Electric propulsion working medium on-orbit high-density storage and supply device and method

Abstract

The invention relates to an electric propulsion working medium on-orbit high-density storage and supply device and method, belongs to the technical field of spacecraft deep space exploration and on-orbit service, and can effectively save space resources and quality resources of spacecrafts. A storage box, a refrigerator, a pump and an injection pipe are connected in sequence; the storage box, the heating evaporator and the third electromagnetic valve are circularly connected; the storage tank, the gasifier and the buffer cavity are connected in sequence. According to the invention, the complexity of the propulsion system is simplified, the potential fault risk is reduced, the application of a novel electric propulsion technology with high power, high specific impulse and long service life is effectively supported, and important support is provided for the development of tasks such as deep space exploration and on-orbit service.

Description

Technical Field

[0001] The present invention relates to an on-orbit high-density storage and supply device and method for electric propulsion working fluid, belonging to the technical field of deep space exploration and on-orbit service of spacecraft. Background Art

[0002] To meet the demands of missions such as deep space exploration and in-orbit space servicing, spacecraft propulsion systems must possess the following characteristics: high propulsion efficiency and high specific impulse to increase payload mass; large velocity increments and high thrust to shorten mission cycles; and long life to support repeated transfers between different orbits. To meet these new mission requirements, high-power electric propulsion systems in the 100-kilowatt class, represented by nuclear propulsion, with their high specific impulse, high thrust, and long life, can effectively extend the service life of spacecraft, reduce launch costs, and meet the requirements of high-maneuverability missions, thereby comprehensively improving the functional performance of propulsion systems and expanding their application scenarios. The publication number is CN104075104B, and the invention is named as a method for hot pressurized xenon filling of satellite electric propulsion system. The publication number is CN104075105B, and the invention is named as a hot pressurized xenon filling system for satellite electric propulsion system. Its technical solution discloses that the purity, pressure, temperature and filling amount of xenon filling process meet the required requirements. The focus is on solving the problems of xenon purity and temperature control to ensure the safety of filling test. It does not directly involve the high-density storage and management of electric propulsion working fluid on orbit; the publication number is CN214663682U, and the invention is named as a xenon filling system for satellite electric propulsion system, in which the xenon transfer device uses liquid Nitrogen is used to cool and heat xenon gas, allowing it to be stored and transferred in different states. Other cooling media are required for cooling. In aerospace, a field with strict requirements and severe restrictions on space design, this cooling method is not suitable for on-orbit use. The existing demand for large-thrust, high-total-impulse propulsion systems means that more propellant needs to be carried. The space resources and mass resources of spacecraft are very precious. Therefore, the original electric propulsion xenon, krypton, and argon working fluids in gaseous or supercritical states can no longer meet mission requirements due to low storage density and the need to be equipped with large-volume pressure vessels. Therefore, how to achieve high-density storage and management technology of electric propulsion working fluids on orbit is a difficult problem that must be solved to further improve the level of space propulsion technology.

[0003] Therefore, it is urgent to propose an on-orbit high-density storage and supply device and method for electric propulsion working fluid to solve the above technical problems. Summary of the Invention

[0004] To address the complexities of propulsion systems, a device and method for high-density on-orbit storage and supply of electric propulsion fluid is provided. The following provides a brief overview of the invention to provide a basic understanding of certain aspects of the invention. It should be understood that this overview is not an exhaustive overview of the invention. It is not intended to identify key or important aspects of the invention, nor is it intended to limit the scope of the invention.

[0005] The technical solution of the present invention: An on-orbit high-density storage and supply device for electric propulsion working fluid, comprising a refrigeration circuit comprising a storage tank, a refrigerator, a pump, and an injection pipe connected in a sequential loop, wherein the injection pipe of the refrigeration circuit is disposed within the storage tank; Booster circuit: storage tank, heating evaporator, and third solenoid valve are connected in a circular manner; Gaseous working medium circuit: storage tank, vaporizer, and buffer tank are connected in sequence.

[0006] Preferably, one opening of the four-way pipe is connected to the output end of the storage tank, and the other three openings of the four-way pipe are connected to the input ends of the refrigerator, the heating evaporator, and the vaporizer respectively.

[0007] Preferably, the injection pipe is provided with a plurality of evenly arranged working medium outlet holes.

[0008] Preferably, the output end of the heating evaporator of the boosting circuit is connected to the input end of the tank via a second conduit, and a third solenoid valve is provided on the second conduit.

[0009] Preferably, the gaseous working medium circuit is provided with a first solenoid valve, which is provided on a four-way pipe, an output end of the first solenoid valve is connected to an input end of the vaporizer, and a first safety valve is provided on the pipeline between the input end of the first solenoid valve and the four-way pipe; A second solenoid valve and a second safety valve are provided on the pipeline between the input end of the buffer tank and the gasifier, and the buffer tank is provided with a second temperature sensor and a second pressure sensor.

[0010] Preferably, the number of buffer tanks is two or more.

[0011] Preferably, the first solenoid valve and the first safety valve of the gaseous working medium circuit are connected to the four-way pipe through a first flange, and the second safety valve and the buffer tank are connected to the second solenoid valve through a third flange.

[0012] Preferably, the outer side of the tank is wrapped with a heat insulation layer, and the tank is provided with a second flange for connecting with the satellite structure.

[0013] Preferably, the storage tank is provided with a first pressure sensor and a first temperature sensor.

[0014] A method for high-density storage and supply of an electric propulsion working fluid on-orbit is provided, using a high-density storage and supply device for an electric propulsion working fluid on-orbit, comprising the following steps: Working fluid storage: The tank contains working fluid. When the temperature does not meet the set value or the pressure is too high, the refrigeration circuit is activated, and the liquid working fluid in the tank is cooled and transported to the tank. When the propellant is transported out of the tank, the boosting circuit is activated, and the liquid working fluid in the tank is vaporized and transported to the buffer tank. Working fluid delivery: deliver working fluid to the buffer tank until the pressure in the buffer tank meets the set value.

[0015] The present invention has the following beneficial effects: The present invention is applied in the field of aerospace, and is designed with space and weight as key factors. It solves the problem that traditional electric propulsion working fluids such as xenon, krypton, and argon are stored in gas cylinders in a gaseous or supercritical state, which leads to excessive pressure, complex pressure vessel structure, and requires higher strength, and has low density and small storage capacity compared to liquid storage. The liquid propellant storage of the present invention can significantly increase the propellant carrying capacity, utilize the medium in the tank for circulating pressure and temperature regulation, save space, significantly reduce the volume of the storage tank, improve mission feasibility, meet higher requirements for propellant carrying capacity and storage density, and can achieve high-density storage and efficient supply of working fluids such as xenon, krypton, and argon for electric propulsion, and has broad application prospects.

[0016] The present invention simplifies the complexity of the propulsion system and reduces the risk of potential failures. It can be applied to multiple links such as spacecraft thermal control, liquid propellant microgravity management, and liquid propellant vaporization and evaporation, providing important support for the implementation of deep space exploration, on-orbit services and other tasks.

[0017] Based on the physical properties of electric propulsion fluids such as xenon, krypton, and argon, and according to the changes in fluid density with temperature, the present invention combines multiple factors such as space, weight, and environment to design a solution for achieving high-density storage of working fluids through on-orbit low-temperature storage, effectively increasing the amount of working fluid carried on-orbit and adapting to on-orbit use. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is an on-orbit high-density storage and supply device for electric propulsion working fluid; Figure 2 This is a partial diagram of an on-orbit high-density storage and supply device for electric propulsion working fluid; Figure 3 This is the PρT relationship diagram for xenon.

[0019] In the figure, 1-storage tank, 2-injection pipe, 3-first conduit, 4-refrigeration machine, 5-first solenoid valve, 6-first safety valve, 7-vaporizer, 8-second solenoid valve, 9-second safety valve, 10-buffer tank, 11-second temperature sensor, 12-second pressure sensor, 13-third flange, 14-first flange, 15-second flange, 16-insulation layer, 17-satellite structure, 18-pump, 19-heating evaporator, 20-four-way pipe, 21-second conduit, 22-third solenoid valve, 23-working medium outlet, 24-guide plate, 25-liquid accumulator, 26-first pressure sensor, 27-first temperature sensor. DETAILED DESCRIPTION

[0020] To make the objectives, technical solutions, and advantages of the present invention more clearly apparent, the present invention is described below using specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are merely illustrative and are not intended to limit the scope of the present invention. In addition, in the following description, descriptions of well-known structures and technologies are omitted to avoid unnecessary confusion of the concepts of the present invention.

[0021] Specific implementation method 1: Combination Figure 1-2 This embodiment describes an on-orbit high-density storage and supply device for electric propulsion working fluid, including: Refrigeration circuit: The storage tank 1, refrigerator 4, pump 18, and injection pipe 2 are connected in a circular manner to form a refrigeration circuit. The storage tank 1 is a surface tension storage tank for storing the working medium. The pump 18 is a liquid pump. The working medium in the storage tank 1 is cooled by the refrigerator 4 and evenly ejected into the storage tank 1 through the injection pipe 2. The injection pipe 2 is used to reduce the temperature of the working medium in the storage tank 1. The refrigeration circuit further includes a first conduit 3, through which the output end of a pump 18 disposed outside the tank 1 is connected to the input end of an injection pipe 2 disposed inside the tank 1. The present invention increases the amount of portable working fluid within a limited space, thereby minimizing the impact on the spacecraft configuration design. The injection pipe 2 is located at the axis of the tank 1. Several evenly spaced medium outlet holes 23 are machined on the injection pipe 2 as the output end of the injection pipe 2, ensuring uniform mixing and improving cooling efficiency. This invention achieves zero evaporation of the working fluid, greatly extending its service life and meeting a 15-year on-orbit service life. Based on the physical properties of electric propulsion working fluids such as xenon, krypton, and argon, and the change in working fluid density with temperature, this patent designs a solution for achieving high-density storage of working fluids through on-orbit low-temperature storage, effectively increasing the amount of working fluid carried on-orbit. Boosting circuit: The storage tank 1, the heating evaporator 19, and the third solenoid valve 22 are connected in a loop to form a boosting circuit; the working fluid in the storage tank 1 is heated and vaporized by the heating evaporator 19 and then returns to the storage tank 1 for pressure regulation; The boost circuit also includes a second conduit 21, through which the output of the heating evaporator 19 is connected to the input of the tank 1. The heating evaporator heats and vaporizes the liquid working medium, which is then fed into the tank, achieving self-regulation of the tank pressure. The thermal insulation layer separates the second conduit 21 from the tank 1, effectively preventing heat exchange and ensuring the working medium's state in the tank. Gaseous working medium circuit: The storage tank 1, vaporizer 7, and buffer tank 10 are connected in sequence to form a gaseous working medium circuit; the vaporizer 7 is used to vaporize the working medium; the working medium in the storage tank 1 enters the vaporizer 7 for heating and vaporization, and the vaporizer 7 uses a heating evaporator to enter the buffer tank 10 to form a high-pressure working medium; It also includes a four-way pipe 20, one opening of which is connected to the liquid accumulator 25 at the output end of the storage tank 1. Screens are provided at the liquid outlets on the top and side of the liquid accumulator 25. The other three openings of the four-way pipe 20 are respectively connected to the input ends of the refrigerator 4, the heating evaporator 19, and the vaporizer 7. The gaseous working medium circuit also includes a first solenoid valve 5 and a first safety valve 6. The storage tank 1 is connected to the input end of the first solenoid valve 5 through the opening corresponding to the vaporizer of the four-way pipe 20. The output end of the first solenoid valve 5 is connected to the input end of the vaporizer 7. The first safety valve 6 is provided on the pipeline between the input end of the first solenoid valve 5 and the opening corresponding to the vaporizer of the four-way pipe 20. The gaseous working medium circuit also includes a second solenoid valve 8, a second safety valve 9, a second temperature sensor 11, and a second pressure sensor 12. The second solenoid valve 8 and the second safety valve 9 are both connected to the input end of the buffer tank 10, and the second temperature sensor 11 and the second pressure sensor 12 are both connected to the output end of the buffer tank 10. The present invention controls the opening and closing time of the valves and combines temperature and pressure control measures to control the working medium flowing into the buffer gas volume after gasification within a desired pressure range, thereby facilitating downstream pressure and flow management. There are two buffer tanks 10, and the output end of the vaporizer 7 is connected to the input ends of two second electromagnetic valves 8 connected in parallel; this facilitates control and ensures stable flow delivery; The present invention has a simple structure, low cost, and is not easily damaged. It can achieve high-density storage and efficient supply of working fluids such as xenon, krypton, and argon for electric propulsion, and provides a low-temperature, high-density storage tank and management system for electric propulsion working fluids with "zero boil-off" on orbit. This effectively supports the promotion and application of electric propulsion in deep space exploration, on-orbit services, and other fields. The gaseous working medium circuit also includes a third flange 13 and a first flange 14. The first solenoid valve 5 and the first safety valve 6 are connected to the opening corresponding to the vaporizer of the four-way pipe 20 through the first flange 14. The second safety valve 9 and the buffer tank 10 are connected to the second solenoid valve 8 through the third flange 13. The output end of the present invention is the outlet, and the input end is the inlet. It also includes a second flange 15 and a thermal insulation layer 16. The outer side of the tank 1 is wrapped with a thermal insulation layer 16. The thermal insulation layer 16 adopts a foam thermal insulation layer for multi-layer insulation. The tank 1 is detachably connected to the satellite structure 17 through the second flanges 15 arranged on the upper and lower sides, and the flanges are prepared by using thermal insulation materials to achieve thermal insulation. The present invention performs thermal insulation treatment on the tank to isolate the heat conduction inside and outside the tank. It also includes a second flange 15 and a thermal insulation layer 16. The outer side of the tank 1 is wrapped with a thermal insulation layer 16. The thermal insulation layer 16 adopts a foam thermal insulation layer for multi-layer insulation. The tank 1 is detachably connected to the satellite structure 17 through the second flanges 15 arranged on the upper and lower sides, and the flanges are prepared by using thermal insulation materials to achieve thermal insulation. The present invention performs thermal insulation treatment on the tank to isolate the heat conduction inside and outside the tank. Heat conduction inside and outside; the present invention increases the portable working fluid in a limited space and reduces the impact on the spacecraft configuration design; the present invention realizes high-density storage of electric propulsion xenon, krypton and argon working fluids in orbit throughout the entire life cycle; it solves the problem of limited storage capacity due to the use of supercritical or gaseous storage of electric propulsion working fluids; the storage density is low, and the working fluid carrying capacity is increased mainly by increasing the volume of the gas cylinder. The present invention is suitable for high-density storage and supply of electric propulsion xenon, krypton and argon working fluids, realizing independent control of key aerospace resources, providing strong support for the development and application of high-performance propulsion systems for spacecraft, providing strong guarantee for the development of high-performance propulsion systems for space probes, and providing important support for the implementation of major national tasks such as deep space exploration and on-orbit services.

[0022] Specific implementation method 2: Combination Figure 1-3 This embodiment describes a method for high-density storage and supply of an electric propulsion working fluid on-orbit, including: The working fluid storage is achieved through the structure upstream of the vaporizer: the tank 1 contains the working fluid, which can be xenon, krypton or argon. The pressure and temperature in the tank 1 are detected by the first pressure sensor 26 and the first temperature sensor 27. If there is temperature stratification and / or pressure instability, that is, the temperature and pressure do not meet the set values; when the temperature does not meet the set value or the pressure is too high (higher than the set range), the refrigerator 4 and pump 18 of the refrigeration circuit are started, and the other passages are closed. The liquid working fluid in the tank 1 is cooled and transported to the injection pipe 2, and is evenly sprayed into the tank 1 through the working fluid outlet 23 of the injection pipe 2; when the pressure is too low (lower than the set range), the third solenoid valve 22 of the boosting circuit and the heating evaporator 19 are started, and the other passages are closed. The liquid working fluid in the tank 1 is vaporized and transported to the tank 1 through the heating evaporator 19; the present invention is applied to the on-orbit high-density storage and management system of electric propulsion working fluids. Based on the physical properties of electric propulsion working fluids such as xenon, krypton, and argon, the temperature of the on-orbit working fluid storage cylinder is controlled to convert the supercritical working fluid into a liquid or a gas-liquid mixed state or even a solid state, thereby improving the storage density of the working fluid, effectively increasing the carrying capacity of the electric propulsion working fluid, and effectively reducing the operating pressure of the system, simplifying the complexity of the propulsion system and reducing the risk of potential failures. The present invention can be applied to multiple links such as spacecraft thermal control, liquid propellant microgravity management, and liquid propellant vaporization and evaporation, providing important support for the implementation of deep space exploration, on-orbit service and other missions; The working medium is transported. The end downstream of the vaporizer is connected to the electric thruster through a pneumatic or electromagnetic valve to transport the gaseous working medium to the electric thruster: the tank 1 contains the working medium, which can be xenon, krypton or argon. The pressure and temperature in the tank 1 are detected by the first pressure sensor 26 and the first temperature sensor 27 to meet the requirements for working medium storage. If they do not meet the requirements, the working medium storage step is adjusted to meet the set value, and the working medium is transported to the downstream of the evaporator; when transporting the gaseous working medium to the downstream of the evaporator, the refrigeration circuit and the boost circuit are closed, the second electromagnetic valve 8 is started, and then the first electromagnetic valve 27 is started. A solenoid valve 5 detects the pressure of the buffer tank 10 through a second pressure sensor 12 until it meets the set value, then closes the second solenoid valve 8 and the first solenoid valve 5. If the set value is not met, the second solenoid valve 8 and the first solenoid valve 5 are restarted. The buffer tank 10 is detected by a second temperature sensor 11. If the pressure is too low, the heating device is activated until the set value is met. When the valve at the end is opened for supply, if the pressure is lower than the set value, the valve at the end is closed to stop the gas supply, and the second solenoid valve 8 and the first solenoid valve 5 are restarted, thus realizing high-density storage and management of electric propulsion working fluid on orbit. The high-density storage and supply method for electric propulsion system working fluid proposed in the present invention is based on the physical properties of electric propulsion working fluids such as xenon, krypton, and argon. In combination with multiple factors such as space, weight, and environment, a scheme for achieving high-density storage of working fluids through on-orbit low-temperature storage is designed, which effectively increases the on-orbit working fluid carrying capacity. It is a domestic first and is highly innovative. It is suitable for on-orbit high-density storage and supply of xenon, krypton, and argon working fluids in spacecraft electric propulsion systems. By controlling the temperature of the on-orbit working fluid storage cylinders, the supercritical working fluid is converted into liquid or gas-liquid mixed state or even solid state, thereby increasing the storage density of the working fluid and effectively increasing the carrying capacity of the electric propulsion working fluid. It can also effectively reduce the system working pressure, simplify the complexity of the propulsion system, and reduce the risk of potential failures, providing support for the implementation of deep space exploration, on-orbit services and other tasks.

[0023] Example 1: Combine Figure 1-Figure 3 As shown: An on-orbit high-density storage and supply device for electric propulsion working fluid is used, comprising: Refrigeration circuit: storage tank 1, refrigerator 4, pump 18, injection pipe 2 are connected in a circular sequence; The refrigeration circuit's injection pipe 2 is located inside the tank 1 and is provided with a number of evenly spaced fluid outlet holes 23, providing uniform cooling. Through the active and passive refrigeration systems, zero evaporation of the fluid is achieved, ensuring a 15-year on-orbit service life. Booster circuit: storage tank 1 and heating evaporator 19 are connected in a circular manner; The output end of the heating evaporator 19 of the boosting circuit is connected to the input end of the tank 1 through a second conduit 21. A third solenoid valve 22 is provided on the second conduit 21. This realizes a self-regulating pressure system that heats and vaporizes the liquid working medium flowing out of the tank, and then flows the vaporized working medium back into the tank to boost the tank pressure. Gaseous working medium circuit: storage tank 1, vaporizer 7, and buffer tank 10 are connected in sequence; The input end of the first solenoid valve 5 of the gaseous working medium circuit is connected to the tank 1 through the four-way pipe 20, and the output end of the first solenoid valve 5 is connected to the input end of the vaporizer 7. A first safety valve 6 is provided between the input end of the first solenoid valve 5 and the four-way pipe 20; The second solenoid valve 8 and the second safety valve 9 are sequentially arranged along the working medium flow direction on the pipeline between the input end of the buffer tank 10 and the gasifier 7. The second temperature sensor 11 and the second pressure sensor 12 are arranged at the output end of the buffer tank 10. The buffer tank 10 is There are two buffer tanks 10 , the output end of the buffer tank 10 is provided with a solenoid valve, and the outside of the buffer tank 10 is provided with a heating device; The first solenoid valve 5 and the first safety valve 6 of the gaseous working medium circuit are connected to the cross-piece 20 through the first flange 14, and the second safety valve 9 and the buffer tank 10 are connected to the second solenoid valve 8 through the third flange 13; The outer side of the tank 1 is wrapped with a heat-insulating layer 16, and the tank 1 is detachably connected to the satellite structure 17 via second flanges 15 arranged on the upper and lower sides; Tank 1 is provided with a first pressure sensor 26 and a first temperature sensor 27. The output and input of tank 1 are located on different sides, such as at the upper and lower ends of tank 1, respectively, or at the bottom of tank 1 and the input of tank 1 on the side of tank 1. The tank contains a propellant management device (PMD) that can effectively manage propellant in microgravity and ensure that the working fluid discharged from the tank is liquid. The opening section of the injection pipe 2 is set in the tank 1. The outer side of the injection pipe 2 is provided with a circumferentially evenly arranged guide plate 24. The injection pipe 2 is machined with a number of working fluid outlet holes 23. The working fluid is stored in the tank 1. The tank contains a propellant management device (PMD), which can achieve effective propellant management in microgravity and ensure that the working fluid discharged from the tank is liquid. The PMD consists of a cylinder structure (central cylinder) and guide plates. The central cylinder serves as a structural support and is evenly distributed with injection holes. Under the action of the refrigerator and pump, the refrigerated working fluid is injected into various parts of the tank. The device further comprises: Tank 1 and heating evaporator 19 are connected in a sequential loop to form a pressurization circuit. The working fluid in tank 1 is heated and vaporized by heating evaporator 19 and then returns to tank 1 for pressure regulation. Taking advantage of the low boiling points and easy vaporization characteristics of commonly used working fluids for electric propulsion, such as xenon (boiling point -108.1°C), krypton (boiling point -153.35°C), and argon (boiling point -185.3°C), a pressure self-regulating system is designed to adjust the tank operating pressure to meet working fluid supply requirements. Specifically, the low boiling point physical properties of electric propulsion working fluids such as xenon, krypton, and argon are utilized in conjunction with a vaporizer to vaporize the outflowing liquid working fluid before returning to the tank, achieving self-regulation of the tank pressure and further simplifying system complexity. The storage tank 1, refrigerator 4, pump 18, and injection pipe 2 are connected in a circular manner to form a refrigeration circuit. The storage tank 1 is a surface tension storage tank for storing the working medium. The pump 18 is a liquid pump. The working medium in the storage tank 1 is cooled by the refrigerator 4 and is evenly ejected into the storage tank 1 through the injection pipe 2. The injection pipe 2 is used to reduce the temperature of the working medium in the storage tank 1. The present invention is based on the physical properties of electric propulsion fluids such as xenon, krypton, and argon, and according to the change of working fluid density with temperature, designs a scheme for achieving high-density storage of working fluids through on-orbit low-temperature storage, effectively increasing the amount of working fluid carried on orbit. At the same time, the working fluid in the tank 1 is used to enter the boosting circuit and the refrigeration circuit, and the pressure and temperature are controlled by the self-circulation of the working fluid. The working fluid state is adjustable, which not only increases the portable working fluid in a limited space, but also greatly reduces the space occupied by additional equipment such as storage tanks, reduces the impact on the spacecraft configuration design, and realizes the controllable adjustment of the state of the working fluid storage and transportation process. The pressure self-regulation technology designed by the present invention based on the physical properties of the working fluid greatly simplifies the traditional high-pressure gas boosting system, significantly saves space and weight resources of the spacecraft, and improves the feasibility of the mission. The inlet of the tank 1 is located on the upper side or the side as a gas working medium pressurization inlet, and the lower side of the tank 1 has an opening for arranging the injection pipe 2. The structure of the present invention is simple, low-cost, and not easy to damage. The injection pipe 2 is located at the center. The injection pipe 2 is cylindrical with an inner cavity. The inner cavity of the injection pipe 2 is connected to the inner cavity of the tank 1 through a plurality of circumferential openings 23. The lower end of the injection pipe 2 is connected to the pump 18 outside the tank 1 through the first conduit 3. The upper end of the injection pipe 2 is sealed. The hydraulic pressure is concentrated at the opening 23. The working medium is injected over a long distance, further improving the cooling range and achieving uniform and efficient cooling. The injection pipe 2 is machined with a working medium outlet hole 23, and is provided with guide plates 24 evenly arranged in the circumferential direction. The side wall of the injection pipe 2 between adjacent guide plates 24 has a plurality of working medium outlet holes 23 along the axial direction. The injection pipe 2 is connected to the first pipe opening of the cross-tube 20, the second pipe opening of the cross-tube 20 is connected to the refrigerator 4 for supplying working fluid to the refrigeration circuit, the third pipe opening of the cross-tube 20 is connected to the heating evaporator 19 for supplying working fluid to the boost circuit, and the fourth pipe opening of the cross-tube 20 is used to supply working fluid into the gaseous working fluid path; the injection pipe 2 is connected to the pump 18, so that the pump 18 is connected to the annular cavity for spraying low-temperature medium for uniform cooling, with a compact structure and easy installation and maintenance; based on the physical properties of the gas working fluid All substances may present various states such as solid, liquid, gas-liquid mixed state, gaseous state and supercritical state under different pressure P and temperature T combinations, and the corresponding density is a fixed value; Taking xenon as an example, the relationship between its phase change (density) and pressure P and temperature T is as follows: Figure 3 As shown in the figure, when the temperature is higher than 16.6℃, xenon is in a gaseous state. If the pressure is higher than 5.84MPa at the same time, xenon is in a supercritical state. In the supercritical state, the density of xenon behaves like a liquid, but its transport properties behave like a gas. Table 1 summarizes the properties of xenon, krypton, and argon. Similar to the physical properties of xenon, liquid or solid working fluids only appear when the storage temperature is below the critical temperature. Therefore, to achieve high-density storage of working fluids, the storage temperature must first be lowered to below the supercritical temperature of the working fluid. Table 1 Characteristics of xenon, krypton, and argon working fluids

[0024] On this basis, we can select the appropriate cryogenic storage temperature based on the physical properties of different working fluids such as xenon, krypton, and argon, according to factors such as the amount of electric propulsion working fluid carried by the on-orbit spacecraft, the structural envelope requirements of the spacecraft itself, and the on-orbit refrigeration capacity, to achieve high-density storage of working fluids. The corresponding relationships between the saturated vapor pressure, liquid phase density, and gas phase density of xenon, krypton, and argon at different temperatures are shown in Table 2. As the temperature decreases, the saturated vapor pressure of the working fluid decreases and the liquid phase density increases, which means that more electric propulsion working fluid can be stored and carried. Table 2 Density of working fluid at different temperatures

[0025] Cryogenic fluid on-orbit management and supply system hardware Through spacecraft thermal design, high-density storage of xenon, krypton, and argon working fluids for electric propulsion on orbit is achieved throughout the entire life cycle. This involves multiple aspects such as spacecraft thermal control, liquid propellant microgravity management, and liquid propellant vaporization and evaporation. The on-orbit management and supply system for cryogenic fluids primarily consists of a surface tension tank, a thermal control system (refrigerator 4, injection pipe 2), valves, a buffer gas container (buffer tank 10), a heating evaporator (vaporizer 7), and temperature and pressure sensors. Tank 1 requires thermal insulation to isolate heat transfer inside and outside the tank. The valve opening and closing times are controlled to control the mass of liquid propellant flowing into the buffer gas cylinder, and the liquid gas supply is heated and vaporized by the heating evaporator, ultimately providing gaseous fluid for the downstream storage and supply system. Workflow Taking the storage and supply of liquid xenon as an example, the storage and supply process of liquid xenon is as follows: Step 1: The propellant is stored in liquid form in tank 1, which is actively temperature-controlled at -25°C to -20°C and a pressure of approximately 2 to 3 MPa. During storage, the storage tank 1 is refrigerated so that the storage temperature of the working fluid is lower than the critical temperature, and the working fluid is converted into liquid or gas-liquid mixed state or solid state, thereby increasing the storage density of the working fluid and effectively increasing the carrying capacity of the electric propulsion working fluid. It can also effectively reduce the working pressure of the system, simplify the complexity of the propulsion system and reduce the risk of potential failures, providing support for the implementation of tasks such as deep space exploration and on-orbit services; it solves the problem that the current electric propulsion working fluids are all stored in a supercritical state or gaseous state with low storage density, and the carrying capacity of the working fluid is mainly increased by increasing the volume of the gas cylinder. The present invention creatively applies to a method for high-density storage and supply of xenon, krypton and argon working fluids for electric propulsion. Currently, there is no similar method or system for electric propulsion gas working fluids, and this device is not proposed.

[0026] Step 2: Open the first solenoid valve 5. Liquid xenon pushes the propellant into the downstream pipeline through the action of surface tension and pressure difference and is vaporized by the vaporizer 7. During the brief opening moment of the first solenoid valve 5, a small amount of xenon gas enters the cryogenic buffer tank 10. Step 3: After a certain amount of xenon gas flows into the buffer tank 10, it is heated to above 16.6°C to completely vaporize it, forming high-pressure xenon gas (about 3-5 MPa) that enters the downstream pressure control module; The branches of the two groups of buffer tanks 10 are connected in parallel, with the purpose of alternating the flow of vaporized xenon gas with the branches to make the downstream flow as stable as possible; Step 4: The buffer tank 10 is supplied. When the pressure in any buffer tank 10 is less than a certain value, go to step 2; The present invention controls the opening and closing time of the valve and combines temperature and pressure control measures to control the working medium flowing into the buffer gas volume after gasification within the required pressure range, thereby facilitating downstream pressure and flow management; With the application of electric propulsion technology in the fields of deep space exploration, on-orbit services, etc., higher requirements are put forward for the carrying capacity and storage density of propellant working fluids. The method of this patent invention can realize high-density storage and efficient supply of electric propulsion working fluids such as xenon, krypton, and argon, and has broad application prospects in the above-mentioned fields.

[0027] It should be noted that in the above embodiments, as long as the technical solutions are not contradictory, they can be permuted and combined. Those skilled in the art can exhaust all possibilities based on the mathematical knowledge of permutations and combinations. Therefore, the present invention will no longer describe the technical solutions after permutations and combinations one by one, but it should be understood that the technical solutions after permutations and combinations have been disclosed by the present invention.

[0028] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. An on-orbit high-density storage and supply device for electric propulsion working fluid, characterized by: include: Refrigeration circuit: a storage tank (1), a refrigerator (4), a pump (18), and an injection pipe (2) are connected in a circular sequence, and the injection pipe (2) of the refrigeration circuit is arranged in the storage tank (1); Pressurizing circuit: storage tank (1), heating evaporator (19), and third solenoid valve (22) are cyclically connected; Gaseous working medium circuit: the storage tank (1), the vaporizer (7), and the buffer tank (10) are connected in sequence.

2. The on-orbit high-density storage and supply device for electric propulsion working fluid according to claim 1, characterized in that: One opening of the four-way pipe (20) is connected to the output end of the storage tank (1), and the other three openings of the four-way pipe (20) are respectively connected to the input ends of the refrigerator (4), the heating evaporator (19), and the vaporizer (7).

3. The on-orbit high-density storage and supply device for electric propulsion working fluid according to claim 1 or 2, characterized in that: The injection pipe (2) is provided with a plurality of evenly arranged working medium outlet holes (23).

4. The on-orbit high-density storage and supply device for electric propulsion working fluid according to claim 1 or 2, characterized in that: The output end of the heating evaporator (19) of the boost circuit is connected to the input end of the tank (1) through a second conduit (21), and a third solenoid valve (22) is provided on the second conduit (21).

5. The on-orbit high-density storage and supply device for electric propulsion working fluid according to claim 2, characterized in that: The gaseous working medium circuit is provided with a first solenoid valve (5), which is provided on a four-way pipe (20), an output end of the first solenoid valve (5) is connected to an input end of the vaporizer (7), and a first safety valve (6) is provided on the pipeline between the input end of the first solenoid valve (5) and the four-way pipe (20); A second solenoid valve (8) and a second safety valve (9) are provided on the pipeline between the input end of the buffer tank (10) and the vaporizer (7), and the buffer tank (10) is provided with a second temperature sensor (11) and a second pressure sensor (12).

6. The on-orbit high-density storage and supply device for electric propulsion working fluid according to claim 5, characterized in that: The number of buffer tanks (10) is two or more.

7. The on-orbit high-density storage and supply device for electric propulsion working fluid according to claim 5 or 6, characterized in that: The first solenoid valve (5) and the first safety valve (6) of the gaseous working medium circuit are connected to the four-way pipe (20) via the first flange (14), and the second safety valve (9) and the buffer tank (10) are connected to the second solenoid valve (8) via the third flange (13).

8. The on-orbit high-density storage and supply device for electric propulsion working fluid according to claim 1, characterized in that: The outer side of the tank (1) is wrapped with a heat insulation layer (16), and the tank (1) is provided with a second flange (15) for connecting with a satellite structure (17).

9. The on-orbit high-density storage and supply device for electric propulsion working fluid according to claim 1, characterized in that: The storage tank (1) is provided with a first pressure sensor (26) and a first temperature sensor (27).

10. A method for high-density storage and supply of electric propulsion working fluid on-orbit, characterized by: The on-orbit high-density storage and supply device for electric propulsion working fluid according to any one of claims 1 to 9 comprises the following steps: Working medium storage: The tank (1) contains working medium; when the temperature does not meet the set value or the pressure is too high, the refrigeration circuit is started, and the liquid working medium in the tank (1) is cooled and transported to the tank (1); when the propellant is transported out of the tank, the boosting circuit is started, and the liquid working medium in the tank (1) is vaporized and transported to the buffer tank (10); Working fluid delivery: delivering working fluid to the buffer tank (10) until the pressure of the buffer tank meets the set value.

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