Space cryogenic propellant loading refrigeration device and method
By combining a microfluidic heat exchanger and a Stirling refrigerator, the problems of heat exchange efficiency and power consumption of traditional heat exchangers in the process of cryogenic propellant refueling in space are solved, realizing efficient and low-power cryogenic propellant refueling cooling, which meets the technical requirements of on-orbit refueling in space.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- CENT SOUTH UNIV
- Filing Date
- 2026-04-10
- Publication Date
- 2026-07-14
AI Technical Summary
Traditional heat exchangers suffer from small heat exchange area, long heat conduction distance, and poor heat exchange efficiency during the refueling of cryogenic propellants in space. This leads to rapid heating and evaporation of liquid xenon and liquid krypton, resulting in increased pressure. Furthermore, the power requirements of the refrigeration unit are too high, which cannot meet the technical requirements of on-orbit refueling in space.
By combining microfluidic heat exchanger components with a Stirling refrigerator, the heat exchange area of cold energy is increased and the heat exchange distance of cold energy is shortened through microfluidic channels. Combined with insulation structure and radiator, the refrigerator power is optimized to achieve high-efficiency cooling.
It achieves high-efficiency, low-power cryogenic propellant refueling and cooling, reduces the weight and volume of the heat exchanger, improves the reliability and safety of the refrigeration unit, and meets the technical requirements for on-orbit refueling in space.
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Figure CN122384342A_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of space on-orbit refueling technology, and more specifically, to a space cryogenic propellant refueling refrigeration device and method. Background Technology
[0002] In the aerospace field, cryogenic propellants offer numerous advantages over ambient temperature propellants in satellite and spacecraft propulsion subsystems. In the field of spacecraft electric propulsion, compared to ambient temperature high-pressure gaseous propellants such as xenon and krypton, cryogenic propellants like liquid xenon and liquid krypton offer advantages such as high-density storage, small volume, large duty cycle, large payload, low storage pressure, lightweight tanks, and on-orbit refueling capability.
[0003] Currently, satellites and spacecraft face the historical challenge of running out of fuel and reaching the end of their lifespan. By establishing space refueling stations and adopting on-orbit refueling technology, we can ensure that satellites and spacecraft can be used repeatedly, thereby increasing the lifespan of spacecraft, improving the economics of space missions, reducing overall costs, and laying a technological foundation for the sustainable development of space exploration.
[0004] The refueling process of liquefied xenon and krypton for satellite electric propulsion engines is affected by factors such as the space thermal environment, satellite wall heat exchange, pipeline heat dissipation, and pre-cooling of the refueling tank. This can cause the liquid xenon and krypton to heat up rapidly, evaporate and vaporize, resulting in increased pressure and refueling failure. Alternatively, it can cause the liquid xenon and krypton in the refueling tank to be in a high-temperature, high-pressure saturated state, which is not conducive to the safe zero-evaporation storage requirements of cryogenic propellants.
[0005] Traditional finned convection heat exchangers have small heat exchange areas, long heat conduction distances, and poor heat exchange efficiency. To meet the required heat exchange efficiency, they are extremely large and heavy, failing to meet the technical requirements of compact size, lightweight design, and high performance. Using traditional heat exchangers necessitates increasing the chiller power by 2-3 times, raising the space's electrical power consumption and failing to meet the platform's low power consumption requirements. Therefore, traditional heat exchangers cannot meet the technical requirements for on-orbit refueling in space. Summary of the Invention
[0006] This application provides a space cryogenic propellant refueling refrigeration device and method, which solves problems such as evaporation loss, temperature and pressure rise, excessive power consumption of the refrigeration unit, and large size and weight of the heat exchanger during space cryogenic propellant refueling, and achieves high-efficiency and low-power cryogenic propellant refueling refrigeration.
[0007] To achieve the above objectives, this application provides a space cryogenic propellant refueling and cooling device, comprising a fluid inlet, a microfluidic heat exchanger assembly, a fluid outlet, a refrigeration unit, a radiator, an insulation structure, and a measurement and control component. The fluid inlet receives the cryogenic propellant to be refueled; the inlet end of the microfluidic heat exchanger assembly is connected to the fluid inlet for heat exchange and cooling of the cryogenic propellant; the fluid outlet is connected to the outlet end of the microfluidic heat exchanger assembly for outputting the cooled cryogenic propellant to the target tank; the refrigeration unit includes an expander and a compressor connected in sequence; the expander is connected to the microfluidic heat exchanger assembly via a cold head for providing cooling; the radiator is connected to the compressor for radiating heat into outer space; the insulation structure covers the outside of the microfluidic heat exchanger assembly to reduce cooling loss; and the measurement and control component is electrically connected to the refrigeration unit and the radiator respectively for controlling the cooling temperature and power of the refrigeration unit.
[0008] Furthermore, the microfluidic heat exchanger assembly is composed of multiple microfluidic units, each of which includes a dual-channel fluid plate, a fluid inlet branch fluid plate, a transition fluid plate, and a fluid outlet confluence fluid plate stacked sequentially.
[0009] Furthermore, microchannels are provided on the dual-channel fluid plate, the fluid inlet branch fluid plate, and the fluid outlet confluence fluid plate. Specifically, the dual-channel fluid plate has two microchannels; the fluid inlet branch fluid plate and the fluid outlet confluence fluid plate each have ≥10 microchannels; and the cross-sectional length of the microchannels is ≤200 micrometers and the width is ≤200 micrometers.
[0010] Furthermore, the transition fluid plate is provided with transition holes, which are rectangular in structure. The number of these transition holes is the same as the number of microchannels on the fluid inlet branch fluid plate and the fluid outlet confluence fluid plate. The length and width of the transition holes are both ≤1mm.
[0011] Furthermore, the insulation structure, from the inside out, includes a polyimide foam layer, a cold shield, and a variable density multilayer insulation layer, wherein: the thickness of the polyimide foam layer is ≥5mm; the thickness of the variable density multilayer insulation layer is ≥20mm; and the cold shield is a copper alloy cold shield with a thickness ≤1mm, located between the polyimide foam layer and the variable density multilayer insulation layer.
[0012] Furthermore, the cold head includes a first cold head and a second cold head, wherein: the first cold head is connected to the flange of the microfluidic heat exchanger assembly for cooling the cryogenic propellant flowing through the microfluidic heat exchanger assembly; and the second cold head is fastened to the cold screen for cooling the cold screen.
[0013] Furthermore, it also includes flow meters and temperature sensors, wherein: the flow meter is installed on the pipeline connected to the fluid inlet or fluid outlet to monitor the flow rate of the cryogenic propellant; multiple temperature sensors are installed on the pipeline at the fluid inlet, the pipeline at the fluid outlet, the heat exchange surface of the microfluidic heat exchanger assembly, and the insulation structure to monitor the temperature at different locations; the flow meter and multiple temperature sensors are all connected to the measurement and control components.
[0014] Furthermore, the applicable temperature range for the temperature sensor and flow meter is -230K to 60K.
[0015] Furthermore, the refrigeration unit is a Stirling refrigeration unit with a refrigeration power of >60W / 120K and a refrigeration temperature at least 1K higher than the solid phase temperature of the cryogenic propellant.
[0016] In addition, this application also provides a method for manufacturing a space cryogenic propellant refueling refrigeration device, comprising the following steps: Step 1: Use copper alloy material to machine the fluid inlet and fluid outlet; Step 2: Use chemical etching to fabricate the dual-channel fluid plate, the fluid inlet branch fluid plate, the transition fluid plate, and the fluid outlet confluence fluid plate; Step 3: Use diffusion welding process to combine and connect the dual-channel fluid plate, the fluid inlet branch fluid plate, the transition fluid plate, and the fluid outlet confluence fluid plate to form a microfluidic heat exchanger assembly. Step 4: Weld the fluid inlet, microfluidic heat exchanger assembly, and fluid outlet together. Step 5: Assemble the microfluidic heat exchanger assembly, temperature sensor, flow meter, refrigeration unit, radiator, and measurement and control components; Step 6: Sequentially fabricate a polyimide foam layer, a cold shield, and a variable density multilayer insulation layer on the outside of the microfluidic heat exchanger assembly to form an insulation structure.
[0017] The space cryogenic propellant refueling and cooling device and method provided in this application have the following beneficial effects: 1. The microfluidic heat exchanger assembly of this application uses microfluidic channels as fluid paths, which greatly increases the heat exchange area of cold energy, shortens the heat exchange distance of cold energy, enhances the active cooling heat exchange efficiency, reduces the weight and volume of the heat exchanger, and reduces the power consumption of the refrigerator. It has the advantages of high efficiency, low power consumption, high reliability, and high safety. 2. This application physically connects the expander cold head to the microfluidic heat exchanger assembly flange. By setting the shortest path for refrigeration energy transfer, the loss of cold energy is reduced. The cold head and the heat exchanger are connected in parallel with a multi-channel microfluidic channel for direct heat conduction and refrigeration, which maximizes the heat exchange area between the refrigeration cold head and the heat exchanger, and improves the internal temperature uniformity of the heat exchanger and the refrigeration efficiency of the refrigeration system. 3. This application manufactures polyimide foam and variable density multilayer insulation on the outside of the microfluidic heat exchanger assembly, which effectively controls radiative heat transfer, ensures the balance of cooling capacity under insulation conditions, and effectively implements the thermal management of the structure. Attached Figure Description
[0018] The accompanying drawings, which form part of this application, are used to provide a further understanding of the application and to make other features, objects, and advantages of the application more apparent. The illustrative embodiments and descriptions of this application are used to explain the application and do not constitute an undue limitation of the application. In the drawings: Figure 1 This is a schematic diagram of the structure of a space cryogenic propellant refueling and cooling device according to an embodiment of this application; Figure 2 This is a schematic diagram of a microfluidic heat exchanger assembly provided according to an embodiment of this application; Figure 3 This is a schematic diagram and enlarged view of a single microfluidic unit according to embodiments of this application; Figure 4 This is a schematic diagram of a combination of multiple microfluidic units provided according to embodiments of this application; In the diagram: 1-Fluid inlet, 2-Microfluidic heat exchanger assembly, 21-Dual-channel fluid plate, 22-Fluid inlet branch fluid plate, 23-Transition fluid plate, 24-Fluid outlet merging fluid plate, 3-Fluid outlet, 4-Refrigeration unit, 41-Expander, 42-Compressor, 5-Radiator, 6-Insulation structure, 61-Polyimide foam layer, 62-Cold shield, 63-Variable density multilayer insulation layer, 7-Measurement and control components, 8-First cold head, 9-Second cold head, 10-Flow meter, 11-Temperature sensor. Detailed Implementation
[0019] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of the present application.
[0020] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate for the embodiments of this application described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.
[0021] In this application, the terms "upper," "lower," "left," "right," "front," "rear," "top," "bottom," "inner," "outer," "middle," "vertical," "horizontal," "lateral," and "longitudinal" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These terms are primarily for the purpose of better describing this application and its embodiments, and are not intended to limit the indicated device, element, or component to having a specific orientation, or to be constructed and operated in a specific orientation.
[0022] Furthermore, in addition to indicating location or positional relationship, some of the aforementioned terms may also have other meanings. For example, the term "above" may also be used in some cases to indicate a certain dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this application based on the specific circumstances.
[0023] In addition, the term "multiple" should mean two or more.
[0024] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.
[0025] like Figure 1-2As shown, this application provides a space cryogenic propellant refueling and cooling device, including a fluid inlet 1, a microfluidic heat exchange component 2, a fluid outlet 3, a cooling unit 4, a radiator 5, an insulation structure 6, and a measurement and control component 7, wherein: the fluid inlet 1 is used to receive the cryogenic propellant to be refueled; the inlet end of the microfluidic heat exchange component 2 is connected to the fluid inlet 1 for heat exchange and cooling of the cryogenic propellant; the fluid outlet 3 is connected to the outlet end of the microfluidic heat exchange component 2 for outputting the cooled cryogenic propellant to the target tank; the cooling unit 4 includes an expander 41 and a compressor 42 connected in sequence; the expander 41 is connected to the microfluidic heat exchange component 2 through a cold head for providing cooling capacity; the radiator 5 is connected to the compressor 42 for radiating heat into outer space; the insulation structure 6 covers the outside of the microfluidic heat exchange component 2 for reducing cooling capacity loss; the measurement and control component 7 is electrically connected to the cooling unit 4 and the radiator 5 respectively for controlling the cooling temperature and power of the cooling unit 4.
[0026] Specifically, the cryogenic propellant refueling and cooling device provided in this application embodiment features low power consumption, small size, light weight, high reliability, and high safety. During operation, the cryogenic fluid enters the microfluidic heat exchange component 2 through the fluid inlet 1, is cooled by the refrigeration unit 4, and temperature and flow information are fed back through the temperature sensor 11 and flow meter 10. This optimizes the operating parameters of the expander 41 and compressor 42 of the refrigeration unit 4, achieving efficient cooling of the cryogenic fluid. The pre-cooled cryogenic fluid flows out from the fluid outlet 3 and enters the cryogenic storage tank, completing the on-orbit refueling of cryogenic propellant.
[0027] More specifically, fluid inlet 1 is used to receive cryogenic propellant (such as liquid xenon or liquid krypton) to be refueled. The inlet end of the microfluidic heat exchange assembly 2 is connected to fluid inlet 1 for heat exchange and cooling of the cryogenic propellant. Fluid outlet 3 is connected to the outlet end of the microfluidic heat exchange assembly 2 for outputting the cooled cryogenic propellant to the target tank. The refrigeration unit 4 includes an expander 41 and a compressor 42 connected in sequence. The expander 41 is connected to the microfluidic heat exchange assembly 2 via a cold head to provide cooling. The radiator 5 is connected to the compressor 42 to radiate heat into outer space, preventing the heat from the compressor 42 from affecting the system's cooling efficiency. The insulation structure 6 covers the outside of the microfluidic heat exchange assembly 2 to reduce cooling loss. The measurement and control assembly 7 is electrically connected to the refrigeration unit 4 and the radiator 5 respectively, and is used to optimize the operating parameters of the expander 41 and the compressor 42 based on the feedback temperature and flow information to efficiently cool the cryogenic fluid.
[0028] Furthermore, such as Figure 3-4As shown, the microfluidic heat exchange assembly 2 is composed of multiple microfluidic units. Each microfluidic unit includes a dual-channel fluid plate 21, a fluid inlet branch fluid plate 22, a transition fluid plate 23, and a fluid outlet confluence fluid plate 24 stacked sequentially. The number of microfluidic units is not less than 60, and preferably 160 in this embodiment.
[0029] Furthermore, microchannels are provided on the dual-channel fluid plate 21, the fluid inlet branch fluid plate 22, and the fluid outlet confluence fluid plate 24. Specifically, the dual-channel fluid plate 21 has two microchannels; the fluid inlet branch fluid plate 22 and the fluid outlet confluence fluid plate 24 each have ≥10 microchannels; and the cross-sectional length and width of the microchannels are ≤200 micrometers.
[0030] Specifically, in the microfluidic heat exchange component 2, the thickness of each fluid plate is preferably 150 micrometers, the diameter of its main channel passing through the fluid inlet 1 and the fluid outlet 3 is preferably 3 millimeters, the flow rate is preferably 2 L / min, and the structural accuracy is better than 0.05 millimeters. Simultaneously, microchannels are provided on the dual-channel fluid plate 21, the fluid inlet branch fluid plate 22, and the fluid outlet confluence fluid plate 24. The cross-sectional length and width of the microchannels are preferably 150 micrometers, the structural accuracy of the microchannels is better than ±20 micrometers, and the number of microchannels on the fluid inlet branch fluid plate 22 and the fluid outlet 3 confluence fluid plate 24 is preferably 30.
[0031] Furthermore, the transition fluid plate 23 is provided with transition holes. The transition holes have a rectangular structure, and their number is the same as the number of microchannels on the fluid inlet branch fluid plate 22 and the fluid outlet confluence fluid plate 24. The length and width of the transition holes are both ≤1 mm. The transition holes of the transition fluid plate 23 have a rectangular structure, and their number is the same as the number of microchannels on the fluid inlet branch fluid plate 22 and the fluid outlet confluence fluid plate 24. Their positions are matched, and their length and width are preferably both 0.35 mm.
[0032] Furthermore, by adopting a multi-layer microfluidic channel structure, the heat exchange area of cold energy is greatly increased within a limited volume, the heat exchange distance is shortened, and the refrigeration efficiency is improved.
[0033] Furthermore, the insulation structure 6, from the inside out, includes a polyimide foam layer 61, a cold shield 62, and a variable-density multilayer insulation layer 63, wherein: the thickness of the polyimide foam layer 61 is ≥5mm; the thickness of the variable-density multilayer insulation layer 63 is ≥20mm; and the cold shield 62 is a copper alloy cold shield 62 with a thickness ≤1mm, located between the polyimide foam layer 61 and the variable-density multilayer insulation layer 63. The insulation structure 6 integrates passive insulation and active cooling technologies, effectively controlling cooling loss.
[0034] Furthermore, the cold head includes a first cold head 8 and a second cold head 9, wherein: the first cold head 8 is connected to the flange of the microfluidic heat exchange component 2, the flange diameter is preferably 60mm, and it is screwed with M5 bolts, and is used to cool the cryogenic propellant flowing through the microfluidic heat exchange component 2; the second cold head 9 is fastened to the cold screen 62, and is used to cool the cold screen 62.
[0035] Furthermore, it also includes a flow meter 10 and a temperature sensor 11, wherein: the flow meter 10 is installed on the pipeline connected to the fluid inlet 1 or the fluid outlet 3, and is used to monitor the flow rate of the cryogenic propellant; multiple temperature sensors 11 are installed on the pipeline of the fluid inlet 1, the pipeline of the fluid outlet 3, the heat exchange surface of the microfluidic heat exchange component 2, and the insulation structure 6, respectively, and are used to monitor the temperature at different locations; the flow meter 10 and multiple temperature sensors 11 are all connected to the measurement and control component 7.
[0036] Furthermore, the applicable temperature range of temperature sensor 11 and flow meter 10 is -230K to 60K, the accuracy of temperature sensor 11 is better than 0.01K, and the accuracy of flow meter 10 is better than 0.1%.
[0037] Furthermore, the refrigeration unit 4 is a Stirling refrigeration unit with a refrigeration power of >60W / 120K and a refrigeration temperature at least 1K higher than the solid phase temperature of the cryogenic propellant to prevent the propellant from solidifying.
[0038] Specifically, during operation, the cryogenic propellant enters the microfluidic heat exchange component 2 from the fluid inlet 1, where it undergoes efficient heat exchange with the cooling capacity provided by the refrigeration unit 4 in the microfluidic channel, resulting in a temperature reduction. The temperature sensor 11 and the flow meter 10 monitor the temperature, flow rate, and temperature data at key locations of the propellant in real time and transmit the data to the measurement and control component 7. Based on preset parameters and real-time feedback, the measurement and control component 7 controls the cooling temperature and power of the refrigeration unit 4 to ensure that the output fluid reaches the required low-temperature state. The cooled cryogenic propellant flows out from the fluid outlet 3 and enters the target storage tank, completing the on-orbit refueling pre-cooling.
[0039] Furthermore, this application also provides a method for manufacturing a space cryogenic propellant refueling and cooling device, which employs chemical etching and diffusion welding processes to improve the structural precision of the microfluidic channel and solve the problem of stringent cryogenic cooling requirements for satellite on-orbit refueling. The method includes the following steps: Step 1: Use copper alloy material to machine fluid inlet 1 and fluid outlet 3; Step 2: The dual-channel fluid plate 21, the fluid inlet branch fluid plate 22, the transition fluid plate 23, and the fluid outlet confluence fluid plate 24 are fabricated using a chemical etching process. The chemical etching process can achieve a high-precision microchannel structure and meet the micron-level dimensional tolerance requirements.
[0040] Step 3: The dual-channel fluid plate 21, the fluid inlet branch fluid plate 22, the transition fluid plate 23, and the fluid outlet confluence fluid plate 24 are combined and connected using diffusion welding to form the microfluidic heat exchange component 2. Diffusion welding can achieve seamless and high-strength connection between multiple thin plates, ensuring the sealing and structural integrity of the microchannel.
[0041] Step 4: Weld the fluid inlet 1, the microfluidic heat exchange component 2, and the fluid outlet 3 together; Step 5: Assemble the microfluidic heat exchanger 2, temperature sensor 11, flow meter 10, refrigeration unit 4, radiator 5, and measurement and control components 7; Step 6: Sequentially fabricate a polyimide foam layer 61, a cold shield 62, and a variable density multilayer insulation layer 63 on the outside of the microfluidic heat exchange component 2 to form an insulation structure 6.
[0042] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.
Claims
1. A space cryogenic propellant refueling and refrigeration device, characterized in that, This includes a fluid inlet, microfluidic heat exchanger assembly, fluid outlet, refrigeration unit, radiator, insulation structure, and measurement and control components, among which: The fluid inlet is used to receive the cryogenic propellant to be refueled; The inlet end of the microfluidic heat exchanger assembly is connected to the fluid inlet for heat exchange and cooling of the cryogenic propellant. The fluid outlet is connected to the outlet end of the microfluidic heat exchanger assembly and is used to output the cooled cryogenic propellant to the target tank. The refrigeration unit includes an expander and a compressor connected in sequence; The expander is connected to the microfluidic heat exchanger assembly via a cold head to provide cooling capacity; The radiator is connected to the compressor and is used to radiate heat into outer space. The insulation structure covers the outside of the microfluidic heat exchanger assembly to reduce cooling loss. The measurement and control components are electrically connected to the refrigeration unit and the radiator, respectively, and are used to control the refrigeration temperature and power of the refrigeration unit.
2. The space cryogenic propellant refueling and refrigeration device according to claim 1, characterized in that, The microfluidic heat exchanger assembly is composed of multiple microfluidic units, each of which includes a dual-channel fluid plate, a fluid inlet branch fluid plate, a transition fluid plate, and a fluid outlet confluence fluid plate stacked sequentially.
3. The space cryogenic propellant refueling and refrigeration device according to claim 2, characterized in that, The dual-channel fluid plate, the fluid inlet branch fluid plate, and the fluid outlet confluence fluid plate are all provided with microchannels, wherein: The dual-channel fluid plate is provided with two microchannels; The number of microchannels on the fluid inlet branch fluid plate and the fluid outlet confluence fluid plate is ≥10; The cross-sectional length of the microchannel is ≤200 micrometers and the width is ≤200 micrometers.
4. The space cryogenic propellant refueling and refrigeration device according to claim 3, characterized in that, The transition fluid plate is provided with transition holes, which are rectangular in structure. The number of these transition holes is the same as the number of microchannels on the fluid inlet branch fluid plate and the fluid outlet confluence fluid plate. The length and width of the transition holes are both ≤1mm.
5. The space cryogenic propellant refueling and refrigeration device according to claim 1, characterized in that, The insulation structure, from the inside out, comprises a polyimide foam layer, a cold shield, and a variable-density multilayer insulation layer, wherein: The thickness of the polyimide foam layer is ≥5mm; The thickness of the variable density multilayer insulation layer is ≥20mm; The cold shield is a copper alloy cold shield with a thickness of ≤1mm, located between the polyimide foam layer and the variable density multilayer insulation layer.
6. The space cryogenic propellant refueling and refrigeration device according to claim 5, characterized in that, The cold head includes a first cold head and a second cold head, wherein: The first cold head is connected to the flange of the microfluidic heat exchanger assembly and is used to cool the cryogenic propellant flowing through the microfluidic heat exchanger assembly; The second cold head is securely connected to the cold screen and is used to cool the cold screen.
7. The space cryogenic propellant refueling and refrigeration device according to claim 1, characterized in that, It also includes flow meters and temperature sensors, among which: The flow meter is installed on the pipeline connected to the fluid inlet or the fluid outlet to monitor the flow rate of the cryogenic propellant. Multiple temperature sensors are provided, respectively installed on the pipeline of the fluid inlet, the pipeline of the fluid outlet, the heat exchange surface of the microfluidic heat exchanger assembly, and the insulation structure, for monitoring the temperature at different locations; The flow meter and the multiple temperature sensors are all connected to the measurement and control component.
8. The space cryogenic propellant refueling and refrigeration device according to claim 7, characterized in that, The applicable temperature range for the temperature sensor and the flow meter is -230K to 60K.
9. The space cryogenic propellant refueling and refrigeration device according to claim 1, characterized in that, The refrigeration unit is a Stirling refrigeration unit with a refrigeration power >60W / 120K and a refrigeration temperature at least 1K higher than the solid phase temperature of the cryogenic propellant.
10. A method for manufacturing a space cryogenic propellant refueling and refrigeration device according to any one of claims 1-9, characterized in that, Includes the following steps: Step 1: Use copper alloy material to machine the fluid inlet and fluid outlet; Step 2: Use chemical etching to fabricate the dual-channel fluid plate, the fluid inlet branch fluid plate, the transition fluid plate, and the fluid outlet confluence fluid plate; Step 3: Use diffusion welding process to combine and connect the dual-channel fluid plate, the fluid inlet branch fluid plate, the transition fluid plate, and the fluid outlet confluence fluid plate to form a microfluidic heat exchanger assembly. Step 4: Weld the fluid inlet, microfluidic heat exchanger assembly, and fluid outlet together. Step 5: Assemble the microfluidic heat exchanger assembly, temperature sensor, flow meter, refrigeration unit, radiator, and measurement and control components; Step 6: Sequentially fabricate a polyimide foam layer, a cold shield, and a variable density multilayer insulation layer on the outside of the microfluidic heat exchanger assembly to form an insulation structure.