Satellite module cooling system adopting liquid metal and artificial satellite

Abstract

The invention relates to the technical field of satellite heat dissipation, and provides a satellite module heat dissipation system adopting liquid metal and an artificial satellite.The satellite module heat dissipation system adopting the liquid metal comprises a pipeline assembly, an electromagnetic pump, a thermoelectric module, an energy storage module and a radiator, the pipeline assembly is laid on the surface of a satellite module, and the liquid metal flows in the pipeline assembly; the electromagnetic pump is connected with the pipeline assembly to drive the liquid metal to flow; the thermoelectric module is connected with the outflow end of the pipeline assembly and used for generating electricity. The energy storage module is connected with the thermoelectric module, is used for storing electric energy and is electrically connected with the satellite module; the radiator is connected with the outflow end of the thermoelectric module and connected to the pipeline assembly through the electromagnetic pump. The heat dissipation requirement of high-power satellite equipment can be met, the satellite module can be installed in a severe environment, and electric energy stored by the energy storage module is supplied to the satellite equipment for use under extreme conditions.

Description

Technical Field

[0001] The present invention relates to the field of satellite heat dissipation technology, and in particular to a satellite module heat dissipation system and an artificial satellite using liquid metal. Background Art

[0002] With the rapid development of satellite technology, the heat flux density is increasing, and heat dissipation has become a pressing issue. To meet the actual heat dissipation requirements, new technologies such as heat dissipation coatings, high and low temperature zoned heat pipe networks, north-south coupled heat pipes, and deployable radiators have emerged. These developments have significantly improved the heat dissipation capabilities of communication satellites, providing strong support for the development of high-power, high-capacity communication satellite technology. However, the heat dissipation efficiency of existing satellites is still limited, and the heat dissipation of satellites results in energy waste. Summary of the Invention

[0003] The present invention aims to solve at least one of the technical problems existing in the related art. To this end, the present invention proposes a satellite module heat dissipation system using liquid metal, which aims to improve the heat dissipation efficiency of the satellite and recycle the heat emitted by the satellite.

[0004] The present invention also provides an artificial satellite.

[0005] A satellite module heat dissipation system using liquid metal according to an embodiment of the first aspect of the present invention includes: a pipeline assembly, the pipeline assembly being laid flat on the surface of the satellite module, and liquid metal flowing in the pipeline assembly; an electromagnetic pump connected to the pipeline assembly to drive the liquid metal to flow; a thermoelectric module, the thermoelectric module being connected to the outflow end of the pipeline assembly and being used for generating electricity; An energy storage module, connected to the thermoelectric module and configured to store electrical energy, and electrically connected to the satellite module; A radiator is connected to the outflow end of the thermoelectric module, and the radiator is connected to the pipeline assembly through the electromagnetic pump.

[0006] According to an embodiment of the present invention, a satellite module cooling system using liquid metal exchanges heat through a piping assembly in contact with the satellite module. When the satellite module's operating temperature is too high, an electromagnetic pump drives the liquid metal to flow, leveraging the high thermal conductivity of the liquid metal within the piping assembly to quickly remove heat, thereby improving heat dissipation efficiency. Simultaneously, the heated liquid metal passes through a thermoelectric module, effectively converting heat into electricity that is stored in an energy storage module. Any heat that cannot be converted is dissipated by a radiator. This system not only meets the cooling needs of high-power satellite equipment but also enables the installation of satellite modules in relatively harsh environments, allowing the stored electricity in the energy storage module to be used by the satellite equipment under extreme conditions.

[0007] According to one embodiment of the present invention, the pipeline assembly extends in a serpentine structure along the surface of the satellite module.

[0008] According to one embodiment of the present invention, the pipeline assembly includes a multi-layer serpentine pipeline.

[0009] According to one embodiment of the present invention, the pipeline assembly further includes an input pipe and an output pipe, wherein the input pipe is connected to the input ends of the multiple layers of the serpentine pipelines, and the output pipe is connected to the output ends of the multiple layers of the serpentine pipelines.

[0010] According to one embodiment of the present invention, the satellite module heat dissipation system using liquid metal includes a temperature control switch, which is used to monitor the operating temperature of the satellite module and start the electromagnetic pump when the operating temperature is higher than a set threshold.

[0011] According to one embodiment of the present invention, the electromagnetic pump is an induction electromagnetic pump.

[0012] According to one embodiment of the present invention, the inner diameter of the pump groove of the electromagnetic pump is consistent with the inner diameter of the pipeline of the pipeline assembly.

[0013] According to one embodiment of the present invention, thermal grease is provided on the side of the pipeline assembly that contacts the satellite module.

[0014] According to one embodiment of the present invention, the pipeline assembly is made of stainless steel.

[0015] According to an embodiment of the second aspect of the present invention, an artificial satellite includes a satellite body and the above-mentioned satellite module heat dissipation system using liquid metal, and the satellite module heat dissipation system using liquid metal is arranged on the satellite body.

[0016] The artificial satellite according to the embodiment of the present invention includes the above-mentioned satellite module heat dissipation system using liquid metal, and therefore has all the technical effects of the above-mentioned satellite module heat dissipation system using liquid metal, which will not be repeated here.

[0017] Additional aspects and advantages of the present invention will be set forth in part in the description which follows and, in part, will be obvious from the description which follows, or may be learned by practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or related technologies, the following briefly introduces the drawings required for use in the embodiments or related technical descriptions. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0019] Figure 1 Schematic diagram of a satellite module heat dissipation system using liquid metal provided in an embodiment of the present invention.

[0020] Figure 2 Schematic diagram of a satellite module and pipeline assembly provided in an embodiment of the present invention.

[0021] Figure 3 Schematic diagram of the structure of the pipeline assembly provided by an embodiment of the present invention.

[0022] Reference numerals: 1. Satellite module; 2. Temperature control switch; 3. Thermoelectric module; 4. Energy storage module; 5. Radiator; 6. Electromagnetic pump; 8. Serpentine pipe; 9. Input pipe; 10. Output pipe; 11. Heat sink fins. DETAILED DESCRIPTION

[0023] The following embodiments of the present invention are described in further detail with reference to the accompanying drawings and examples. The following examples are used to illustrate the present invention but are not intended to limit the scope of the present invention.

[0024] In the description of the embodiments of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be understood as limiting the embodiments of the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and should not be understood as indicating or implying relative importance.

[0025] In the description of the embodiments of the present invention, it should be noted that, unless otherwise specified or limited, the terms "connected" and "connection" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; mechanical connections, electrical connections; and direct connections or indirect connections through an intermediary. Those skilled in the art will understand the specific meanings of the above terms in the embodiments of the present invention based on the specific circumstances.

[0026] In the embodiments of the present invention, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediate medium. Furthermore, a first feature being "above," "above," or "above" a second feature may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. A first feature being "below," "below," or "below" a second feature may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0027] In the description of this specification, the reference terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the embodiment of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and features of different embodiments or examples without contradiction.

[0028] Based on the limited heat dissipation capacity per unit area of ​​existing satellite equipment and the harsh working environment, in order to ensure that these devices can operate within the normal temperature range, a satellite module heat dissipation system using liquid metal is proposed. It is safe, stable, and has a reliable circulation, which can meet the heat dissipation needs of high-power satellites.

[0029] like Figure 1 As shown, the satellite module heat dissipation system using liquid metal according to the embodiment of the first aspect of the present invention includes a pipeline assembly, an electromagnetic pump 6, a thermoelectric module 3, an energy storage module 4 and a radiator 5. The pipeline assembly is laid flat on the surface of the satellite module 1, and liquid metal flows in the pipeline assembly; the electromagnetic pump 6 is connected to the pipeline assembly to drive the flow of liquid metal; the thermoelectric module 3 is connected to the outflow end of the pipeline assembly, and the thermoelectric module 3 is used to generate electricity; the energy storage module 4 is connected to the thermoelectric module 3 for storing electrical energy, and the energy storage module 4 is electrically connected to the satellite module 1; the radiator 5 is connected to the outflow end of the thermoelectric module 3, and the radiator 5 is connected to the pipeline assembly through the electromagnetic pump 6.

[0030] According to the satellite module heat dissipation system using liquid metal in an embodiment of the present invention, heat exchange is carried out by contacting the satellite module 1 through the pipeline assembly. When the operating temperature of the satellite module 1 is too high, the electromagnetic pump 6 drives the liquid metal to flow, and the high thermal conductivity of the liquid metal in the pipeline assembly is used to quickly remove heat, thereby improving the heat dissipation efficiency. At the same time, the heated liquid metal effectively converts heat into electricity through the thermoelectric module 3 and stores it in the energy storage module 4. The heat that cannot be converted is dissipated by the radiator 5. In this way, it can not only meet the heat dissipation requirements of high-power satellite equipment, but also enable the satellite module 1 to be installed in a relatively harsh environment. The electricity stored in the energy storage module 4 is supplied to the satellite equipment under extreme conditions. In order to solve the oxidation and corrosive problems of liquid metal, it is necessary to first evacuate the pipeline assembly during the system filling process, and then use nitrogen as a protective gas to store the liquid metal in the system for sealed preservation.

[0031] As can be understood, electromagnetic pump 6 is activated to drive the liquid metal in the pipeline assembly to flow. The liquid metal enters the pipes laid flat on the surface of satellite module 1 and then passes through thermoelectric module 3, where it begins to generate electricity due to the thermoelectric effect. Thermoelectric module 3 is typically composed of N-type and P-type semiconductor materials with different electrical and thermal conductivity properties. At the high-temperature end (hot end), electrons are activated by the high temperature and diffuse toward the low-temperature area (cold end), forming an electric current. The generated electrical energy is stored in energy storage module 4. In this way, most of the heat dissipated by satellite module 1 is converted into electricity and stored in energy storage module 4, reducing energy waste. In addition, a small amount of heat is dissipated through connecting pipes to radiator 5. This reciprocating cycle further reduces the temperature of the liquid metal through air cooling in radiator 5, forming an internal feedback regulation loop system and improving the reliability of the device.

[0032] like Figure 2 As shown, according to one embodiment of the present invention, the pipeline assembly extends in a serpentine structure along the surface of the satellite module 1, which can effectively increase the heat exchange area and improve the heat exchange efficiency, so that the heat emitted by the satellite module 1 can heat the liquid metal in the pipeline assembly faster.

[0033] like Figure 3 As shown, according to one embodiment of the present invention, the pipeline assembly includes a multi-layer serpentine pipeline 8. It can be understood that the multi-layer serpentine pipeline 8 is stacked, wherein the outermost layer is attached to the surface of the satellite module 1 for heat exchange. The multi-layer serpentine pipeline 8 is close to each other to facilitate heat transfer, and the multi-layer serpentine pipeline 8 can also achieve rapid heat removal. Optionally, a plurality of heat dissipation fins 11 are provided on the outside of the pipeline assembly, and the plurality of heat dissipation fins 11 are arranged at intervals. The multi-layer serpentine pipeline 8 reciprocates through the plurality of heat dissipation fins 11, and can contact the surface of the satellite module 1 through the heat dissipation fins 11, thereby improving the heat exchange efficiency, thereby quickly transferring heat to the liquid metal in the pipeline assembly.

[0034] According to one embodiment of the present invention, the piping assembly further includes an input pipe 9 and an output pipe 10. The input pipe 9 connects to the input end of the multi-layer serpentine pipe 8, and the output pipe 10 connects to the output end of the multi-layer serpentine pipe 8. It will be appreciated that the input pipe 9 is used to aggregate the input ends of the multi-layer serpentine pipe 8 for connection to the electromagnetic pump 6, thereby eliminating the need to provide multiple electromagnetic pumps 6 for each multi-layer serpentine pipe 8 and saving installation space. Simultaneously, the output pipe 10 is used to aggregate the output ends of the multi-layer serpentine pipe 8 so that the liquid metal in the multi-layer serpentine pipe 8 can be collectively transported to the thermoelectric module 3, reducing structural complexity.

[0035] In one embodiment, if Figure 3 As shown, the piping assembly is a staggered fin-tube heat exchanger with specific dimensions: 225 tubes, 8mm transverse tube spacing, 7mm longitudinal tube spacing, 350mm length, 40mm width, 120mm height, and a mass of 1kg. During the piping assembly design, closer fin spacing and increased fin thickness enhance direct heat transfer, so a closer fin spacing and thicker fins were selected.

[0036] According to one embodiment of the present invention, a satellite module heat dissipation system using liquid metal includes a temperature control switch 2, which monitors the operating temperature of the satellite module 1 and activates an electromagnetic pump 6 when the operating temperature exceeds a set threshold. Using this temperature control switch 2, the flow rate of liquid metal in the system circulation can be adjusted according to the satellite's actual operating state, taking into account the varying amounts of heat dissipated by the satellite under different operating conditions, resulting in a cost-effective and efficient solution.

[0037] According to one embodiment of the present invention, the electromagnetic pump 6 is an induction electromagnetic pump. The satellite module 1 requires a relatively high flow rate for heat dissipation, so an induction electromagnetic pump is selected. Numerical simulation results show that increasing the electromagnetic force by selecting a strong ferromagnetic material, increasing the number of primary cores, thinning the center core, reducing the pump groove gap, and increasing the power supply current and frequency can increase the flow rate of the liquid metal and thus the heat exchange capacity.

[0038] According to one embodiment of the present invention, the inner diameter of the pump groove of the electromagnetic pump 6 is consistent with the inner diameter of the pipe of the pipeline assembly, which is simple to process, has low resistance, and is easy to install.

[0039] According to one embodiment of the present invention, thermal grease is provided on the side of the pipe assembly that contacts the satellite module 1 , which is beneficial to enhancing the heat transfer performance.

[0040] According to one embodiment of the present invention, the pipeline assembly is made of stainless steel. For example, stainless steel 316L, which has good corrosion resistance and good thermal conductivity, is selected to facilitate the heat dissipation of the liquid metal during circulation.

[0041] According to an embodiment of the second aspect of the present invention, an artificial satellite includes a satellite body and the above-mentioned satellite module heat dissipation system using liquid metal, and the satellite module heat dissipation system using liquid metal is arranged on the satellite body.

[0042] The artificial satellite according to the embodiment of the present invention includes the above-mentioned satellite module heat dissipation system using liquid metal, and therefore has all the technical effects of the above-mentioned satellite module heat dissipation system using liquid metal, which will not be repeated here.

[0043] Finally, it should be noted that the above embodiments are intended to illustrate the present invention only and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the embodiments, it should be understood by those skilled in the art that various combinations, modifications, or equivalent substitutions of the technical solutions of the present invention do not depart from the spirit and scope of the technical solutions of the present invention and are intended to be encompassed by the claims of the present invention.

Claims

1. A satellite module cooling system using liquid metal, characterized in that: include: A pipeline assembly, wherein the pipeline assembly is laid flat on the surface of the satellite module, and liquid metal flows in the pipeline assembly; An electromagnetic pump, the electromagnetic pump is connected to the pipeline assembly to drive the liquid metal to flow; A thermoelectric module, the thermoelectric module is connected to the outflow end of the pipeline assembly, and the thermoelectric module is used to generate electricity; An energy storage module, the energy storage module is connected to the thermoelectric module and is used to store electric energy, and the energy storage module is electrically connected to the satellite module; A radiator is connected to the outflow end of the thermoelectric module, and the radiator is connected to the pipeline assembly through the electromagnetic pump.

2. The satellite module cooling system using liquid metal according to claim 1, characterized in that: The pipeline assembly is bent and extended in a serpentine structure along the surface of the satellite module.

3. The satellite module cooling system using liquid metal according to claim 2, characterized in that: The pipeline assembly includes a multi-layer serpentine pipeline.

4. The satellite module cooling system using liquid metal according to claim 3 is characterized in that: The pipeline assembly also includes an input pipe and an output pipe, wherein the input pipe is connected to the input ends of the multiple layers of the serpentine pipelines, and the output pipe is connected to the output ends of the multiple layers of the serpentine pipelines.

5. The satellite module cooling system using liquid metal according to claim 1, characterized in that: The satellite module heat dissipation system using liquid metal includes a temperature control switch, which is used to monitor the operating temperature of the satellite module. When the operating temperature is higher than a set threshold, the electromagnetic pump is started.

6. The satellite module cooling system using liquid metal according to claim 1, characterized in that: The electromagnetic pump is an induction electromagnetic pump.

7. The satellite module cooling system using liquid metal according to claim 1, characterized in that: The inner diameter of the pump groove of the electromagnetic pump is consistent with the inner diameter of the pipeline of the pipeline assembly.

8. The satellite module cooling system using liquid metal according to claim 1, characterized in that: The side of the pipeline assembly that is in contact with the satellite module is provided with thermal conductive silicone grease.

9. The satellite module cooling system using liquid metal according to any one of claims 1 to 8, characterized in that: The pipeline assembly is made of stainless steel.

10. An artificial satellite, characterized in that: It comprises a satellite body and a satellite module cooling system using liquid metal as claimed in any one of claims 1 to 9, wherein the satellite module cooling system using liquid metal is arranged on the satellite body.

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