Pump-reservoir temperature control device and method in space environment

Abstract

The present application relates to a kind of space environment under pump-reservoir temperature control device and method, space environment under pump-reservoir temperature control device includes heat insulation shell, reservoir, pump, cold plate assembly, first radiation condenser, second radiation condenser, first pipeline, second pipeline and third pipeline, first radiation condenser is installed on heat insulation shell and is formed with heat insulation shell jointly closed heat insulation cavity, reservoir and pump are all installed in closed heat insulation cavity;The inlet of pump is connected and communicated with the outlet of first radiation condenser by first pipeline, the outlet of pump is connected and communicated with the inlet of cold plate assembly by second pipeline, the outlet of cold plate assembly is connected and communicated with the inlet of second radiation condenser by third pipeline, the outlet of second radiation condenser is connected and communicated with the inlet of reservoir and the inlet of first radiation condenser by fourth pipeline respectively.By setting closed heat insulation cavity with radiation condenser, the impact of on-orbit external transient heat flow on the inlet side of pump can be effectively coped with.

Description

Technical Field

[0001] This invention relates to the field of aerospace thermal control technology, specifically to a pump-reservoir temperature control device and method in a space environment. Background Technology

[0002] As spacecraft develop towards higher integration and higher power, the heat flux density of electronic components continues to rise. Mechanically Pumped Two-phase Loop (MPTL) technology has become a key technology direction in the field of high power density thermal control for spacecraft.

[0003] In spacecraft engineering practice, the pumps and reservoirs of the MPTL (Multi-Pump Tank Transfer Unit) are core functional components for system operation. The pumps provide the driving force for the working fluid circulation, and their performance directly affects the system's flow distribution and heat transfer efficiency. The reservoirs, on the other hand, perform multiple functions, including working fluid storage, vapor-liquid separation, pressure regulation, and temperature control, making them crucial for maintaining stable system operation. Considering factors such as satellite mounting interfaces, structural layout, thermal coupling relationships, and ease of piping connections, the pump-reservoir assembly is typically installed externally to the satellite frame. However, when the pump-reservoir is installed externally, the assembly is directly exposed to the space thermal environment, subjected to the combined effects of external space heat flows, including solar radiation, Earth's albedo, and Earth's infrared radiation. The magnitude and direction of these external space heat flows vary drastically with the spacecraft's orbital attitude and operational period, resulting in an extremely complex and harsh temperature environment for the pump-reservoir assembly.

[0004] The thermal effects of external heat flow on the pump-receiver assembly are mainly reflected in the following two aspects: Firstly, under the continuous heating effect of external heat flow, the temperature of the pump body and inlet side pipeline increases significantly. Especially for the pump inlet area, excessively high temperatures may cause the working fluid to reach saturation or even generate steam, resulting in insufficient or complete loss of subcooling of the working fluid at the pump inlet. Secondly, the internal temperature and pressure of the receiver change under the influence of external heat flow. When the external power decreases or the system needs to drain and regulate, the temperature of the fluid discharged from the receiver is high. If not effectively controlled, the high-temperature fluid will directly enter the pump.

[0005] Furthermore, the liquid reservoir undergoes a drainage process during operation. If the high-temperature fluid accompanying this drainage directly enters the pump inlet, it will further exacerbate the pump's cavitation risk. Therefore, effectively reducing the impact of external heat flow on the pump and addressing the effects of liquid reservoir drainage on pump cavitation have become critical technical challenges that urgently need to be overcome in the application of pump-driven two-phase fluid loop technology in space.

[0006] A utility model patent with authorization announcement number CN205168942U proposes an automatically adjustable heat insulation plate. It uses a Ni-Ti based shape memory alloy plate as the driving element, combined with multi-layer heat insulation components and a solar absorption coating, to achieve adaptive heat insulation functionality by automatically unfolding and rolling up according to light intensity. This device can unfold to shield the radiator at high temperatures, reducing the equivalent emissivity and thus providing heat insulation; and automatically roll up at low temperatures, allowing the radiator to dissipate heat completely. However, this patent mainly focuses on adjusting the heat dissipation area of ​​the radiator and does not address the heat insulation protection of the pump inlet pipe.

[0007] Chinese patent application CN116424579A discloses a two-phase fluid loop system for spacecraft heat dissipation. This system employs a microchannel cold plate to achieve vapor-liquid separation, reducing internal flow instability and solving the problems of cavitation in mechanical pumps and liquid slugging in compressors. The patent achieves vapor-liquid separation through a microchannel cold plate structure within the evaporation unit, ensuring that the working fluid entering the mechanical pump is in the liquid phase, thus preventing cavitation. However, this solution primarily addresses the impact of the two-phase flow at the evaporator outlet on the pump, without providing protective measures against the heating of the pump inlet by external heat flow.

[0008] In a two-phase pump-driven loop system with multiple evaporators and radiators developed by a certain company, a phase separator and a thermoelectric subcooler are installed before the pump inlet. The phase separator separates the vapor phase in the two-phase flow at the radiator outlet, allowing only single-phase liquid to enter the circulating pump; the thermoelectric subcooler subcools the saturated liquid by less than 1°C with a relatively small cooling power, ensuring sufficient net positive suction head (NPSH) at the pump inlet to prevent cavitation. This scheme increases system complexity and power consumption, and the subcooler's cooling capacity is limited, potentially making it difficult to maintain sufficient subcooling under strong external heat flow conditions.

[0009] In summary, existing technologies have the following shortcomings in addressing the impact of external space heat flow on pump-reservoir components: 1) Existing thermal insulation technologies primarily target the thermal protection of spacecraft cabins, radiators, or large equipment, lacking miniaturized, high-precision thermal insulation designs for pump-reservoir components. When the pump is installed outside the satellite frame, the pump-reservoir components are directly exposed to the external heat flow environment, and traditional multi-layered thermal insulation materials are difficult to adapt to complex piping layouts and confined installation spaces. 2) The impact of high-temperature fluid on the pump during reservoir drainage has not been effectively resolved. When the reservoir needs to drain for operational adjustments, if the drainage temperature is too high, the high-temperature fluid entering the pump inlet will cause localized overheating, increasing the risk of cavitation. Existing technologies lack active control measures for the drainage temperature of the reservoir. 3) Existing solutions often sacrifice cavitation protection for increased system complexity, power consumption, and weight, such as adding phase separators and thermoelectric coolers, which contradicts the spacecraft's requirements for low power consumption and high reliability.

[0010] Therefore, in order to meet the application requirements of long-term reliable operation of pump-reservoir assemblies in orbit, there is an urgent need to develop a temperature control method and device that can overcome the difficulties of existing technologies. Summary of the Invention

[0011] In order to solve one or more technical problems existing in the prior art, the present invention provides a pump-reservoir temperature control device and method in a space environment.

[0012] The technical solution of the present invention to solve the above-mentioned technical problems is as follows: The present invention provides a pump-storage temperature control device in a space environment, including a heat insulation shell, a storage tank, a pump, a cold plate assembly, a first radiant condenser, a second radiant condenser, a first pipeline, a second pipeline and a third pipeline. The first radiant condenser is installed on the heat insulation shell and together with the heat insulation shell forms a closed heat insulation cavity. The storage tank and the pump are both installed in the closed heat insulation cavity. The pump inlet is connected to the outlet of the first radiant condenser via a first pipeline, the pump outlet is connected to the inlet of the cold plate assembly via a second pipeline, the cold plate assembly outlet is connected to the inlet of the second radiant condenser via a third pipeline, and the outlet of the second radiant condenser is connected to the inlet of the liquid reservoir and the inlet of the first radiant condenser via a fourth pipeline.

[0013] The beneficial effects of this invention are as follows: The pump-reservoir temperature control device in the space environment of this invention, by setting a closed heat insulation cavity with a first radiant condenser, can effectively cope with the impact of transient heat flow outside the orbit on the pump inlet side, and prevent the pump from cavitation due to excessively high inlet temperature; it can also eliminate the influence of high-temperature discharge of the reservoir on pump cavitation, and can actively control the fluid temperature through the first radiant condenser during reservoir discharge to avoid high-temperature fluid directly entering the pump; it can also provide a radiant low-temperature environment for the pump and reservoir, ensuring that the fluid temperature near the pump is at a low level and facilitating reservoir temperature control.

[0014] Based on the above technical solution, the present invention can be further improved as follows.

[0015] Furthermore, the heat insulation housing includes a mounting plate and a heat insulation enclosure. The heat insulation enclosure surrounds the mounting plate and forms a top-open mounting cavity. The liquid reservoir and the pump are both located in the mounting cavity and mounted on the mounting plate. The first radiative condenser is mounted at the top open end of the mounting cavity.

[0016] The beneficial effect of adopting the above-mentioned further solution is that by setting up the mounting plate and the heat insulation plate, it is possible to effectively prevent external heat from entering the heat insulation cavity and avoid affecting the pump and the liquid reservoir.

[0017] Furthermore, the heat insulation panel is arranged in a rectangular structure.

[0018] The beneficial effects of adopting the above-mentioned further solution are: the use of a rectangular structure for the heat insulation enclosure facilitates the installation and fixing of pumps and liquid reservoirs.

[0019] Furthermore, multiple supports are provided between the first radiative condenser and the mounting plate.

[0020] The beneficial effect of adopting the above-mentioned further solution is that by setting up multiple supports, the installation of the first radiative condenser can be effectively supported.

[0021] Furthermore, the first radiative condenser includes a pre-pump radiative subcooler pipeline and a phase change plate. The pre-pump radiative subcooler pipeline is embedded on the side of the phase change plate facing the liquid reservoir. The side of the phase change plate facing away from the liquid reservoir is coated with a radiative coating. The phase change plate has a cavity, and the cavity is filled with a phase change material.

[0022] The beneficial effects of adopting the above-mentioned further scheme are as follows: By setting up a phase change plate and a pre-pump radiation subcooler pipeline, when the external heat flow power increases, the heat is first absorbed by the phase change material in the phase change plate in the form of solid-liquid phase change, converting the heat from the short-term high-power external heat flow into a continuous and stable phase change-radiation-condensation cycle, achieving periodic averaging of the external heat flow power. The phase change plate is coated with a high emissivity and low absorptivity coating facing the outer surface of space to radiate heat towards outer space, ensuring that the phase change plate remains in a low-temperature state for a long time; the internal cavity structure of the phase change plate can be realized by machining, 3D printing, or welding, and the cavity is filled with solid-liquid phase change materials, such as paraffin wax and inorganic salts, which remain in a solid state for a long time under the action of the radiation coating.

[0023] Furthermore, the phase change plate has multiple pipe mounting slots on one side facing the liquid storage tank. Multiple radiant subcooler pipes are provided before the pump and are respectively embedded in the corresponding pipe mounting slots. The two ends of the multiple radiant subcooler pipes before the pump are respectively connected to an inlet collector and an outlet collector. The inlet collector is connected to and communicates with the outlet of the first radiant condenser, and the outlet collector is connected to and communicates with the inlet of the pump through the first pipe.

[0024] The beneficial effect of adopting the above-mentioned further solution is that by setting up the pipeline installation groove, it is convenient to stably install the pipeline of the pre-pump radiant subcooler.

[0025] Furthermore, a heater is installed on the side of the phase change plate opposite to the liquid reservoir.

[0026] The beneficial effect of adopting the above-mentioned further solution is that by setting up a heater, when the space temperature is too low, the heater can be used to heat the space appropriately, thus preventing the pump and liquid reservoir from failing to work at low temperatures.

[0027] Furthermore, a first inlet is provided on the heat insulation shell, and a three-way connecting pipe is connected to the first inlet. The fourth pipe is connected and communicates with the first inlet. The first interface of the three-way connecting pipe is connected and communicates with the first inlet. The second interface of the three-way connecting pipe is connected and communicates with the inlet of the liquid reservoir. The third interface of the three-way connecting pipe is connected and communicates with the inlet of the first radiant condenser.

[0028] The beneficial effect of adopting the above-mentioned further solution is that by setting a three-way connecting pipe, it is convenient to connect the fourth pipeline to the first radiant condenser and the liquid receiver respectively.

[0029] Furthermore, the heat insulation shell is provided with a first outlet, and the second pipe passes through the first outlet.

[0030] This invention also provides a pump-reservoir temperature control method in a space environment, implemented using the pump-reservoir temperature control device described above. The reservoir, along with the pump, cold plate assembly, first radiant condenser, second radiant condenser, first pipeline, second pipeline, and third pipeline, all constitute a main temperature control loop containing a working fluid. The method includes the following steps: In on-orbit application, the pump drives the liquid working fluid to flow through the second pipeline, which transports the liquid working fluid to the cold plate assembly. The liquid working fluid undergoes a phase change in the cold plate assembly, becoming a two-phase gas-liquid working fluid. It is then transported through the third pipeline into the second radiative condenser for cooling. After the working fluid returns to a single-phase liquid, it partially exchanges with the working fluid in the reservoir through the fourth pipeline (either entering the reservoir through the fourth pipeline or merging with the liquid working fluid in the reservoir and entering the first radiative condenser). Part of it flows into the first radiative condenser, undergoes secondary cooling, and then flows back into the pump.

[0031] The beneficial effects of the present invention are: the pump-reservoir temperature control method in the space environment of the present invention, by setting a first radiant condenser, the first radiant condenser and the heat insulation shell are combined to form a radiant cooling screen device, thereby realizing effective thermal control of the pump-reservoir assembly and ensuring the long-term stable and reliable operation of the pump in the pump-driven two-phase fluid circuit. Attached Figure Description

[0032] Figure 1 This is a schematic diagram of the overall structure of the pump-reservoir temperature control device in a space environment according to the present invention; Figure 2 This is a schematic diagram of the split structure of the pump-reservoir temperature control device in a space environment according to the present invention; Figure 3 This is a three-dimensional structural diagram of the pre-pump radiant subcooler piping of the present invention; Figure 4 This is a three-dimensional structural diagram of the phase change plate of the present invention.

[0033] The attached diagram lists the components represented by each number as follows: 1. First heat insulation board; 11. Second heat insulation board; 12. Third heat insulation board; 13. Fourth heat insulation board; 14. Mounting plate; 15. Bracket; 2. First radiant condenser; 21. Radiant subcooler piping before pump; 22. Phase change plate; 23. Heater; 24. Piping mounting groove; 25. Inlet collector; 26. Outlet collector; 3. Liquid receiver; 4. Pump; 5. Cold plate assembly; 6. Second radiant condenser; 7. First pipeline; 71. Second pipeline; 72. Third pipeline; 73. Fourth pipeline; 8. T-connector pipe. Detailed Implementation

[0034] The principles and features of the present invention are described below. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0035] Example 1 like Figures 1-4 As shown, a pump-reservoir temperature control device in a space environment according to this embodiment includes a heat insulation shell, a reservoir 3, a pump 4, a cold plate assembly 5, a first radiant condenser 2, a second radiant condenser 6, a first pipeline 7, a second pipeline 71, and a third pipeline 72. The first radiant condenser 2 is installed on the heat insulation shell and together with the heat insulation shell forms a closed heat insulation cavity. The reservoir 3 and the pump 4 are both installed in the closed heat insulation cavity. The inlet of the pump 4 is connected to the outlet of the first radiant condenser 2 via the first pipe 7. The outlet of the pump 4 is connected to the inlet of the cold plate assembly 5 via the second pipe 71. The outlet of the cold plate assembly 5 is connected to the inlet of the second radiant condenser 6 via the third pipe 72. The outlet of the second radiant condenser 6 is connected to the inlet of the liquid reservoir 3 and the inlet of the first radiant condenser 2 via the fourth pipe 73.

[0036] The cold plate assembly 5 in this embodiment includes multiple cold plates connected in series. The first radiative condenser 2 and the second radiative condenser 6 can adopt the radiative condenser structure commonly used in space. A high emissivity and low absorptivity coating can be sprayed on the outer surface facing space to radiate heat towards outer space and realize the condensation of the working fluid.

[0037] The liquid reservoir 3 in this embodiment can be made of stainless steel.

[0038] The liquid receiver in this embodiment has a drainage and cooling function. During the operation of the pump-driven two-phase circuit (i.e., the circuit formed by the connection of various pipelines in this embodiment), when the heat source power decreases or is shut down, the mass fraction of the gas phase in the two-phase pipeline will decrease, and the liquid content will increase. The increased liquid needs to be replenished from the liquid receiver. Since the temperature control point of the liquid receiver is relatively high, the liquid replenished in the liquid receiver is a high-temperature liquid. Typically, the drainage process is characterized by short duration, high speed, and high temperature. If the liquid discharged from the liquid receiver is not cooled, it can easily cause cavitation in the pump once it flows into the pump, leading to pump damage. To address this, a pre-pump radiative subcooler (i.e., the first radiative condenser) is installed. It is a hollow pipeline assembly connected in parallel or series. The pipeline has a certain wall thickness and can withstand a certain pressure. The pipeline assembly can be achieved through welding, screwing, gluing, etc., to achieve effective thermal contact with the phase change plate.

[0039] This embodiment can form a closed heat insulation cavity by setting up a heat insulation shell and a first radiative condenser. The heat insulation shell can be equipped with multiple layers of heat insulation components. The heat insulation components are selected from commonly used space heat insulation structural components, and the number of layers is selected according to the requirements to shield the heat from the actual low-power external heat flow on the side.

[0040] The pump-reservoir temperature control device in this embodiment, through the setting of a closed heat insulation cavity with a first radiant condenser, can effectively cope with the impact of transient heat flow outside the orbit on the pump inlet side, and prevent the pump from cavitation due to excessively high inlet temperature; it can also eliminate the impact of high-temperature discharge from the reservoir on pump cavitation, and actively control the fluid temperature through the first radiant condenser during reservoir discharge to prevent high-temperature fluid from directly entering the pump; it can also provide a radiant low-temperature environment for the pump and reservoir, ensuring that the fluid temperature near the pump is at a low level and facilitating reservoir temperature control.

[0041] Example 2 Based on Example 1, this example provides a preferred structure for the heat insulation shell, such as... Figure 1 and Figure 2 As shown, the heat-insulating housing in this embodiment includes a mounting plate 14 and a heat-insulating enclosure. The heat-insulating enclosure surrounds the mounting plate 14 and forms a mounting cavity with an open top. The liquid reservoir 3 and the pump 4 are both located inside the mounting cavity and mounted on the mounting plate 14. The first radiant condenser 2 is mounted at the open top end of the mounting cavity. By setting the mounting plate and the heat-insulating enclosure, external heat can be effectively prevented from entering the heat-insulating cavity, avoiding any impact on the pump and the liquid reservoir.

[0042] Preferred, such as Figure 2 As shown, the heat insulation panel is arranged in a rectangular structure. The rectangular arrangement of the heat insulation panel facilitates the installation and fixing of pumps, liquid reservoirs, etc.

[0043] like Figure 1 and Figure 2 As shown, in this embodiment, multiple supports 15 are also provided between the first radiant condenser 2 and the mounting plate 14. By providing multiple supports, the installation of the first radiant condenser can be effectively supported.

[0044] Specifically, such as Figure 1 and Figure 2 As shown, the heat insulation enclosure in this embodiment includes a first heat insulation board 1, a second heat insulation board 11, a third heat insulation board 12, and a fourth heat insulation board 13. The first heat insulation board 1, the second heat insulation board 11, the third heat insulation board 12, and the fourth heat insulation board 13 are connected in sequence to form a rectangular frame structure.

[0045] Based on Embodiment 1 or Embodiment 2, this embodiment provides a preferred structure for the first radiative condenser 2, as shown in Figure 1~ Figure 4 As shown, the first radiative condenser 2 includes a pre-pump radiative subcooler pipe 21 and a phase change plate 22. The pre-pump radiative subcooler pipe 21 is embedded on the side of the phase change plate 22 facing the liquid reservoir 3. The side of the phase change plate 22 facing away from the liquid reservoir 3 is coated with a radiative coating. The phase change plate 22 has a cavity filled with phase change material. By setting the phase change plate and the pre-pump radiative subcooler pipe, when the external heat flow power increases, the heat is first absorbed by the phase change material in the phase change plate in the form of solid-liquid phase change, converting the heat from the short-term high-power external heat flow into a continuous and stable phase change-radiation-condensation cycle, achieving periodic averaging of the external heat flow power. The phase change plate is coated with a high emissivity and low absorptivity coating on its outer surface to radiate heat into outer space, thus keeping the phase change plate in a low-temperature state for a long time. The internal cavity structure of the phase change plate can be achieved by machining, 3D printing or welding. The cavity is filled with solid-liquid phase change materials, such as paraffin wax or inorganic salts. Under the action of the radiation coating, the phase change materials remain in a solid state for a long time.

[0046] Preferred, such as Figure 3 and Figure 4 As shown, in this embodiment, the phase change plate 22 facing the liquid reservoir 3 has multiple pipe mounting slots 24. Multiple pre-pump radiant subcooler pipes 21 are provided and respectively embedded in the corresponding pipe mounting slots 24. The two ends of each pre-pump radiant subcooler pipe 21 are connected to an inlet collector 25 and an outlet collector 26, respectively. The inlet collector 25 is connected to and communicates with the outlet of the first radiant condenser 2, and the outlet collector 26 is connected to and communicates with the inlet of the pump 4 through a first pipe 7. By providing pipe mounting slots, stable installation of the pre-pump radiant subcooler pipes is facilitated.

[0047] like Figure 1 and Figure 2As shown, in a preferred embodiment, a heater 23 is installed on the side of the phase change plate 22 facing away from the liquid reservoir 3. By providing a heater, when the ambient temperature is too low, the heater can be used to appropriately heat the water, preventing the pump and liquid reservoir from failing to operate at low temperatures.

[0048] Specifically, in this embodiment, the phase change plate 22 is a plate structure internally filled with phase change material. It can be a flat plate, an arc-shaped plate, or similar structure. A high emissivity, low absorptivity coating is sprayed onto the outer surface of space to radiate heat towards outer space, ensuring the phase change plate remains at a low temperature for extended periods. The internal cavity structure of the phase change plate can be achieved through machining, 3D printing, or welding. The cavity is filled with a solid-liquid phase change material, such as paraffin wax or inorganic salts. Under the action of the radiation coating, the phase change material remains in a solid state for a long period. The other side of the phase change plate has a pipe mounting groove, which facilitates the thermal connection between the phase change plate and multiple pre-pump radiation subcooler pipes. The connection can be welded or glued. To ensure proper assembly, the radius of the pipe mounting groove is larger than the outer diameter of the pipes. When the external heat flow power increases, the heat is first absorbed by the phase change material in the phase change plate through a solid-liquid phase change, converting the brief high-power external heat flow into a continuous and stable phase change-radiation-condensation cycle, achieving periodic averaging of the external heat flow power.

[0049] In this embodiment, when the liquid reservoir discharges liquid, the high-temperature liquid working fluid first flows through the pre-pump radiant subcooler pipeline. The heat carried by the high-temperature liquid working fluid is uniformly diffused in the pre-pump radiant subcooler pipeline and absorbed by the phase change material inside the phase change plate in the form of solid-liquid phase change. The phase change material then partially melts, thereby achieving the cooling process of the high-temperature liquid working fluid. After the discharge is completed, the coating sprayed on the outside of the phase change plate continues to radiate heat outward, achieving the re-solidification of the phase change material and preparing the cooling cycle for the next discharge process. To prevent the liquid in the pre-pump radiant subcooler pipeline from freezing, a heater is arranged in the phase change plate, and its temperature is controlled to ensure that the temperature at the lowest point is higher than the freezing point of the working fluid.

[0050] To maintain stable temperature control in the receiver during operation, its own heating device alone cannot meet the continuous temperature control requirements; a stable external cooling input is necessary. Furthermore, to ensure the pump can start at any time, the working fluid inside the pump must be kept in a reliably subcooled state, which also requires a continuous cooling supply. To solve these problems, the following structure is used: a bracket supports the first radiative condenser to a set height, creating a gap for heat radiation transfer; a high-emissivity coating or high-emissivity material is sprayed onto the pump, receiver housing, and the surface of the phase change plate facing the pump and receiver; in this arrangement, the cooling energy stored in the phase change plate is transferred to the pump and receiver via heat radiation, achieving stable temperature control for both and continuous subcooling of the working fluid inside the pump, thereby maintaining the system's operational reliability under dynamic external heat flow conditions.

[0051] This embodiment achieves effective thermal control of the pump-storage assembly by setting up a radiant cooling shield, ensuring the long-term stable and reliable operation of the pump in the pump-driven two-phase fluid loop. Specifically, by filling the radiant cooling shield with phase change material, external heat flow fluctuations are absorbed and buffered, reducing the impact of external thermal shocks on the assembly, thereby providing stable thermal boundary conditions for the pump and connected pipelines, ensuring that the internal fluid remains subcooled. Simultaneously, the liquid flowing out of the storage tank is cooled, effectively suppressing cavitation within the pump and providing a cooling shield environment for the storage tank's temperature control, enhancing its reliability and stability in on-orbit temperature control. The method and apparatus proposed in this invention solve the technical problem of pump cavitation caused by external heat flow fluctuations and excessively high temperatures of the liquid discharged from the storage tank during on-orbit operation of the pump-storage assembly, achieving long-term, stable, and reliable operation of the assembly in the space environment, and possessing good engineering application prospects.

[0052] Example 4 Based on any of the above embodiments, in this embodiment, the heat insulation shell is provided with a first inlet, and a three-way connecting pipe 8 is connected to the first inlet. The fourth pipe 73 is connected and communicates with the first inlet. The first interface of the three-way connecting pipe 8 is connected and communicates with the first inlet, the second interface of the three-way connecting pipe 8 is connected and communicates with the inlet of the liquid reservoir 3, and the third interface of the three-way connecting pipe 8 is connected and communicates with the inlet of the first radiant condenser 2. By providing the three-way connecting pipe, it is convenient for the fourth pipe to be connected to the first radiant condenser and the liquid reservoir respectively.

[0053] Optionally, the heat insulation shell is further provided with a first outlet, and the second pipe 71 passes through the first outlet.

[0054] Example 5 This embodiment provides a pump-reservoir temperature control method in a space environment, implemented using a pump-reservoir temperature control device as described in any of the above embodiments. The main temperature control loop, consisting of the reservoir 3, pump 4, cold plate assembly 5, first radiant condenser 2, second radiant condenser 6, first pipeline 7, second pipeline 71, and third pipeline 72, stores a working fluid. The method includes the following steps: In on-orbit application, pump 4 drives the liquid working medium to flow through the second pipeline 71. The second pipeline 71 transports the liquid working medium to the cold plate assembly 5. The liquid working medium undergoes a phase change in the cold plate assembly 5, becoming a two-phase gas-liquid working medium. It is then transported through the third pipeline 72 into the second radiative condenser 6 for cooling. After the working medium becomes a single-phase liquid working medium again, it partially exchanges with the working medium in the liquid reservoir 3 through the fourth pipeline 73 (either entering the liquid reservoir 3 through the fourth pipeline 73 or merging with the liquid working medium in the liquid reservoir 3 into the first radiative condenser 2). Part of it flows into the first radiative condenser 2 and, after secondary cooling, flows back to pump 4.

[0055] The pump-reservoir temperature control method in this embodiment, in a space environment, achieves effective thermal control of the pump-reservoir assembly by setting a first radiant condenser, which is combined with the heat insulation shell to form a radiant cooling screen device, thus ensuring the long-term stable and reliable operation of the pump in the pump-driven two-phase fluid circuit.

[0056] In the description of this invention, it should be understood that the terms "top", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing this invention 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, and therefore should not be construed as a limitation of this invention.

[0057] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0058] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0059] In this invention, unless otherwise explicitly 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," "over," and "on top" of 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.

[0060] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. 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.

[0061] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A pump-reservoir temperature control device for a space environment, characterized in that, It includes a heat insulation shell, a liquid reservoir, a pump, a cold plate assembly, a first radiative condenser, a second radiative condenser, a first pipeline, a second pipeline, and a third pipeline. The first radiative condenser is installed on the heat insulation shell and together with the heat insulation shell forms a closed heat insulation cavity. The liquid reservoir and the pump are both installed inside the closed heat insulation cavity. The pump inlet is connected to the outlet of the first radiant condenser via a first pipeline, the pump outlet is connected to the inlet of the cold plate assembly via a second pipeline, the cold plate assembly outlet is connected to the inlet of the second radiant condenser via a third pipeline, and the outlet of the second radiant condenser is connected to the inlet of the liquid reservoir and the inlet of the first radiant condenser via a fourth pipeline.

2. The pump-reservoir temperature control device for a space environment according to claim 1, characterized in that, The heat insulation housing includes a mounting plate and a heat insulation enclosure. The heat insulation enclosure surrounds the mounting plate and forms a top-open mounting cavity. The liquid reservoir and the pump are both located in the mounting cavity and mounted on the mounting plate. The first radiative condenser is mounted at the top open end of the mounting cavity.

3. The pump-reservoir temperature control device for a space environment according to claim 2, characterized in that, The heat insulation panel is arranged in a rectangular structure.

4. The pump-reservoir temperature control device for a space environment according to claim 2, characterized in that, Multiple supports are also provided between the first radiative condenser and the mounting plate.

5. The pump-reservoir temperature control device for a space environment according to claim 1, characterized in that, The first radiative condenser includes a pre-pump radiative subcooler pipeline and a phase change plate. The pre-pump radiative subcooler pipeline is embedded on the side of the phase change plate facing the liquid reservoir. The side of the phase change plate facing away from the liquid reservoir is coated with a radiative coating. The phase change plate has a cavity, which is filled with a phase change material.

6. The pump-reservoir temperature control device for a space environment according to claim 5, characterized in that, The phase change plate has multiple pipe mounting slots on one side facing the liquid storage tank. Multiple radiant subcooler pipes are provided before the pump and are respectively embedded in the corresponding pipe mounting slots. The two ends of the multiple radiant subcooler pipes before the pump are respectively connected to an inlet collector and an outlet collector. The inlet collector is connected to and communicates with the outlet of the first radiant condenser, and the outlet collector is connected to and communicates with the inlet of the pump through a first pipe.

7. The pump-reservoir temperature control device for a space environment according to claim 5, characterized in that, A heater is installed on the side of the phase change plate opposite to the liquid reservoir.

8. The pump-reservoir temperature control device for a space environment according to claim 1, characterized in that, The heat insulation shell has a first inlet, and a three-way connecting pipe is connected to the first inlet. The fourth pipe is connected to and communicates with the first inlet. The first interface of the three-way connecting pipe is connected to and communicates with the first inlet. The second interface of the three-way connecting pipe is connected to and communicates with the inlet of the liquid reservoir. The third interface of the three-way connecting pipe is connected to and communicates with the inlet of the first radiant condenser.

9. The pump-reservoir temperature control device for a space environment according to claim 1, characterized in that, The heat insulation shell is also provided with a first outlet, and the second pipeline passes through the first outlet.

10. A method for temperature control of a pump-reservoir in a space environment, characterized in that, The temperature control device for a pump-reservoir in a space environment, as described in any one of claims 1 to 9, is implemented by storing a working fluid in the reservoir and the main temperature control loop consisting of the pump, cold plate assembly, first radiant condenser, second radiant condenser, first pipeline, second pipeline, and third pipeline, and includes the following steps: In on-orbit application, the pump drives the liquid working fluid to flow through the second pipeline, which transports the liquid working fluid to the cold plate assembly. The liquid working fluid undergoes a phase change in the cold plate assembly, becoming a two-phase gas-liquid working fluid. It is then transported through the third pipeline to the second radiative condenser for cooling. After the working fluid becomes a single-phase liquid working fluid again, it exchanges part of its contents with the working fluid in the liquid reservoir through the fourth pipeline, and part of its contents flow into the first radiative condenser for secondary cooling before flowing back into the pump.

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