Satellite propellant working substance solid storage and partition phase change supply device and manufacturing method thereof

Abstract

The application relates to the technical field of satellite working medium cryogenic storage, in particular to a satellite propellant working medium solid-state storage and partitioned phase change supply device and a manufacturing method thereof.The device comprises a storage box shell, a storage box cover plate, a heat exchange assembly, a storage box liquid port, a storage box gas port, a refrigerator interface, an electric connector and a flowmeter, wherein the storage box shell is in sealed connection with the storage box cover plate to form a closed working medium storage space; the heat exchange assembly is arranged in the interior of the storage box shell; the storage box liquid port and the storage box gas port are arranged on the storage box cover plate; the refrigerator interface is arranged on the storage box shell; the electric connector is arranged on the storage box shell; and the flowmeter is connected with the storage box gas port.The application adopts solid working medium storage, the storage pressure is low, is suitable for the storage box structure design of special-shaped space layout, enhances the flexibility of the structure and layout design of a satellite propulsion system, improves the space occupation ratio of the working medium storage box, and provides additional space for satellite load configuration.

Description

Technical Field

[0001] This application relates to the field of cryogenic storage technology for satellite propellant, and more specifically, to a solid-state storage and partitioned phase change supply device for satellite propellant and its manufacturing method. Background Technology

[0002] Krypton, as the current and future mainstream propellant for electric propulsion, has advantages such as high specific impulse and low cost, and is widely used in aerospace satellite fields such as communication, remote sensing, navigation, manned spaceflight, and deep space exploration. Traditional ultra-high pressure gaseous storage methods have problems such as low storage density, large container volume, high storage pressure, and large container weight. Due to the volume and weight constraints of the satellite platform, the volume and weight of other functional equipment payloads are squeezed, and the number and configuration of functional equipment payloads cannot meet the target supporting capabilities, thus limiting the satellite's functions and performance and significantly reducing its performance indicators.

[0003] The densities of high-pressure krypton gas, cryogenic liquid krypton, and cryogenic solid krypton working fluids are 1110 kg / m³. 3 2405 kg / m 3 2830kg / m 3 Using cryogenic liquid and cryogenic solid states can significantly increase the density of krypton working propellant, meeting the requirements for small size and light weight in propulsion systems. Cryogenic liquid krypton storage requires a comprehensive surface tension management system, which is relatively complex and has high manufacturing costs. Cryogenic liquid krypton storage necessitates controlling the internal fluid distribution to prevent sloshing and ensure proper center of mass control. Strict control of internal pressure is required during storage and discharge, and the internal fluid control is quite complex, resulting in a high complexity for the liquid krypton storage and supply system. Due to the high internal pressure of liquid storage tanks, containers are typically spherical or cylindrical rotating structures, suitable for irregular spaces, and do not meet structural requirements.

[0004] Cryogenic solid krypton storage offers advantages such as high storage density, small volume, and suitability for irregularly shaped storage tank structures. Liquid krypton has a temperature of 120 K and a gas phase pressure of 101.3 kPa, while solid krypton has a temperature of 115.78 K and a gas phase pressure of 73.53 kPa. The temperature difference is relatively small, and the gas phase pressure of solid krypton can directly meet the gas supply pressure requirements. Compared to cryogenic liquid storage, the power consumption of the active cooling system is similar when using solid storage. Electric propulsion propellants require a gaseous state, and the temperature difference between solid krypton and its liquid / gas transition is small, resulting in lower vaporization power consumption. However, solid krypton storage and vaporization require simultaneously addressing both cooling and heating issues. Achieving stable storage of solid krypton propellants and ensuring adequate gas exhaust supply during vaporization has become a major problem affecting the application of solid krypton propellants in satellites. Summary of the Invention

[0005] This application provides a satellite propellant solid storage and partitioned phase change supply device and its manufacturing method, which solves the problems of large-capacity krypton propellant storage, large volume and weight, complex management system, and difficulty in adapting to irregular space layout, and achieves the technical goals of satellite propellant solid storage, efficient gasification, and gas supply.

[0006] To achieve the above objectives, this application provides a satellite propellant solid-state storage and zoned phase change supply device, including a tank shell, a tank cover, a heat exchange assembly, a tank liquid inlet, a tank gas inlet, a refrigerator interface, an electrical connector, and a flow meter. The tank shell and tank cover are sealed together to form a closed propellant storage space. The heat exchange assembly is located inside the tank shell and is used to realize solid-state storage and zoned controllable phase change supply of the propellant. The tank liquid inlet and tank gas inlet are respectively located on the tank cover and are used for propellant filling and gaseous propellant output, respectively. The refrigerator interface is located on the tank shell and is used to connect to an external refrigerator. The electrical connector is located on the tank shell and is used to connect to an external power supply and controller. The flow meter is connected to the tank gas inlet and is used to monitor the flow rate of the output gaseous propellant.

[0007] Furthermore, the tank shell, tank cover, tank liquid inlet, and tank gas inlet are all made of titanium alloy; the tank shell is cylindrical, spherical, annular, conical, or irregularly shaped, with a height ≥ 0.3m and a cross-sectional area ≥ 0.3m². 2 Both the liquid inlet and the gas inlet of the storage tank adopt an M5 ball-cone metal sealing structure.

[0008] Furthermore, the heat exchange assembly includes a three-dimensional mesh cold plate, a membrane heater, a heater mounting bracket, temperature sensors, and pressure sensors. Specifically: the three-dimensional mesh cold plate is divided into three layers along its height, each layer further divided into eight regions, forming 24 independent heat exchange units of similar volume; 24 membrane heaters are evenly distributed on the top of each heat exchange unit, and are fixed to the three-dimensional mesh cold plate by bonding and riveting with the heater mounting bracket; there are 48 temperature sensors, with two installed in each heat exchange unit, one mounted on the three-dimensional mesh cold plate to monitor the cold plate temperature, and the other mounted on the membrane heater to monitor the heating temperature; and four pressure sensors are located in the upper space inside the tank shell or near the tank's vent to monitor the internal pressure of the tank.

[0009] Furthermore, the three-dimensional mesh-like cold plate is made of copper alloy; the membrane heater uses a polyimide film heating belt with a power density ≥0.3W / cm² and a heating area ≥0.003m². 2 Heating temperature ≤358K.

[0010] Furthermore, the heater mounting bracket is made of glass fiber epoxy resin composite material, with a thermal conductivity ≤0.3W / (m·K), strength ≥300Mpa, and elastic modulus ≥30Gpa.

[0011] Furthermore, the temperature sensor has a temperature measurement range of 70K to 400K, a resolution of <0.01K, and a response time of <1.5s.

[0012] Furthermore, the pressure sensor has a measurement range of 0-0.2 MPa and 0-3 MPa, a power supply voltage of 12V±1V, and a power consumption of 0.5W.

[0013] Furthermore, the refrigeration unit interface is made of copper alloy material and is welded to the tank shell wall plate through a copper-titanium transition metal; the outer flange of the refrigeration unit interface has a diameter of 60mm and a thickness of 8mm, and is fixed to the refrigeration unit cold head with 8 M5 bolts.

[0014] Furthermore, the flow meter is connected to the gas inlet of the storage tank via a Φ6mm bellows; the flow meter has a measurement range of 0 to 1mg and a medium temperature range of 120K to 373K.

[0015] In addition, this application also provides a method for manufacturing a satellite propellant solid storage and partitioned phase change supply device, comprising the following steps: Step 1: The tank shell, tank cover, tank liquid inlet, and tank gas inlet are machined using titanium alloy materials; Step 2: Use copper alloy material to process a three-dimensional mesh-like cold plate and a refrigeration unit interface; Step 3: Weld the tank shell to the refrigeration unit interface, and weld the tank cover to the tank liquid port and tank gas port; Step 4: Install the membrane heater, heater holder, temperature sensor, and pressure sensor onto the three-dimensional grid-like cold plate to complete the manufacturing of the heat exchange assembly; Step 5: Assemble the heat exchange components into the tank shell, complete the welding of the temperature sensor, pressure sensor and electrical connector, and assemble and weld the tank shell and tank cover plate. Step 6: Connect the flow meter to the gas inlet of the storage tank using a bellows screw connection.

[0016] The satellite propellant solid storage and partitioned phase change supply device and its manufacturing method provided in this application have the following beneficial effects: 1. This application uses solid working fluid storage, which has low storage pressure and is suitable for tank structure design with irregular spatial layout. It enhances the flexibility of satellite propulsion system structure and layout design, increases the duty cycle of working fluid tank, and provides additional space for satellite payload configuration. 2. This application adopts an active refrigeration system with a cooling structure. The three-dimensional grid-like cold plate plays a dual role in structural reinforcement and efficient cooling, thereby improving the structural strength, rigidity and stability of the storage tank. 3. This application adopts a layered and segmented low-temperature storage and heating gasification technology solution. The overall storage capacity is divided into 24 independent heat exchange units with similar volumes, and independent zone heating circuits are set up. This realizes sequential heating and gasification in a top-down, layer-by-layer and block-by-block manner, which reduces the main cooling power consumption and has high energy utilization efficiency. 4. This application achieves comprehensive monitoring of the cryogenic storage and gas supply heat exchange status of solid krypton in 24 independent heat exchange units through multi-parameter monitoring and control, providing a good guarantee for the operation of the cryogenic solid krypton storage and supply system. Attached Figure Description

[0017] 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 a satellite propellant solid storage and partitioned phase change supply device according to an embodiment of this application; Figure 2 This is a schematic diagram of the internal structure of a satellite propellant solid storage and partitioned phase change supply device according to an embodiment of this application; Figure 3 This is a schematic diagram of a heat exchange component provided according to an embodiment of this application; In the figure: 1-tank shell, 2-tank cover, 3-heat exchange assembly, 31-three-dimensional mesh cold plate, 32-film heater, 33-heater bracket, 34-temperature sensor, 35-pressure sensor, 4-tank liquid port, 5-tank gas port, 6-refrigeration unit interface, 7-electrical connector, 8-flow meter. Detailed Implementation

[0018] 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.

[0019] 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.

[0020] 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.

[0021] 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.

[0022] In addition, the term "multiple" should mean two or more.

[0023] 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.

[0024] like Figure 1-2As shown, this application provides a satellite propellant solid-state storage and zoned phase change supply device, including a tank shell 1, a tank cover 2, a heat exchange assembly 3, a tank liquid inlet 4, a tank gas inlet 5, a refrigerator interface 6, an electrical connector 7, and a flow meter 8. The tank shell 1 and tank cover 2 are sealed together to form a closed propellant storage space. The heat exchange assembly 3 is disposed inside the tank shell 1 to realize solid-state storage and zoned controllable phase change supply of the propellant. The tank liquid inlet 4 and tank gas inlet 5 are respectively disposed on the tank cover 2 for propellant filling and gaseous propellant output. The refrigerator interface 6 is disposed on the tank shell 1 for connection to an external refrigerator to achieve active cooling. The electrical connector 7 is disposed on the tank shell 1 for connection to an external power supply and controller. The electrical connector 7 connects to a multi-channel secondary power supply to achieve sequential heating and vaporization in different zones and levels. The flow meter 8 is connected to the tank gas inlet 5 to monitor the flow rate of the output gaseous propellant.

[0025] Specifically, the satellite propellant solid-state storage and zoned phase change supply device provided in this application embodiment achieves the functional requirements of stable solid-state cryogenic storage and sequential heating and vaporization in a top-down, layer-by-layer, and block-by-block manner. Compared to high-pressure gaseous storage (density 1110 kg / m³), this device achieves significantly better performance. 3 The solid storage density reaches 2830 kg / m³. 3 The volume is reduced by approximately 60.78%; compared to titanium alloy high-pressure gas cylinders, the thin-walled cryogenic storage tank is about 73% lighter, freeing up valuable weight and volume space for other payloads on the satellite platform.

[0026] Furthermore, the tank shell 1, tank cover 2, tank liquid inlet 4, and tank gas inlet 5 are all made of titanium alloy. Titanium alloy has the advantages of high specific strength, good low-temperature toughness, and good compatibility with the working fluid. The tank shell 1 has a cylindrical, spherical, annular, conical, or irregular shape to adapt to the irregular spatial layout inside the satellite cabin. Its height is ≥0.3m, preferably 0.96m, and its cross-sectional area is ≥0.3m². 2 Preferably 2m 2 Both the liquid inlet 4 and the gas inlet 5 of the storage tank adopt an M5 ball-cone metal sealing structure to ensure a leak-free seal under low temperature and high pressure.

[0027] Furthermore, such as Figure 3As shown, the heat exchange assembly 3 includes a three-dimensional mesh-like cold plate 31, a membrane heater 32, a heater mounting bracket 33, a temperature sensor 34, and a pressure sensor 35. Specifically: the three-dimensional mesh-like cold plate 31 is divided into three layers along its height, each layer comprising eight regions, forming 24 independent heat exchange units of similar volume; the membrane heaters 32 are evenly distributed on the top of each heat exchange unit, totaling 24, and are fixed to the three-dimensional mesh-like cold plate 31 by bonding and riveting with the heater mounting bracket 33; the number of temperature sensors 34 is 48, with two installed in each heat exchange unit, one on the three-dimensional mesh-like cold plate 31 for monitoring the cold plate temperature, and the other on the membrane heater 32 for monitoring the heating temperature; the number of pressure sensors 35 is 4, located in the upper space inside the tank shell 1 or near the tank vent 5, for monitoring the internal pressure of the tank.

[0028] Furthermore, the three-dimensional mesh-like cold plate 31 is made of copper alloy; the membrane heater 32 uses a polyimide film heating belt with a power density ≥0.3W / cm² and a heating area ≥0.003m². 2 Heating temperature ≤358K.

[0029] Specifically, the three-dimensional mesh-like cold plate 31 is made of copper alloy, which has extremely high thermal conductivity, enabling it to quickly and evenly transfer the cooling energy provided by the refrigeration unit's cold head to the entire cold plate. The three-dimensional mesh-like cold plate 31 is divided into three layers along its height, each layer further divided into eight regions, forming 24 independent heat exchange units of similar volume. This crisscrossing three-dimensional mesh structure has a dual function: firstly, it serves as a cooling path, evenly distributing the cooling energy among the heat exchange units, overcoming the problems of large temperature gradients and uneven cooling caused by the low thermal conductivity of solid krypton; secondly, it acts as a structural reinforcement, improving the strength, rigidity, and resistance to instability of the tank shell 1. The membrane heaters 32 use polyimide film heating strips, numbering 24, evenly distributed on the top of each heat exchange unit. The power density of the membrane heaters 32 is preferably 0.5 W / cm², the heating area is preferably 0.006 m², and the heating temperature does not exceed 358 K. Polyimide film heating belts have the advantages of low temperature resistance, thin thickness, uniform heating and fast response; each heat exchange unit is independently controlled for heating, which can realize sequential vaporization "from top to bottom, layer by layer and block by block", avoiding the vaporization chaos and additional cooling power consumption caused by simultaneous melting of large areas.

[0030] Furthermore, the heater mounting bracket 33 is made of glass fiber epoxy resin composite material, with a thermal conductivity ≤0.3W / (m·K), strength ≥300Mpa, and elastic modulus ≥30Gpa.

[0031] Specifically, the heater mounting bracket 33 is made of glass fiber epoxy resin composite material, which preferably has a thermal conductivity of 0.27 W / (m·K), a strength of 380 MPa, and an elastic modulus of 40 GPa. The heater mounting bracket 33 is bonded to the membrane heater 32 and the three-dimensional mesh cold plate 31 and then riveted to achieve physical isolation between the heat conduction (three-dimensional mesh cold plate 31) and the heat exchange (membrane heater 32), preventing the heat from the heater from being directly transferred to the cold plate and causing a loss of cooling capacity.

[0032] Furthermore, the temperature sensor 34 has a temperature measurement range of 70K to 400K, a resolution of <0.01K, and a response time of <1.5s.

[0033] Specifically, there are 48 temperature sensors 34, with two installed in each heat exchange unit. One temperature sensor 34 is mounted on the three-dimensional mesh-like cold plate 31 to monitor the temperature of the cold plate, and the other is mounted on the membrane heater 32 to monitor the temperature of the heating belt. The temperature sensors 34 have a temperature measurement range of 70K to 400K, an accuracy better than ±0.1K, a resolution less than 0.01K, a response time less than 1.5s, short-term stability better than 1mK, repeatability better than ±10mK, a volume less than 140mm³, and a weight less than 3g, preferably 2.3g. These high-precision sensors can provide real-time feedback on the cold and hot end temperatures of each heat exchange unit, providing accurate data for zoned heating sequence control.

[0034] Furthermore, the pressure sensor 35 has a measurement range of 0-0.2 MPa and 0-3 MPa, a power supply voltage of 12V±1V, and a power consumption of 0.5W.

[0035] Specifically, there are four pressure sensors 35, located in the upper space inside the tank housing 1 or near the tank gas inlet 5, including two with a measurement range of 0-0.2 MPa and two with a measurement range of 0-3 MPa. The 0-0.2 MPa sensor is used to accurately monitor the low-pressure range (initial gas supply), and the 0-3 MPa sensor is used to monitor the high-pressure range (refueling or abnormal operating conditions). The accuracy of the pressure sensor 35 is better than ±1.0%FS, the thermal zero-point drift is better than ±0.1%FS / K, the power supply voltage is 12V±1V, the power consumption is 0.5W, the sensor output is 0.2~5V, and the helium leakage rate at 0.2 MPa is less than 1×10⁻⁶. -7 Pa·m³ / s.

[0036] Furthermore, the refrigeration unit interface 6 is made of copper alloy material and is welded to the wall plate of the storage tank shell 1 through a copper-titanium transition metal; the outer flange of the refrigeration unit interface 6 has a diameter of 60mm and a thickness of 8mm, and is connected and fixed to the refrigeration unit cold head with 8 M5 bolts to ensure good thermal contact and mechanical reliability.

[0037] Furthermore, the flow meter 8 is connected to the gas inlet 5 of the storage tank via a Φ6mm bellows, which can compensate for assembly errors and thermal deformation. The flow meter 8 has a measurement range of 0 to 1 mg, a medium temperature range of 120 K to 373 K, and an accuracy better than ±1%. The flow meter 8 monitors the gas supply flow in real time and feeds it back to the controller to adjust the heating power, thus achieving closed-loop control.

[0038] In addition, this application also provides a method for manufacturing a satellite propellant solid storage and partitioned phase change supply device, comprising the following steps: Step 1: The tank shell 1, tank cover 2, tank liquid inlet 4, and tank air inlet 5 are machined using titanium alloy materials; after machining, the sealing surfaces are precision ground to ensure the roughness requirements of the M5 ball-cone seal.

[0039] Step 2: The three-dimensional mesh-shaped cold plate 31 and the refrigeration unit interface 6 are processed using copper alloy material; the three-dimensional mesh-shaped cold plate 31 is processed by CNC machining or wire EDM to ensure the mesh size accuracy and position accuracy.

[0040] Step 3: Weld the tank shell 1 to the refrigeration unit interface 6, and weld the tank cover 2 to the tank liquid port 4 and the tank gas port 5. Since titanium alloy and copper alloy cannot be directly welded, a copper-titanium transition ring is used as an intermediate medium. It is first welded to the titanium alloy shell and then to the copper alloy interface. All welding is carried out under vacuum or high-purity argon protection to prevent oxidation.

[0041] Step 4: Install the membrane heater 32, heater bracket 33, temperature sensor 34 and pressure sensor 35 on the three-dimensional grid-like cold plate 31 to complete the manufacturing of the heat exchange component 3; Specifically, the membrane heater 32 is first bonded to the top of each heat exchange unit of the three-dimensional grid-shaped cold plate 31, and then the heater fixing frame 33 is covered and bonded with epoxy resin adhesive. The rivet points are then reinforced. The temperature sensor 34 is pasted in the designated position (on the surface of the cold plate and the surface of the heater), and the pressure sensor 35 is installed on the bracket in the upper space inside the tank.

[0042] Step 5: Assemble the heat exchange component 3 into the tank shell 1, complete the welding of the temperature sensor 34, pressure sensor 35 and electrical connector 7, and assemble and weld the tank shell 1 and tank cover plate 2; use electron beam welding or laser welding to ensure the airtightness of the weld.

[0043] Step 6: Connect the flow meter 8 to the gas inlet 5 of the storage tank using a bellows screw connection. After installation, conduct an airtightness test; the external leakage rate should be less than 1×10⁻⁶ under a helium pressure of 0.2 MPa. -7 Pa·m³ / s.

[0044] Specifically, through the aforementioned manufacturing method, a highly reliable and energy-efficient satellite propellant solid-state storage and zoned phase-change supply device was obtained. During operation, the device first cools the three-dimensional grid-like cold plate 31 to approximately 115K using a refrigerator, causing the krypton propellant in the storage tank to solidify. When gas supply is required, the controller, based on pressure and temperature signals, sequentially energizes the membrane heaters 32 of specific heat exchange units in a top-to-bottom, layer-by-layer, block-by-block manner, melting and vaporizing the solid krypton within that unit. The gaseous krypton is then supplied to the electric propulsion engine via the storage tank port 5 and flow meter 8. Since only one or a few units are heated at a time, the heating power consumption is low, and the pressure of the vaporized gas is stable, directly meeting the engine inlet pressure requirements without the need for additional pressure regulation. Simultaneously, through comprehensive multi-parameter monitoring, long-term stable storage of the solid propellant and efficient on-demand gas supply are achieved.

[0045] 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 satellite propellant solid-state storage and zoned phase-change supply device, characterized in that, This includes the tank shell, tank cover, heat exchange components, tank liquid inlet, tank gas inlet, refrigeration unit interface, electrical connector, and flow meter, among which: The tank shell and the tank cover are sealed together to form a closed working fluid storage space; The heat exchange assembly is located inside the tank shell and is used to realize solid-state storage of the working fluid and zoned controllable phase change supply. The liquid inlet and the gas inlet of the storage tank are respectively provided on the storage tank cover plate for the addition of working fluid and the output of gaseous working fluid; The refrigeration unit interface is located on the storage tank shell and is used to connect to an external refrigeration unit; The electrical connector is mounted on the tank housing and is used to connect to an external power source and controller. The flow meter is connected to the gas port of the storage tank and is used to monitor the flow rate of the output gaseous working fluid.

2. The satellite propellant solid storage and zoned phase change supply device according to claim 1, characterized in that, The tank shell, tank cover, tank liquid inlet, and tank gas inlet are all made of titanium alloy. The tank shell is cylindrical, spherical, annular, conical, or irregularly shaped, with a height ≥ 0.3m and a cross-sectional area ≥ 0.3m². 2 Both the liquid inlet and the gas inlet of the storage tank adopt an M5 ball-cone metal sealing structure.

3. The satellite propellant solid storage and zoned phase change supply device according to claim 1, characterized in that, The heat exchange assembly includes a three-dimensional mesh-like cold plate, a membrane heater, a heater mounting bracket, a temperature sensor, and a pressure sensor, wherein: The three-dimensional grid-like cold plate is divided into three layers along the height direction, each layer is divided into 8 regions, forming 24 independent heat exchange units of similar volume; The membrane heaters are evenly distributed on the top of each heat exchange unit, with a total of 24 heaters. They are fixed by bonding and riveting to the three-dimensional mesh cold plate through the heater fixing frame. The number of temperature sensors is 48, with two installed in each heat exchange unit. One sensor is installed on the three-dimensional mesh cold plate to monitor the cold plate temperature, and the other sensor is installed on the membrane heater to monitor the heating temperature. The number of pressure sensors is four, which are installed in the upper space inside the tank shell or near the tank vent, for monitoring the internal pressure of the tank.

4. The satellite propellant solid storage and zoned phase change supply device according to claim 3, characterized in that, The three-dimensional mesh-like cold plate is made of copper alloy; the membrane heater uses a polyimide film heating belt with a power density ≥0.3W / cm² and a heating area ≥0.003m². 2 Heating temperature ≤358K.

5. The satellite propellant solid storage and zoned phase change supply device according to claim 3, characterized in that, The heater mounting bracket is made of glass fiber epoxy resin composite material with a thermal conductivity ≤0.3W / (m·K), strength ≥300Mpa, and elastic modulus ≥30Gpa.

6. The satellite propellant solid storage and zoned phase change supply device according to claim 3, characterized in that, The temperature sensor has a temperature measurement range of 70K to 400K, a resolution of <0.01K, and a response time of <1.5s.

7. The satellite propellant solid storage and zoned phase change supply device according to claim 3, characterized in that, The pressure sensor has a measurement range of 0-0.2 MPa and 0-3 MPa, a power supply voltage of 12V±1V, and a power consumption of 0.5W.

8. The satellite propellant solid storage and zoned phase change supply device according to claim 1, characterized in that, The refrigeration unit interface is made of copper alloy material and is welded to the wall plate of the storage tank shell through a copper-titanium transition metal; the outer flange of the refrigeration unit interface has a diameter of 60mm and a thickness of 8mm, and is connected and fixed to the refrigeration unit cold head with 8 M5 bolts.

9. The satellite propellant solid storage and zoned phase change supply device according to claim 1, characterized in that, The flow meter is connected to the gas inlet of the storage tank via a Φ6mm bellows; the flow meter has a measurement range of 0 to 1mg and a medium temperature range of 120K to 373K.

10. A method for manufacturing a satellite propellant solid-state storage and partitioned phase-change supply device according to any one of claims 1-9, characterized in that, Includes the following steps: Step 1: The tank shell, tank cover, tank liquid inlet, and tank gas inlet are machined using titanium alloy materials; Step 2: Use copper alloy material to process a three-dimensional mesh-like cold plate and a refrigeration unit interface; Step 3: Weld the tank shell to the refrigeration unit interface, and weld the tank cover to the tank liquid port and tank gas port; Step 4: Install the membrane heater, heater holder, temperature sensor, and pressure sensor onto the three-dimensional grid-like cold plate to complete the manufacturing of the heat exchange assembly; Step 5: Assemble the heat exchange components into the tank shell, complete the welding of the temperature sensor, pressure sensor and electrical connector, and assemble and weld the tank shell and tank cover plate. Step 6: Connect the flow meter to the gas inlet of the storage tank using a bellows screw connection.

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