Dual-cycle satellite thermal insulation and heat dissipation system, satellite and satellite thermal insulation and heat dissipation method

Abstract

This application relates to the field of satellite equipment, providing a dual-circulation satellite thermal insulation and heat dissipation system, a satellite, and a satellite thermal insulation and heat dissipation method. The dual-circulation satellite thermal insulation and heat dissipation system includes: a solar panel; the solar panel includes a first outer shell and an external circulation pipeline assembly disposed inside the first outer shell, the external circulation pipeline assembly including an inlet pipeline and an outlet pipeline, and multiple branch pipeline assemblies connecting the inlet and outlet pipelines; an external circulation storage tank, connected to the solar panel and satellite equipment to form an external circulation pipeline to increase the temperature of the satellite equipment; a cold plate; an internal circulation storage tank, connected to the cold plate and satellite equipment to form an internal circulation pipeline to reduce the temperature of the satellite equipment; and an energy storage module, electrically connected to the solar panel, for storing and providing the power required by the dual-circulation satellite thermal insulation and heat dissipation system. The dual-circulation satellite thermal insulation and heat dissipation system provided by this application can solve the problem of poor satellite thermal management in the prior art and improve the operational reliability of satellite equipment.

Description

Technical Field

[0001] This application relates to the field of satellite equipment, and more particularly to a dual-cycle satellite heat preservation and heat dissipation system, a satellite, and a satellite heat preservation and heat dissipation method. Background Technology

[0002] The thermal control system is a critical subsystem of the satellite, and its core function is to ensure that the satellite equipment operates in a suitable temperature environment during its on-orbit operation through proper design. Under the special conditions of deep space, the main heat transfer methods between satellite equipment are thermal radiation and thermal conduction. The heat generated by the equipment must ultimately be released into the deep space through the heat dissipation coating on the satellite's surface in the form of radiative heat exchange, completing the heat dissipation cycle.

[0003] With the rapid iteration of aerospace technology, the overall power density of spacecraft continues to increase, and satellite equipment is characterized by high integration and tight arrangement. This directly leads to a gradual increase in the heat load on the surface of the satellite, placing higher demands on the performance of the heat dissipation system. At the same time, to ensure the long-term stable and reliable operation of individual units, their operating temperature must be strictly maintained within a specific range. Therefore, targeted insulation measures are required: for low-power units, temperature control can be achieved through simple measures such as "spraying a high-emissivity coating on the surface" and "thermally conductive mounting with the mounting plate"; for high-heat-consumption units, the conventional solution is to first use a heat spreader to diffuse the heat, and then use high-efficiency heat transfer elements to conduct the heat away to meet the heat dissipation requirements.

[0004] Different insulation and heat dissipation methods have provided basic support for the technological development of high-power, high-capacity communication satellites. However, the existing satellite thermal management system still has obvious limitations, and there are problems such as energy waste and poor satellite thermal management effect during the heat dissipation process. Summary of the Invention

[0005] This application provides a dual-cycle satellite thermal insulation and heat dissipation system to solve the problem of poor satellite thermal management in the prior art and improve the operational reliability of satellite equipment.

[0006] This application also provides a satellite.

[0007] This application also provides a satellite heat preservation and heat dissipation method.

[0008] A dual-cycle satellite thermal insulation and heat dissipation system according to a first aspect of this application is used to maintain the temperature of satellite equipment within a preset range. The dual-cycle satellite thermal insulation and heat dissipation system includes:

[0009] A solar panel; the solar panel includes a first outer shell and an external circulation pipeline assembly disposed inside the first outer shell, the external circulation pipeline assembly including an inlet pipeline and an outlet pipeline, and multiple branch pipeline assemblies connecting the inlet pipeline and the outlet pipeline;

[0010] An external circulation storage tank is connected to the solar panel and the satellite equipment to form an external circulation pipeline to increase the temperature of the satellite equipment;

[0011] Cold plate;

[0012] An internal circulation storage tank is connected to the cold plate and the satellite equipment to form an internal circulation pipeline to reduce the temperature of the satellite equipment;

[0013] An energy storage module, electrically connected to the solar panel, is used to store and provide the power required by the dual-cycle satellite heat preservation and cooling system.

[0014] According to one embodiment of this application, the branch assembly includes a first branch, a second branch, and a third branch extending from the inlet pipe to the outlet pipe, and a connecting branch disposed between the first branch and the second branch, and between the second branch and the third branch.

[0015] According to one embodiment of this application, the shunt branch assembly is provided with a turbulence component.

[0016] According to one embodiment of this application, the external circulation pipeline further includes an external circulation valve, which is disposed between the solar panel and the external circulation storage tank to control the on / off state of the external circulation pipeline; and / or

[0017] The internal circulation pipeline also includes an internal circulation valve, which is located between the cold plate and the internal circulation storage tank to control the opening and closing of the internal circulation pipeline.

[0018] According to one embodiment of this application, the external circulation pipeline further includes an external circulation electromagnetic pump, which is disposed on the pipeline at the outlet of the external circulation storage tank to drive the flow of the medium in the external circulation pipeline; and / or

[0019] The internal circulation pipeline also includes an internal circulation electromagnetic pump, which is installed on the pipeline at the outlet of the internal circulation storage tank to drive the flow of the medium in the internal circulation pipeline.

[0020] According to one embodiment of this application, the solar panel further includes:

[0021] The battery module, housed within the first housing, generates electricity based on sunlight.

[0022] A thermoelectric module includes a hot-end guide plate, a cold-end guide plate, and a thermoelectric generator. The hot-end guide plate is located near the sun-facing side of the solar panel, and the cold-end guide plate is located near the shaded side of the solar panel. The two ends of the thermoelectric generator are connected to the hot-end guide plate and the cold-end guide plate, respectively, to generate electricity based on the temperature difference.

[0023] According to one embodiment of this application, the cold plate includes:

[0024] Second outer shell;

[0025] An internal circulation pipeline assembly is disposed within the second housing;

[0026] An electric heating component, disposed in the second housing, is used to raise the temperature of the medium in the internal circulation pipeline assembly to above the melting point.

[0027] According to a second aspect of this application, a satellite includes the aforementioned dual-circulation satellite thermal insulation and heat dissipation system.

[0028] A satellite thermal insulation and heat dissipation method according to a third aspect of this application, the satellite thermal insulation and heat dissipation method using the aforementioned dual-cycle satellite thermal insulation and heat dissipation system, includes:

[0029] Obtain the temperature of the satellite equipment;

[0030] Since the temperature of the satellite equipment is lower than the first temperature, the medium in the external circulation pipeline is heated by the solar panel and then flows through the satellite equipment to increase the temperature of the satellite equipment.

[0031] Since the temperature of the satellite equipment is higher than the second temperature, the medium in the internal circulation pipeline flows through the satellite equipment after passing through the cold plate, in order to reduce the temperature of the satellite equipment.

[0032] According to one embodiment of this application, the medium in the internal circulation pipeline is heated to above its melting point at the cold plate;

[0033] Furthermore, the melting point of the medium in the internal circulation pipeline is lower than the first temperature.

[0034] The above-described one or more technical solutions in the embodiments of this application have at least one of the following technical effects:

[0035] In the dual-circulation satellite thermal insulation and heat dissipation system of this application, an external circulation pipeline consisting of an external circulation storage tank, solar panels, and satellite equipment is used to heat the satellite equipment. An internal circulation pipeline consisting of an internal circulation storage tank, a cold plate, and satellite equipment is used to cool the satellite equipment. By controlling the satellite equipment temperature through these dual circulation pipelines, the temperature is kept within a reasonable range, improving the operational reliability and service life of the satellite equipment. Furthermore, multiple branch circuit components are installed within the solar panels to improve their heat absorption efficiency, ensuring effective heating of the medium within the external circulation pipeline components and maintaining the satellite equipment temperature.

[0036] Additional aspects and advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0037] To more clearly illustrate the technical solutions in the embodiments or related technologies of this application, the accompanying drawings used in the description of the embodiments or related technologies will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0038] Figure 1 This is a schematic diagram of the dual-cycle satellite heat preservation and heat dissipation system provided in this application.

[0039] Figure 2 This is a schematic diagram of the structure of the solar panel provided in this application. Figure 1 (Top view, sectional view).

[0040] Figure 3 This is a schematic diagram of the structure of the solar panel provided in this application. Figure 2 (Front view).

[0041] Figure 4 This is a schematic diagram of the thermoelectric module provided in this application.

[0042] Figure 5 This is a schematic diagram of the structure of the cold plate provided in this application. Figure 1 (Top view, sectional view).

[0043] Figure 6 This is a schematic diagram of the structure of the cold plate provided in this application. Figure 2 (Front view, sectional view).

[0044] Figure 7 This is a flowchart illustrating the satellite heat preservation and heat dissipation method provided in this application.

[0045] Figure label:

[0046] 1. Solar panel; 11. First outer casing; 12. External circulation pipeline assembly; 121. Inlet pipeline; 122. Outlet pipeline; 123. Branch pipeline assembly; 1231. First branch pipeline; 1232. Second branch pipeline; 1233. Third branch pipeline; 1234. Connecting branch; 124. Turbulence assembly; 14. Thermoelectric module; 141. Hot end guide vane; 142. Cold end guide vane; 143. Thermoelectric generator; 144. Heat dissipation fins; 2. External circulation storage tank; 3. Cold plate; 31. Second outer casing; 32. Internal circulation pipeline assembly; 33. Electric heating assembly; 4. Internal circulation storage tank; 5. Energy storage module; 6. Satellite equipment; 71. External circulation valve; 72. External circulation electromagnetic pump; 81. Internal circulation valve; 82. Internal circulation electromagnetic pump. Detailed Implementation

[0047] The embodiments of this application will be described in further detail below with reference to the accompanying drawings and examples. The following examples are used to illustrate this application, but should not be used to limit the scope of this application.

[0048] In the description of the embodiments of this application, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of this application. In addition, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0049] In the description of the embodiments of this application, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application based on the specific circumstances.

[0050] In the embodiments of this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0051] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the embodiments of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0052] A dual-cycle satellite thermal insulation and heat dissipation system according to an embodiment of the first aspect of this application, such as Figure 1 As shown, to maintain the temperature of satellite equipment 6 within a preset range, the dual-circulation satellite heat preservation and heat dissipation system includes: a solar panel 1; the solar panel 1 includes a first outer shell 11 and an external circulation pipeline assembly 12 disposed inside the first outer shell 11, the external circulation pipeline assembly 12 includes an inlet pipeline 121 and an outlet pipeline 122, and multiple branch pipeline assemblies 123 are connected between the inlet pipeline 121 and the outlet pipeline 122; an external circulation storage tank 2, which is connected to the solar panel 1 and the satellite equipment 6 to form an external circulation pipeline to increase the temperature of the satellite equipment 6; a cold plate 3; an internal circulation storage tank 4, which is connected to the cold plate 3 and the satellite equipment 6 to form an internal circulation pipeline to reduce the temperature of the satellite equipment 6; and an energy storage module 5, which is electrically connected to the solar panel 1 to store and provide the power required by the dual-circulation satellite heat preservation and heat dissipation system.

[0053] The dual-circulation satellite thermal insulation and heat dissipation system constructs a two-way regulation mechanism for the temperature of satellite equipment through an independent closed-loop design of external and internal circulation. This solves the problem that existing single heat dissipation or single thermal insulation technologies are difficult to adapt to the complex temperature environment of satellites in orbit and cannot simultaneously meet the heating and cooling needs of equipment. The external circulation pipeline connects the external circulation storage tank 2, the solar panel 1, and the satellite equipment 6, and mainly undertakes the heating function of the satellite equipment 6. The solar panel 1 serves as the core heat absorption carrier of the external circulation. The external circulation pipeline assembly 12 inside its first outer shell 11 includes an inlet pipeline 121, an outlet pipeline 122, and multiple branch pipeline assemblies 123. The design of multiple branch pipelines can significantly expand the contact area between the pipeline and the internal space of the solar panel 1, prolong the residence time of the medium in the solar panel 1, thereby improving the heat absorption efficiency of the solar panel 1 and ensuring that the heat transfer medium in the external circulation pipeline can fully absorb solar heat and achieve effective heating. The heated medium is continuously transported to the satellite equipment 6 through the external circulation pipeline to replenish the heat of the equipment and prevent the temperature of the equipment from falling below the preset range due to the low temperature of the environment or its own low power consumption in the cryogenic space. This ensures the normal start-up and stable operation of the equipment under low temperature conditions and indirectly extends the service life of the equipment.

[0054] The internal circulation pipeline connects the internal circulation storage tank 4, the cold plate 3, and the satellite equipment 6 to achieve the cooling function of the satellite equipment 6: When the satellite equipment 6 generates heat due to continuous operation and the temperature exceeds the preset upper limit, the heat transfer medium in the internal circulation pipeline can quickly absorb the heat on the surface of the equipment. Then, the medium carrying the heat flows through the cold plate 3, and the heat is efficiently released through the heat exchange effect of the cold plate 3 (such as the cold plate 3 can conduct heat through radiation heat exchange with the external space of the satellite or through the internal heat dissipation structure). The cooled medium then flows back to the satellite equipment 6, forming a continuous cooling cycle. This internal circulation design of "equipment heat absorption - cold plate 3 heat dissipation" solves the problem that the heat dissipation efficiency of existing high heat-consuming equipment is limited by the heat expansion plate and it is difficult to quickly control the temperature rise. It is especially suitable for highly integrated and high power density satellite equipment 6, and avoids the equipment from performance degradation, component damage or shutdown due to overheating.

[0055] The electrical connection design between the energy storage module 5 and the solar panel 1 provides stable power support for the entire dual-cycle system, solving the problem that existing thermal management systems are prone to power outages and temperature control failures due to unstable solar energy supply (such as when the satellite enters the Earth's shadow zone or when the intensity of solar radiation in orbit fluctuates). When the satellite is in orbit, the solar panel 1 absorbs heat to power the external circulation while storing the converted electrical energy in the energy storage module 5. When the solar energy supply is insufficient, the energy storage module 5 can directly provide power to the medium drive components (such as electromagnetic pumps) and temperature monitoring components in the external and internal circulation pipelines, ensuring that the heating and cooling cycles are uninterrupted and that the equipment temperature is always within the preset range.

[0056] Meanwhile, the solar panel 1 has the dual functions of "heat absorption carrier" and "power source". This integrated design does not require a separate heat absorption component for the external circulation, nor does it require an additional dedicated power generation device for the system. It can effectively reduce the satellite's payload weight and internal installation space occupation, which meets the design requirements of satellite equipment 6 for high integration and lightweighting. It avoids the problems of increased assembly complexity and low space utilization caused by the dispersed arrangement of multiple components.

[0057] The independent operation of the external and internal circulation systems allows for flexible adjustment based on the real-time temperature requirements of Satellite Equipment 6: when the equipment temperature is below the preset lower limit, precise heating can be achieved by simply activating the external circulation system; when the equipment temperature is above the preset upper limit, rapid cooling can be achieved by simply activating the internal circulation system; in complex scenarios such as sudden temperature changes in cryogenic space or equipment operating condition switching, the temperature can be quickly balanced through the coordinated operation of the dual circulation systems. Compared with existing single temperature control technologies, this significantly improves the flexibility and response speed of temperature control, further enhancing the reliability of Satellite Equipment 6's long-term on-orbit operation.

[0058] It should be noted that in the external circulation pipeline, the solar panel 1 acts as the heating medium, while the cold plate 3 does not participate in the external circulation pipeline; that is, the cold plate 3 is not present in the external circulation pipeline. However, in specific structural arrangements, such as... Figure 1 As shown, the external circulation pipe passes through the cold plate 3. This is only to reduce the overall volume of the dual-circulation satellite heat preservation and heat dissipation system. Part of the external circulation pipe is placed in the cold plate 3 to reduce the extra volume occupied by the external circulation pipe. At this time, the cold plate 3 does not heat or cool the medium in the external circulation pipe, but only serves to accommodate part of the external circulation pipe.

[0059] According to one embodiment of this application, such as Figure 2 As shown, the branch assembly 123 includes a first branch 1231, a second branch 1232, and a third branch 1233 extending from the inlet pipe 121 to the outlet pipe 122, and a connecting branch 1234 disposed between the first branch 1231 and the second branch 1232, and between the second branch 1232 and the third branch 1233. Figure 3 This is a front view of the solar panel to show the location of outlet pipe 122.

[0060] In the branch circuit assembly 123, the first branch circuit 1231, the second branch circuit 1232, and the third branch circuit 1233 all extend from the inlet pipe 121 to the outlet pipe 122. The parallel design of multiple branches can significantly increase the contact area between the external circulation pipe assembly 12 and the internal space of the first outer shell 11 of the solar panel 1, extend the flow path and residence time of the external circulation medium in the solar panel 1, and allow the medium to absorb solar heat for a longer time, effectively improving the heat absorption efficiency of the solar panel 1. This provides a basic support for the efficient transfer of heat from the external circulation pipe to the satellite equipment 6 and for ensuring the temperature stability of the equipment under low-temperature conditions.

[0061] The connecting branch 1234, located between the first branch 1231 and the second branch 1232, and between the second branch 1232 and the third branch 1233, further optimizes the stability of the medium flow and the reliability of the system. On the one hand, the connecting branch 1234 can balance the medium flow in the three branch lines, avoiding situations where the flow in one branch is too large or too small due to differences in pipeline resistance. This ensures that the medium in each branch can absorb solar heat evenly, preventing insufficient local medium heating from affecting the overall heating effect of the external circulation and improving the uniformity of the external circulation medium temperature. On the other hand, the connecting branch 1234 forms a flow redundancy channel. If the flow in one branch decreases due to minor blockage (such as impurity deposition that may occur during on-orbit operation), the medium can flow to the adjacent branch line through the connecting branch 1234. This avoids a significant decrease in the heat absorption capacity of the external circulation pipeline assembly 12 due to a single branch failure, ensuring the continuous and stable operation of the external circulation system and indirectly improving the reliability of the temperature control of the satellite equipment 6.

[0062] Meanwhile, this structural design of "three branch paths + connecting branch paths 1234" can balance heat absorption efficiency and structural compactness within the limited internal space of the solar panel 1, meeting the design requirements of high integration and lightweight of satellite equipment 6, and avoiding the problem of increased volume and weight of solar panel 1 due to complex pipeline structure.

[0063] According to one embodiment of this application, such as Figure 2 As shown, a flow-disrupting component 124 is provided in the branch assembly 123, and the flow-disrupting component 124 can be fixed on the inner wall of the pipeline.

[0064] The branch assembly 123 is equipped with a finned turbulence component 124 to break the laminar flow state of the heat transfer medium inside the pipe and promote turbulent flow, thereby significantly improving the heat exchange efficiency between the medium and the pipe wall. For the external circulation pipe, the branch assembly 123 is the core area for the medium to absorb solar heat. The turbulence component 124, by disturbing the flow of the medium, allows the medium to contact the inner wall of the pipe more fully (the temperature of the pipe wall rises after absorbing solar energy), avoiding the formation of a "temperature gradient" in the center of the pipe (i.e., the medium temperature is high near the pipe wall and low in the center), ensuring that the medium heats up uniformly as a whole, and providing a guarantee for the stable transfer of heat from the external circulation to the satellite equipment 6.

[0065] In some cases, flow-disrupting components 124 can also be installed in the inlet pipe 121 and the outlet pipe 122. In the inlet pipe 121, the flow-disrupting component 124 allows the newly entered low-temperature medium to quickly exchange heat with the pipe wall, shortening the medium preheating time and further improving the heating efficiency of the external circulation. In the outlet pipe 122, the flow-disrupting component 124 allows the medium in each branch to mix thoroughly, avoiding temperature fluctuations in the outlet medium due to temperature differences between different branch media, ensuring stable heat delivery to the satellite equipment 6, and preventing sudden changes in local temperature of the equipment.

[0066] The inclusion of the baffle assembly 124 does not require increasing the volume of the piping or altering the overall piping layout; it only necessitates adding a structure within the piping, meeting the "lightweight and highly integrated" design requirements of Satellite Equipment 6. Compared to methods that improve heat exchange efficiency by increasing the pipe diameter, the baffle assembly 124 achieves enhanced heat exchange performance within a limited piping space. This avoids the problems of increased satellite payload weight and excessive installation space occupation caused by increased pipe volume, further ensuring the compactness and operational reliability of the overall satellite structure.

[0067] According to one embodiment of this application, such as Figure 1 As shown, the external circulation pipeline also includes an external circulation valve 71, which is located between the solar panel 1 and the external circulation storage tank 2 to control the opening and closing of the external circulation pipeline; and / or, the internal circulation pipeline also includes an internal circulation valve 81, which is located between the cold plate 3 and the internal circulation storage tank 4 to control the opening and closing of the internal circulation pipeline.

[0068] An external circulation valve 71 is located between the solar panel 1 and the external circulation storage tank 2. It controls the opening and closing of the external circulation pipeline, allowing for on-demand start and stop of the external circulation heating function. This avoids the problem of the satellite equipment 6 overheating due to continuous operation of the external circulation pipeline, or wasting energy when heating is not needed. When the temperature of the satellite equipment 6 reaches the preset range and further heating is not required, the external circulation valve 71 closes, cutting off the flow of the heat transfer medium in the external circulation pipeline. This prevents the medium continuously heated by the solar panel 1 from being delivered to the equipment, thus preventing the equipment temperature from exceeding the reasonable range. When the equipment temperature is below the preset lower limit and heating is required, the external circulation valve 71 opens, allowing the medium in the external circulation storage tank 2 to flow normally into the solar panel 1 to absorb heat, and then be delivered to the equipment to complete the heating process. This ensures precise and controllable heating, reduces unnecessary energy consumption, and lowers the power supply burden on the energy storage module 5.

[0069] An internal circulation valve 81 is located between the cold plate 3 and the internal circulation storage tank 4. By controlling the opening and closing of the internal circulation pipeline, the internal circulation cooling function can be flexibly adjusted, avoiding the problem that continuous operation of the internal circulation pipeline may lead to excessively low equipment temperature or increased system energy consumption when cooling is not required. When the temperature of the satellite equipment 6 drops to the preset range and no further cooling is needed, the internal circulation valve 81 closes, stopping the flow of the internal circulation medium and preventing the medium continuously cooled by the cold plate 3 from absorbing heat from the equipment, thus preventing the equipment temperature from falling below the working requirements. When the equipment temperature is higher than the preset upper limit and cooling is required, the internal circulation valve 81 opens, allowing the medium in the internal circulation storage tank 4 to flow normally through the equipment to absorb heat and then enter the cold plate 3 to dissipate heat, forming a stable cooling cycle. This ensures that the cooling process starts as needed, improving the energy utilization efficiency of the internal circulation system.

[0070] From the perspective of the dual-circulation system as a whole, the independent control characteristics of the external circulation valve 71 and the internal circulation valve 81 allow for flexible combination of external circulation heating and internal circulation cooling based on the real-time temperature requirements of the equipment. When heating is needed, the external circulation valve 71 is opened and the internal circulation valve 81 is closed; when cooling is needed, the internal circulation valve 81 is opened and the external circulation valve 71 is closed. When temperature fluctuations are small, both valves can be closed simultaneously, reducing system energy consumption. Compared to existing single-circulation or uncontrollable circulation systems, this control method significantly improves the flexibility of temperature control and energy utilization efficiency, while adapting to the variable temperature environment and equipment operating conditions during satellite in-orbit operation, ensuring long-term stable operation of the equipment. Furthermore, the valves are small in size and easy to install, requiring no significant changes to the existing pipeline layout, meeting the highly integrated and lightweight design requirements of satellite equipment 6, and avoiding excessive space occupation or weight increase caused by adding control components.

[0071] In some cases, to improve the accuracy of valve control and the system's self-adaptability, the functions of the external circulation valve 71 and the internal circulation valve 81 can be expanded. An opening adjustment function is added to both the external circulation valve 71 and the internal circulation valve 81, replacing the traditional on / off control mode. This allows the valves to dynamically adjust their opening based on the difference between the equipment temperature and the target temperature: when the external circulation requires rapid heating (e.g., when the equipment temperature is far below the preset lower limit), the external circulation valve 71 is opened to its maximum, increasing the medium flow rate and accelerating the transfer of heat from the solar panel 1 to the equipment; when the equipment temperature approaches the preset range, the valve opening is gradually reduced to decrease the medium flow rate and prevent a sudden temperature rise; similarly, the internal circulation valve 81 is opened when the equipment temperature is far above the preset upper limit to accelerate cooling, and its opening is reduced when the temperature approaches the target to prevent a sudden temperature drop. This adjustable opening design allows for a smoother and more precise temperature control process, avoiding frequent fluctuations in equipment temperature and further improving the stability of equipment operation.

[0072] According to one embodiment of this application, such as Figure 1As shown, the external circulation pipeline also includes an external circulation electromagnetic pump 72, which is installed on the pipeline at the outlet of the external circulation storage tank 2 to drive the flow of the medium in the external circulation pipeline; and / or, the internal circulation pipeline also includes an internal circulation electromagnetic pump 82, which is installed on the pipeline at the outlet of the internal circulation storage tank 4 to drive the flow of the medium in the internal circulation pipeline.

[0073] An external circulation electromagnetic pump 72 is installed on the outlet pipeline of the external circulation storage tank 2, providing active and stable power to the heat transfer medium in the external circulation pipeline, ensuring reliable operation of the external circulation heating function. The core process of external circulation is that the medium flows out of the external circulation storage tank 2, absorbs heat through the solar panel 1, and is then transported to the satellite equipment 6 to release heat. The external circulation electromagnetic pump 72 directly drives the medium in the outlet pipeline, which can prevent the medium from stagnating at the outlet of the storage tank and ensure that the medium enters the solar panel 1 at a uniform and controllable flow rate. This ensures that the heat absorbed by the solar panel 1 can be carried by the medium and transferred to the satellite equipment 6 in a timely manner. Especially in the microgravity environment of cryogenic space, natural flow is almost ineffective. The external circulation electromagnetic pump 72 becomes the core power source of the external circulation system, which can prevent the temperature of the satellite equipment 6 from dropping suddenly due to the interruption of heat supply and maintain the equipment temperature stable within the preset range. Meanwhile, the electromagnetic pump is characterized by its small size, light weight, and low power consumption. Compared with traditional mechanical pumps, it can reduce the weight of the satellite payload and the power supply burden of the energy storage module 5, and avoid occupying too much installation space due to the excessive size of the pump body. This meets the design requirements of "lightweight, highly integrated, and low energy consumption" for satellites. Moreover, the electromagnetic pump has no mechanical wear parts, has high operational reliability, and can adapt to the long-term on-orbit operation requirements of satellites, reducing the risk of temperature control failure due to pump body failure.

[0074] An internal circulation electromagnetic pump 82 is installed on the pipeline at the outlet of the internal circulation storage tank 4, providing crucial power support for the internal circulation cooling cycle. The core process of internal circulation is that the medium flows out of the internal circulation storage tank 4, absorbs heat through the satellite equipment 6, flows to the cold plate 3 for heat dissipation, and then flows back to the storage tank. The internal circulation electromagnetic pump 82 drives the medium, which can accelerate the circulation speed of the medium in the pipeline, shorten the cycle from "absorbing heat from the equipment" to "heat dissipation from the cold plate 3", and ensure that the heat energy generated by the equipment is quickly removed, preventing the equipment temperature from continuously rising beyond the preset range. Furthermore, the power output of the internal circulation electromagnetic pump 82 is controllable and can work in conjunction with the internal circulation valve 81 and the temperature sensor. When the temperature of the satellite equipment 6 is slightly higher than the preset upper limit, the speed of the electromagnetic pump is reduced, the medium flow rate is reduced, and excessive cooling is avoided to prevent equipment temperature fluctuations. When the equipment temperature is much higher than the preset upper limit, the speed is increased, the flow rate is increased, and the cooling efficiency is improved, achieving precise control of the cooling process and adapting to the needs of the satellite equipment 6 with high heat consumption and high requirements for cooling accuracy.

[0075] From the perspective of the dual-circulation system as a whole, the external circulation electromagnetic pump 72 and the internal circulation electromagnetic pump 82 are respectively installed on the pipelines at the outlet of their respective storage tanks, making the power systems of the two circulations completely independent. They can be started individually or operated in coordination according to the real-time temperature requirements of satellite equipment 6 (e.g., the external circulation electromagnetic pump 72 is started when only heating is needed, and the internal circulation electromagnetic pump 82 is started when only cooling is needed), avoiding mutual interference between the power systems and significantly improving the system's control flexibility. At the same time, the leak-free characteristics of the electromagnetic pumps ensure that the heat transfer medium in the pipeline does not leak, preventing circulation failure due to medium loss, and further ensuring the reliability of the dual-circulation system during long-term on-orbit operation.

[0076] According to one embodiment of this application, the solar panel 1 further includes: a battery module disposed in the first housing 11, which generates electricity based on sunlight; and a thermoelectric module 14, such as... Figure 4 As shown, the device includes a hot-end guide plate 141, a cold-end guide plate 142, and a thermoelectric generator 143. The hot-end guide plate 141 is close to the sun-facing side of the solar panel 1, and the cold-end guide plate 142 is close to the shaded side of the solar panel 1. The two ends of the thermoelectric generator 143 are connected to the hot-end guide plate 141 and the cold-end guide plate 142 respectively, so as to generate electricity based on the temperature difference.

[0077] Figure 4 In the diagram, label 12 indicates the location of the external circulation piping assembly 12, that is, Figure 4 The two heat dissipation fins 144 above the mid-heat end guide plate 141 can be installed on both sides of the external circulation pipeline assembly 12 to absorb the heat in the external circulation pipeline assembly 12 and supply it to the high-temperature end of the thermoelectric generator 143.

[0078] The coordinated arrangement of the battery module and thermoelectric module 14 in solar panel 1 enables the dual utilization of solar energy, specifically both solar "light energy" and "thermal energy." The battery module, as the core power generation component, directly converts sunlight into electricity, supplementing the power supply to the energy storage module 5 and ensuring the basic power supply needs of the dual-cycle satellite insulation and heat dissipation system. Meanwhile, the thermoelectric module 14 absorbs heat from the sun-facing side through its hot-end guide plate 141 and contacts the low temperature of the shaded side through its cold-end guide plate 142, creating a stable temperature difference between the two ends of the thermoelectric generator 143. This temperature difference energy is then converted into electrical energy. This process requires no additional energy consumption and represents energy recovery from the temperature difference within solar panel 1 itself, significantly improving the overall energy output efficiency of solar panel 1 and providing more power reserves for the system. Especially in cryogenic environments, where the temperature on the shaded side of solar panel 1 is extremely low and the temperature difference between the sun-facing and shaded sides is stable and significant, the thermoelectric module 14 can continuously and stably generate electricity, further enhancing power supply reliability.

[0079] Both the battery module and the thermoelectric module 14 are located inside the first outer shell 11, forming an integrated structure of "solar power generation + thermoelectric power generation". There is no need to set up separate external components for the thermoelectric power generation function, which effectively saves the installation space and payload weight of the satellite and meets the design requirements of "high integration and lightweight" of satellite equipment 6.

[0080] The thermoelectric module 14 provides a "dual power supply" backup for the system, solving the problem of unstable power supply caused by the reliance on sunlight by a single battery module and its susceptibility to on-orbit environmental factors (such as the satellite entering the Earth's shadow zone or fluctuations in light intensity). When there is sufficient sunlight, the battery module and thermoelectric module 14 generate electricity simultaneously, and excess energy is stored in the energy storage module 5. When there is insufficient sunlight, the power generation of the battery module decreases, but there is still a temperature difference between the sun-facing and shaded sides of the solar panel 1 (such as the temperature difference maintained by reflected light from the Earth or residual heat from the equipment). The thermoelectric module 14 can continue to generate electricity to supplement the power of the energy storage module 5, ensuring that the power supply of the dual circulation system (external circulation electromagnetic pump 72, internal circulation electromagnetic pump 82, valves, etc.) is uninterrupted, avoiding the failure of temperature control function due to insufficient power supply, and further ensuring the temperature stability of the satellite equipment 6.

[0081] Furthermore, the hot end guide plate 141 of the thermoelectric module 14 is close to the sun-facing side. While absorbing heat for power generation, it can help balance the temperature of the sun-facing side of the solar panel 1—avoiding excessively high local temperatures caused by continuous absorption of sunlight on the sun-facing side, indirectly protecting the battery module from high-temperature damage and extending the battery module's service life. The cold end guide plate 142 is close to the shaded side, which can reduce the transfer of heat from the shaded side to the sun-facing side and maintain a stable temperature difference between the two sides. This not only ensures the power generation efficiency of the thermoelectric module 14, but also provides a more stable thermal environment for the external circulation pipeline assembly 12 (which needs to absorb heat to rise) inside the solar panel 1, indirectly improving the reliability of external circulation heating.

[0082] According to one embodiment of this application, such as Figure 5 and Figure 6 As shown, the cold plate 3 includes: a second outer shell 31; an internal circulation pipeline assembly 32 disposed in the second outer shell 31; and an electric heating assembly 33 disposed in the second outer shell 31 to raise the temperature of the medium in the internal circulation pipeline assembly 32 to above the melting point.

[0083] After the internal circulation medium absorbs the heat from the satellite equipment 6, it flows into the internal circulation pipeline assembly 32 inside the second outer shell 31. The second outer shell 31 can conduct heat out of the medium in the pipeline through radiative heat exchange with the external deep cold space of the satellite or through heat conduction with other heat dissipation structures inside the satellite, thereby achieving medium cooling.

[0084] The electric heating component 33 is a key design feature of the cold plate 3, adapting it to the cryogenic space environment. It solves the core problems of internal circulation medium solidification, pipeline blockage, and internal circulation failure caused by extreme low temperatures in cryogenic space. Before internal circulation starts or during on-orbit operation, if the medium temperature is detected to be close to its melting point, the electric heating component 33 can actively heat the internal circulation pipeline component 32, maintaining the medium temperature above its melting point. This ensures the medium remains liquid, guaranteeing its flow capacity within the pipeline and preventing the internal circulation electromagnetic pump 82 from running idle and its cooling function from interrupting due to medium solidification. This, in turn, prevents the satellite equipment 6 from experiencing temperature runaway due to insufficient heat dissipation. The electric heating component 33 only needs to be activated when the medium temperature is close to its melting point, without continuous operation. Compared to a design that maintains temperature through continuous heating, this reduces energy consumption and the power supply burden on the energy storage module 5, meeting the satellite's "low-energy consumption" design requirements. Of course, the electric heating component 33 can also operate continuously at low power to maintain the medium in a liquid state.

[0085] The internal circulation pipeline assembly 32 and the electric heating assembly 33 are both located inside the second outer shell 31, forming an integrated cold plate 3 structure that combines heat dissipation and anti-condensation. This saves the satellite's installation space and payload weight, meeting the satellite equipment 6's design requirements of "high integration and lightweight".

[0086] In some exemplary embodiments, the liquid metal flowing in the external circulation pipeline is specifically a gallium indium tin alloy with a boiling point as high as 2200°C. The liquid metal flowing in the internal circulation pipeline is specifically a sodium-potassium alloy with a melting point as low as -15°C. The shaded side of the solar panel 1 can be covered with heat insulation material to reduce heat loss; the heat insulation material can be a high-temperature resistant non-ablation ceramic matrix composite material. The external circulation pipeline assembly 12 is a single-inlet / outlet dispersed confluence type multi-channel. The pipeline assembly inside the cold plate 3 is a serpentine channel. The pipeline assembly material is a corrosion-resistant material such as stainless steel, and the inner wall of the pipeline is coated with a boronizing treatment and a pre-oxidized coating on the material surface. The thermoelectric generator 143 includes multiple N-type and P-type semiconductor thermoelectric materials, which are arranged alternately and connected in series through guide plates, and the thermoelectric materials are mainly silicon-germanium alloys. The electric heating element (electric heating assembly 33) is a sandwich structure composed of polyimide and constantan foil, formed by chemical etching to form heating wires, press-sealed, and assembled onto the surface of the satellite product by silicone rubber bonding. Both the external circulation electromagnetic pump 72 and the internal circulation electromagnetic pump 82 can be DC type, and their pump inlet inner diameter is consistent with the inner diameter of the pipeline assembly. The cross-sectional shape of the internal circulation pipeline assembly 32 and the external circulation pipeline assembly 12 can be circular, square, or triangular.

[0087] According to a second aspect of this application, a satellite includes the aforementioned dual-circulation satellite thermal insulation and heat dissipation system.

[0088] According to a third aspect embodiment of this application, a satellite thermal insulation and heat dissipation method utilizes the aforementioned dual-cycle satellite thermal insulation and heat dissipation system, such as... Figure 7 As shown, the process includes: acquiring the temperature of satellite device 6; based on the fact that the temperature of satellite device 6 is lower than a first temperature, the medium in the external circulation pipeline is heated by the solar panel 1 and then flows through satellite device 6 to increase the temperature of satellite device 6; based on the fact that the temperature of satellite device 6 is higher than a second temperature, the medium in the internal circulation pipeline flows through the cold plate 3 and then through satellite device 6 to decrease the temperature of satellite device 6.

[0089] The satellite's thermal insulation and heat dissipation method is based on "real-time temperature monitoring." By switching between external and internal circulation as needed, it achieves precise temperature control of satellite equipment 6. The steps of obtaining the temperature of satellite equipment 6 provide data for subsequent temperature control actions: when the temperature is lower than the first temperature (the critical value at which the equipment needs to be heated), the external circulation is activated; when it is higher than the second temperature (the critical value at which the equipment needs to be cooled), the internal circulation is activated. This ensures that the temperature control actions are perfectly matched with the actual needs of the equipment, reducing unnecessary power and heat consumption and meeting the satellite's "low energy consumption" design requirements.

[0090] The external circulation is activated when the temperature is below the first temperature. This fully utilizes the heat absorption characteristics of the solar panel 1. The medium in the external circulation pipeline is heated by the solar panel 1 and then flows through the satellite equipment 6. This can accurately transfer the heat energy converted by the solar energy to the equipment, avoiding startup failure or performance degradation of the equipment in the deep cold space due to excessively low temperature.

[0091] The internal circulation is activated based on a temperature higher than the second temperature, specifically addressing the heat dissipation problem of satellite equipment 6 (especially high-heat-consumption, highly integrated equipment). The medium in the internal circulation pipeline is kept in a liquid state by the cold plate 3 before flowing through the satellite equipment 6 to absorb heat, and then flows back to the cold plate 3 (the medium in the internal circulation pipeline can dissipate heat and cool down at both the internal circulation pipeline and the cold plate 3). This allows for rapid absorption of the heat generated by the equipment, and the heat is then conducted to the cryogenic space through the cold plate 3, achieving a rapid decrease in the equipment temperature.

[0092] This method enables "interference-free switching" between the external and internal circulation: when the equipment temperature is between the first and second temperatures (normal operating range), both circulations can be shut down, maintaining only temperature monitoring, further saving energy; when the temperature exceeds any threshold, only the corresponding circulation is activated, avoiding energy waste and temperature fluctuations (such as offsetting heating and cooling) caused by simultaneous operation of both circulations. This flexible control mode allows the system to adapt to complex scenarios such as the extreme low temperatures of cryogenic space and equipment operating condition switching (such as a sudden increase in heat consumption during high-power operation), ensuring that satellite equipment 6 remains within the preset temperature range for extended periods, significantly improving the equipment's operational reliability and service life.

[0093] According to one embodiment of this application, the medium in the internal circulation pipeline is heated to above the melting point at the cold plate 3; and the melting point value of the medium in the internal circulation pipeline is lower than the first temperature.

[0094] The medium in the internal circulation pipeline is heated above its melting point at the cold plate 3, solving the problem of medium solidification caused by the extreme low temperature in the cryogenic space and ensuring that the internal circulation system has a stable cooling capacity. The temperature in the cryogenic space is extremely low. The cold plate 3 maintains the medium temperature above its melting point through heating, ensuring that the medium is always in a liquid state and ensuring its flow capacity in the pipeline. This allows the internal circulation to complete the cycle of "medium absorbing heat from equipment - cold plate 3 dissipating heat - medium returning", effectively removing the heat generated by satellite equipment 6 (especially high heat-consuming equipment), preventing equipment from experiencing performance degradation or failure due to overheating, and ensuring that the equipment temperature remains stable within the preset range.

[0095] Setting the melting point of the internal circulation medium below the first temperature further optimizes system energy consumption and operational reliability. The first temperature is the critical temperature for starting the external circulation (the equipment temperature needs to be raised when it is below this value). The fact that the medium's melting point is below the first temperature means that even if the equipment temperature drops to the first temperature (the external circulation start-up point), the internal circulation medium remains in a liquid state. This eliminates the need to additionally activate the heating components of the cold plate 3 to maintain the liquid state of the medium. Heating only needs to be activated when the medium temperature is close to its own melting point (far below the first temperature), significantly reducing the activation frequency and operating time of the heating components, lowering the power consumption of the energy storage module 5, and meeting the satellite's "low energy consumption" design requirements.

[0096] Finally, it should be noted that the above embodiments are only used to illustrate this application and are not intended to limit this application. Although this application has been described in detail with reference to the embodiments, those skilled in the art should understand that various combinations, modifications, or equivalent substitutions of the technical solutions of this application do not depart from the spirit and scope of the technical solutions of this application and should be covered within the scope of the claims of this application.

Claims

1. A dual cycle satellite thermal control system for maintaining the temperature of a satellite device (6) within a predetermined range, characterized by, The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system.

2. The two-cycle satellite thermal management system of claim 1, wherein, The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system.

3. The two-cycle satellite thermal management system of claim 1, wherein, The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system.

4. The two-cycle satellite thermal management system of any one of claims 1 to 3, wherein, The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system.

5. The two-cycle satellite thermal management system of any one of claims 1 to 3, wherein, The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system. 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The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat dissipation system. The application relates to a double-circulation satellite heat preservation and heat An inner circulation pipeline assembly (32) is arranged in the second shell (31); An electric heating assembly (33) is arranged in the second shell (31) to increase the temperature of the medium in the inner circulation pipeline assembly (32) to above the melting point.

6. A satellite, characterized by The double circulation satellite heat preservation and dissipation system comprises the double circulation satellite heat preservation and dissipation system according to any one of claims 1 to 5.

7. A method of satellite heat retention and dissipation, characterized by, The double circulation satellite heat preservation and dissipation system comprises the double circulation satellite heat preservation and dissipation system according to any one of claims 1 to 5. The temperature of the satellite device (6) is acquired; When the temperature of the satellite device (6) is lower than the first temperature, the medium in the outer circulation pipeline is heated by the solar panel (1) and then flows through the satellite device (6) to increase the temperature of the satellite device (6); When the temperature of the satellite device (6) is higher than the second temperature, the medium in the inner circulation pipeline is heated by the cold plate (3) and then flows through the satellite device (6) to decrease the temperature of the satellite device (6).

8. The satellite heat retaining and radiating method according to claim 7, wherein The medium in the inner circulation pipeline is heated to above the melting point at the cold plate (3); And the melting point of the medium in the inner circulation pipeline is lower than the first temperature.

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