temperature field uniformity of the whole satellite, and further improves the heat dissipation capacity of the whole satellite.

[0025] 3. The integrated thermal control film has a short production and implementation cycle, and the product cost is greatly reduced, and is suitable for commercial batch development of constellation satellites. BRIEF DESCRIPTION OF DRAWINGS

[0026] Other features, objects and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments, made with reference to the accompanying drawings:

[0027] Figure 1 FIG. 1 is a schematic diagram of the integrated thermal control film for heat conduction and heat dissipation of the satellite according to the application.

[0028] Figure 2 FIG. 2 is a schematic diagram of heat dissipation and heat conduction of the integrated thermal control film for heat conduction and heat dissipation of the satellite according to the application.

[0029] Figure 3 FIG. 3 is a schematic diagram of the three-dimensional micro-nano structure according to the application.

[0030] FIG. 4 shows:

[0031] DETAILED DESCRIPTION

[0032] The application will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the application, but do not limit the application in any form. It should be pointed out that those skilled in the art can make several changes and improvements without departing from the concept of the application. These all belong to the protection scope of the application.

[0033] The application provides a satellite heat-conducting and heat-dissipating integrated thermal control film, which comprises a protective layer 1, a nano thermal control film 2 and a graphite film 3.

[0034] The nano thermal control film 2 is located on the outer surface of the integrated thermal control film, the graphite film 3 is located on the inner surface of the integrated thermal control film, the nano thermal control film 2 and the graphite film 3 are adhered by hot melt glue, and the integrated thermal control film is adhered to the satellite side plate by silicone rubber.

[0035] As shown in the figure, the outer surface of the nano thermal control film 2 has the protective layer 1, which is mainly used for protecting the internal structure of the film and improving the anti-ultraviolet radiation capacity, has the anti-static function and has good wave-penetrating performance. Figure 1 The nano thermal control film 2 realizes the regulation and control of the solar spectrum and the infrared spectrum through a three-dimensional micro-nano structure, the solar absorption ratio of the nano thermal control film 2 in the solar spectrum is 0.06±0.02, the hemispherical emissivity in the infrared spectrum is 0.90±0.02, the high reflectivity of the solar spectrum and the high emissivity of the infrared spectrum are achieved, and the heat-dissipating capacity of the whole satellite is directly enhanced.

[0036] The graphite film 3 is a high-thermal-conductivity graphite film, the graphite film 3 is hot-pressed and packaged by hot melt glue, the thermal conductivity coefficient of the graphite film 3 is more than 1000 W / mK, the heat transfer amount is enhanced, the surface temperature of the satellite side plate is balanced, the temperature field uniformity of the whole satellite is improved, and the heat-dissipating capacity of the whole satellite is further improved.

[0037] In the prior art, the traditional thermal control coating is directly sprayed on the outer surface of the satellite, the transverse thermal conductivity coefficient is very small, the surface absorption ratio is about 0.2, the implementation cycle is long, and the cost is high.

[0038] More specifically, the satellite heat-conducting and heat-dissipating integrated thermal control film mainly comprises the nano thermal control film 2 and the graphite film 3, the nano thermal control film 2 is on the outer surface, the graphite film 3 is on the inner surface, and the nano thermal control film 2 has good heat-dissipating capacity and the graphite film 3 has high thermal conductivity.

[0039] As shown in the figure, the nano thermal control film 2 has the protective layer on the surface, which can protect the internal structure of the film, improve the anti-ultraviolet radiation capacity, has the anti-static function, has good wave-penetrating performance and improves the product reliability. Figure 3 As shown in the figure, the nano thermal control film 2 has the protective layer on the surface, which can protect the internal structure of the film, improve the anti-ultraviolet radiation capacity, has the anti-static function, has good wave-penetrating performance and improves the product reliability.

[0040] Further, the three-dimensional micro-nano structure is located in the nano thermal control film 2, and is a core layer of the nano thermal control film 2. The three-dimensional micro-nano structure comprises micro-nano particles 6, and the micro-nano particles 6 are used for three-dimensional micro-nano structure configuration and reducing absorption of solar spectrum energy, and a solar absorption ratio is not greater than 0.06. The three-dimensional micro-nano structure is sequentially provided with the conductive layer 4, the ultraviolet reflection enhancement layer 5, the infrared regulation layer 7, the reflection layer 8 and the protective layer 9. The protective layer 9 is closer to the graphite film than the conductive layer 4, and the conductive layer 4 is closer to the protective layer 1 than the protective layer 9. Further, the micro-nano particles 6 are mainly located in the infrared regulation layer 7, and the micro-nano particles 6 and the infrared regulation layer 7 form an integral whole in the middle layer of the three-dimensional micro-nano structure, and the integral whole of the micro-nano particles 6 and the infrared regulation layer 7 has a thickness accounting for 80% to 90% of a total thickness of the three-dimensional micro-nano structure. The nano thermal control film 2 can reflect greater than or equal to 94% of sunlight by using the three-dimensional micro-nano structure, so as to play a role of low absorption ratio and high emission ratio. The infrared regulation layer 7 is made of silicone material, and regulates infrared emission ratio of the thermal control film.

[0041] As shown in Figures 1 to 3 The satellite heat-conducting and heat-dissipating integrated thermal control film provided by the application has the working principle that:

[0042] The integrated thermal control film mainly plays a role of heat expansion and heat dissipation. When sunlight in space irradiates on the integrated thermal control film of the satellite, the sunlight first irradiates on the surface of the integrated thermal control film, and then the sunlight passes through the protective layer 1 of the integrated thermal control film to reach the surface of the nano thermal control film 2. At this time, 6% of heat of the sunlight is absorbed, and 94% of heat of the sunlight is reflected back to the space by the reflection layer 8. Next, the absorbed heat of the sunlight and the heat radiated to the graphite film 3 in the cabin are transmitted through the graphite film 3, so as to reduce temperature difference and improve temperature uniformity. Further, the infrared regulation layer 7 can regulate infrared emission ratio, so as to regulate heat radiated to the space by the nano thermal control film 2.

[0043] Considering ground storage and implementation and space environment, i.e. long-term stable operation of the film in orbit, the protective layer 1 is additionally arranged to protect the internal structure of the film, the conductive layer 4 makes the film have an anti-static function, and the ultraviolet reflection enhancement layer 5 makes the film have a function of resisting ultraviolet, proton, electron and other space particles. Therefore, the satellite heat-conducting and heat-dissipating integrated thermal control film provided by the application has the advantages of less absorption of light heat, more radiation of heat and effective improvement of space heat dissipation capacity.

[0044] In summary, the product of the application has a greatly reduced cost and a short production cycle, and can be batched and pasted, so that the implementation speed is fast, the problem of long development and implementation cycle of the traditional thermal control coating is effectively solved, and the product is suitable for batch production of constellation satellites.

[0045] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0046] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the specific embodiments described above, and various changes or modifications can be made by those skilled in the art within the scope of the claims, which do not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other in the case of no conflict.

Claims

1. An integrated thermal control thin film for heat conduction and dissipation in satellites, characterized in that, It comprises: a protective layer (1), a nano thermal control film (2) and a graphite film (3); the nano thermal control film (2) is located on the outer surface, and the graphite film (3) is located on the inner surface; the nano thermal control film (2) and the graphite film (3) are pasted into an integral whole by means of hot melt adhesive; the satellite heat-conducting and heat-dissipating integrated thermal control film comprises, from inside to outside, the graphite film (3), the nano thermal control film (2) and the protective layer (1); the core layer of the nano thermal control film (2) is a three-dimensional micro-nano structure comprising micro-nano particles (6); the three-dimensional micro-nano structure comprises, arranged in sequence, a conductive layer (4), an ultraviolet reflection-increasing layer (5), an infrared regulation layer (7), a reflective layer (8) and a protective layer (9); the infrared regulation layer (7) has micro-nano particles (6) therein; the protective layer (9) is closer to the graphite film (3) than the conductive layer (4); and the micro-nano particles (6) are mainly distributed in the infrared regulation layer (7).

2. The integrated thermal control film for heat conduction and dissipation for a satellite according to claim 1, characterized by The nano thermal control film (2) has a solar absorption ratio of 0.06±0.02 in the solar spectrum and a hemispherical emissivity of 0.90±0.02 in the infrared spectrum.

3. The integrated thermal control film for heat conduction and dissipation for satellites according to claim 1, characterized by, The graphite film (3) is packaged by means of hot melt adhesive, and the thermal conductivity coefficient thereof is more than 1000 W / mK.

4. The integrated thermal control film for heat conduction and dissipation for satellites according to claim 1, characterized by, The integrated thermal control film is pasted to the side plate of the satellite by means of silicone rubber; further, the nano thermal control film (2) is located on the outer side and does not directly contact the side plate of the satellite, and the graphite film (3) is located on the inner side and is pasted to the side plate of the satellite by means of silicone rubber.

5. The integrated thermal control film for heat conduction and dissipation for satellites according to claim 1, characterized in that, The nano thermal control film (2) is located on the outer side, and the graphite film (3) is located on the inner side.

6. The integrated thermal control film for heat conduction and dissipation for satellites according to claim 1, characterized by The nano thermal control film (2) reflects ≥94% of sunlight by means of the three-dimensional micro-nano structure.

7. A satellite, characterized by The satellite heat-conducting and heat-dissipating integrated thermal control film comprises the satellite heat-conducting and heat-dissipating integrated thermal control film according to any one of claims 1 to 6.

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