A system for producing a slush hydrogen and a method thereof

Abstract

The application discloses a kind of slurry hydrogen preparation systems and method thereof, comprising: preparation component, supply component, evacuation unit and rocket tank, preparation component includes the first dewar and second dewar connected in parallel;Liquid hydrogen tank car is connected with the first liquid hydrogen inlet of first dewar and second dewar respectively, and air bottle group is connected with the first hydrogen inlet of first dewar and second dewar respectively;The number of evacuation unit is two, two evacuation units are connected in parallel, and two evacuation units are communicated with the first hydrogen outlet of first dewar and second dewar respectively, and the first inlet of rocket tank is communicated with the first liquid hydrogen outlet of first dewar and second dewar respectively.The application overcomes the shortcomings of long preparation time and high cost, achieves the effect of short-time large-scale safe preparation of slurry hydrogen.The application also realizes the continuous preparation of slurry hydrogen by setting the double-tank structure, so that the first dewar and the second dewar alternate operation.

Description

Technical Field

[0001] This invention relates to the field of cryogenic propellant densification technology, and in particular to a slurry hydrogen preparation system and method thereof. Background Technology

[0002] With the vigorous development of the aerospace industry, plasma hydrogen, as a propellant with the most promising applications, deserves attention. However, the maturity of plasma hydrogen technology research is still not high, especially plasma hydrogen preparation technology. Plasma hydrogen refers to a solid-liquid mixture in which tiny solid hydrogen particles are suspended in liquid hydrogen, and it exhibits flow characteristics below a certain solid mass fraction (60%). Currently, the main methods for plasma hydrogen preparation include the following four methods: 1. Spray method; 2. Helium injection method; 3. Spiral scraping method; 4. Freeze-and-thaw method. The spray method involves passing liquid hydrogen through a nozzle, which expands adiabatically to produce solid hydrogen particles. The shape of the solid particles is irregular, depending on the nozzle size and pressure parameters. However, this method has been found that the solid hydrogen particles gradually melt after mixing with liquid hydrogen, making it unsuitable for efficient plasma hydrogen production. The helium injection method involves injecting pure helium into the bottom of liquid hydrogen and preparing plasma hydrogen through the principle of concentration gradient diffusion cooling. This method is simple and reliable, but it wastes a large amount of helium and is not suitable for large-scale plasma hydrogen preparation. The spiral scraping method involves introducing cryogenic helium gas into a cold plate within the heat exchange chamber of a liquid hydrogen unit, freezing the hydrogen gas onto the outer wall of the cold plate. A rotating spiral blade then scrapes away the solid hydrogen particles, which fall into the liquid hydrogen below the chamber to form a slurry. The particle size of the solid hydrogen particles is between 0.1 mm and 0.5 mm. This method has the advantage of continuous slurry hydrogen production, but the spiral blades place higher demands on the production equipment, and pilot-scale and large-scale production verification have not yet been conducted. The freeze-thaw method involves evacuating and depressurizing the liquid hydrogen container using a vacuum pump. When the liquid hydrogen temperature drops to the triple point, the gas-liquid interface freezes to form a solid hydrogen layer. When evacuation stops, the solid hydrogen layer melts and breaks down along the container wall into irregular solid hydrogen blocks or loose, flocculent structures, settling into the liquid hydrogen to form a slurry. Repeated freeze-thaw cycles can produce batches of slurry hydrogen products, with the solid hydrogen particle size maintained between 0.5 mm and 0.7 mm. After extensive comparative analysis, the applicant concluded that the freeze-thaw method is the most economical and feasible approach for large-scale preparation of plasma hydrogen for use in cryogenic rocket fuel. However, experimental observations revealed that the freeze-thaw method results in low preparation efficiency and easily produces a liquid hydrogen-bulk solid hydrogen mixture with poor homogeneity, rather than a true plasma hydrogen product. This is because improper time control during freezing can easily lead to the formation of thick, sheet-like or blocky solid hydrogen layers, which then transform into a dense solid during subsequent thawing, resulting in unsuccessful plasma hydrogen preparation. Furthermore, for practical application, plasma hydrogen preparation requires continuous preparation, continuous refueling, and cyclic stabilization technologies, but relevant research has not yet been publicly reported. Therefore, there is an urgent need to propose a comprehensive system operation process for efficient, continuous, and continuous preparation of plasma hydrogen, as well as for maintaining the solid content within the application tank. Summary of the Invention

[0003] Therefore, it is necessary to provide an efficient system and method for preparing hydrogen slurry.

[0004] A slurry hydrogen preparation system, comprising:

[0005] A fabrication assembly, the fabrication assembly comprising a first Dewar and a second Dewar connected in parallel;

[0006] The supply assembly includes a gas replenishment cylinder group and a liquid hydrogen tanker. The liquid hydrogen tanker is connected to the first liquid hydrogen inlet of the first Dewar and the second Dewar, respectively. The liquid hydrogen tanker is used to supply liquid hydrogen to the first Dewar and the second Dewar. The gas replenishment cylinder group is connected to the first hydrogen inlet of the first Dewar and the second Dewar, respectively.

[0007] The system includes two evacuation units connected in parallel, each connected to the first hydrogen outlet of the first Dewar and the second Dewar, respectively. The evacuation units are used to reduce the pressure inside the first or second Dewar, thereby lowering the temperature of the liquid hydrogen inside the first or second Dewar to the triple point temperature and converting some of the liquid hydrogen into solid hydrogen. The gas replenishment cylinder group is used to introduce slightly positive pressure hydrogen into the first or second Dewar to form slurry hydrogen.

[0008] The rocket storage tank has a first inlet connected to the first liquid hydrogen outlets of the first Dewar and the second Dewar, respectively. The first Dewar and the second Dewar are used to transport slurry hydrogen to the rocket storage tank. The first Dewar and the second Dewar operate alternately to achieve continuous production of slurry hydrogen.

[0009] Optionally, the plasma hydrogen preparation system further includes a precooling component, which includes a helium supply tank and a helium circulation pipeline. The outlet of the helium supply tank is connected to the helium circulation pipeline, and the outlet of the helium supply tank is connected to the first hydrogen inlet of the first Dewar and the second Dewar, respectively, to purge the first Dewar and the second Dewar with helium. The outlet of the helium supply tank is also connected to the helium circulation pipeline to output helium to the helium circulation pipeline. The helium circulation pipeline is connected to a first heat exchanger, a second heat exchanger, and the rocket storage tank in sequence. The helium is used to continuously circulate in the helium circulation pipeline. The first heat exchanger is located inside the first Dewar, and the second heat exchanger is located inside the second Dewar. The first heat exchanger is used to exchange heat between the helium and the first Dewar, and the second heat exchanger is used to exchange heat between the helium output from the first heat exchanger and the second Dewar, so as to achieve precooling of the rocket storage tank by the helium.

[0010] Optionally, it also includes an emission assembly, which includes a flame arrester, a hydrogen combustion assembly, and a helium emission assembly. The inlet of the flame arrester is connected to the second hydrogen outlet of the first Dewar and the second Dewar, the outlet of the evacuation unit, and the first outlet of the rocket tank, respectively. The outlet of the flame arrester is connected to the hydrogen combustion assembly. The helium emission assembly is connected to the second outlet of the rocket tank.

[0011] Optionally, a recovery component is also included, comprising a hydrogen compressor unit, wherein the outlet of the flame arrester is connected to the inlet of the hydrogen compressor unit, and the outlet of the hydrogen compressor unit is connected to the refueling cylinder group, so as to realize the recovery and utilization of hydrogen.

[0012] Optionally, the supply assembly further includes a hydrogen cylinder group, which is connected in parallel with the replenishment cylinder group. The hydrogen cylinder group is connected to the first hydrogen outlet of the first Dewar and the second Dewar respectively through two vacuum units. When the vacuum unit uses an ejector, the hydrogen cylinder group provides a high-pressure working gas flow to the vacuum unit. The high-pressure gas flow mixes with the hydrogen output from the first Dewar or the second Dewar and then enters the flame arrester.

[0013] A preparation method based on the above-described slurry hydrogen preparation system includes the following steps:

[0014] The entire slurry hydrogen preparation system was purged with inert gas;

[0015] Preparation of slurry hydrogen: Liquid hydrogen from the liquid hydrogen tanker is transported to the first Dewar. The first Dewar is evacuated using the evacuation unit to reduce the pressure inside the first Dewar and lower the temperature inside the first Dewar to the triple point temperature. At this point, a solid hydrogen layer begins to appear at the liquid hydrogen interface. Evacuation continues until the vacuum level is constant. When the solid hydrogen layer reaches a preset thickness, the hydrogen gas transported by the gas replenishment cylinder group is depressurized to a slightly positive pressure and then transported to the first Dewar. The slightly positive pressure hydrogen gas acts on the solid hydrogen layer, and under the action of thermoacoustic vibration, the sheet-like or block-like solid hydrogen blocks are transformed into uniformly sized tiny spherical solid hydrogen particles, thereby obtaining uniform slurry hydrogen.

[0016] Optionally, the step of preparing slurry hydrogen may be followed by: adding slurry hydrogen;

[0017] The steps for adding hydrogen slurry include: transporting hydrogen slurry to the rocket storage tank; the hydrogen slurry melts due to heat leakage in the rocket storage tank, causing a decrease in its solid content or conversion into liquid hydrogen; forming a mixture of hydrogen slurry with reduced solid content and liquid hydrogen in the rocket storage tank; transporting the mixture to the second Dewar and evacuating, depressurizing, and cooling the second Dewar; controlling the liquid hydrogen tanker to transport liquid hydrogen to the second Dewar; when the amount of hydrogen slurry in the first Dewar decreases to a preset value, controlling the gas replenishment cylinder group to pressurize the second Dewar, so that the second Dewar prepares hydrogen slurry and transports the prepared hydrogen slurry to the rocket storage tank; then controlling the rocket storage tank to transport the mixture to the first Dewar; simultaneously controlling the liquid hydrogen tanker to add liquid hydrogen to the first Dewar; and maintaining the evacuation unit to evacuate, depressurize, and cool the first Dewar, thereby achieving alternating operation of the first and second Dewars, and thus achieving continuous preparation and addition of hydrogen slurry.

[0018] Optionally, the step of adding hydrogen slurry may precede the precooling of the rocket tank.

[0019] Optionally, the pre-cooling step of the rocket storage tank includes: passing helium gas from the helium supply tank into the first heat exchanger and the second heat exchanger sequentially through the helium gas circulation channel for heat exchange, and finally into the rocket storage tank to pre-cool the rocket storage tank; the pre-cooled helium gas then re-enters the first heat exchanger through the helium gas circulation channel to pre-cool the rocket storage tank in a cycle until the internal temperature of the rocket storage tank is pre-cooled to the triple point temperature of liquid hydrogen, so that the rocket storage tank can meet the conditions for adding propellant hydrogen.

[0020] Optionally, the pre-cooling step of the rocket tank includes: transferring helium from the helium supply tank to the rocket tank after heat exchange in the first heat exchanger and the second heat exchanger to maintain a slightly positive pressure inside the rocket tank; transferring liquid hydrogen or slurry hydrogen from the first Dewar to the rocket tank for pre-cooling; and then returning the pre-cooled liquid hydrogen or slurry hydrogen from the rocket tank to the first Dewar for a pre-cooling cycle until the temperature inside the rocket tank is pre-cooled to the triple point temperature of liquid hydrogen, so that the rocket tank can meet the conditions for slurry hydrogen filling.

[0021] The slurry hydrogen preparation system of this application delivers liquid hydrogen to a first Dewar via a liquid hydrogen tanker. A vacuum unit evacuates, depressurizes, and cools the interior of the first Dewar, causing solidification of the liquid hydrogen inside. When the solidified hydrogen layer reaches a preset thickness, a gas supply cylinder group delivers slightly positive pressure hydrogen into the first Dewar. The high-temperature hydrogen gas (slight positive pressure, 300K) relative to solid hydrogen (7kPa, 14K) directly acts on the surface of the solid hydrogen. The combined effect of thermal and pressure wave oscillations generated by the instantaneous pressurization breaks up large or solid hydrogen blocks into uniformly sized, spherical solid hydrogen particles, which are then uniformly suspended in the liquid hydrogen to form a slurry hydrogen product. This results in a uniform slurry hydrogen, improving its quality and shortening the melting time of the solid hydrogen, thus significantly increasing the efficiency of slurry hydrogen preparation. Compared to existing slurry hydrogen preparation technologies such as freeze-thaw, spiral scraping, and helium injection, the freeze-instant pressurization method overcomes the disadvantages of long preparation time and high cost, achieving the effect of safe, large-scale slurry hydrogen preparation in a short time. This application also features a dual-tank structure, allowing the first and second Dewar tanks to operate alternately, thus enabling the continuous production of slurry hydrogen. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the structure of a plasma hydrogen preparation system in one embodiment;

[0024] Figure 2 This is a partial structural schematic diagram of a hydrogen slurry preparation system in one embodiment;

[0025] Component names and numbers in the diagram: 1. Hydrogen cylinder group; 2. Replenishment cylinder group; 3. Liquid hydrogen tanker; 4. PLC controller; 5. Helium supply tank; 6. First evacuation unit; 7. First heat exchanger; 8. First Dewar; 9. First heat exchanger; 10. First pressure gauge; 11. First thermometer; 12. First density meter; 13. Hydrogen compressor unit; 14. Variable direction liquid hydrogen pump; 15. Second evacuation unit; 16. Second heat exchanger; 17. Second Dewar; 8. Second heat exchanger; 19. Second pressure gauge; 20. Second thermometer; 21. Second density meter; 22. Liquid hydrogen pump; 23. Pulp hydrogen pump; 24. Rocket tank; 25. Third density meter; 26. Mesh screen; 27. Hydrogen combustion assembly; 28. Flame arrester; 29. ​​Helium emission assembly; 30. Helium compressor; 31. Fourteenth valve; 32. Eleventh valve; 33. Thirty-first valve; 34. Seventeenth valve; 35. Eighteenth valve; 36. Tenth valve 9. Valve; 37. Twelfth Valve; 38. Twentieth Valve; 39. Thirty-second Valve; 40. First Valve; 41. Second Valve; 42. Third Valve; 43. Fourth Valve; 44. Thirty-fourth Valve; 45. Ninth Valve; 46. Tenth Valve; 47. Twenty-first Valve; 48. Thirty-fifth Valve; 49. Thirty-second Valve; 50. Thirteenth Valve; 51. Fifth Valve; 52. Sixth Valve; 53. Seventh Valve; 54. Eighth Valve; 55. Thirty-third Valve; 56. Thirty-sixth Valve; 57. Twenty-ninth Valve; 58. Thirty-ninth Valve; 59. Twenty-second Valve; 60. Thirty-seventh Valve; 61. Twenty-eighth Valve; 62. Thirty-eighth Valve; 63. Twenty-fifth Valve; 64. Twenty-third Valve; 65. Check Valve; 66. Fifteenth Valve; 67. Sixteenth Valve; 68. Twenty-fourth Valve; 69. Twenty-sixth Valve; 70. Twenty-seventh Valve.

[0026] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0027] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0029] Furthermore, the use of terms such as "first" and "second" in this invention is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the term "and / or" throughout the text includes three solutions; taking A and / or B as an example, it includes technical solution A, technical solution B, and a technical solution that simultaneously satisfies A and B. Furthermore, the technical solutions of various embodiments can be combined with each other, but this must be based on the ability of a person skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0030] refer to Figure 1 This application provides a plasma hydrogen preparation system, which includes a preparation component, a supply component, a evacuation unit, and a rocket storage tank 24. The preparation component includes a first Dewar 8 and a second Dewar 17 connected in parallel. The supply component includes a gas replenishment cylinder group 2 and a liquid hydrogen tanker 3. The liquid hydrogen tanker 3 is connected to the first liquid hydrogen inlet of the first Dewar 8 and the second Dewar 17, respectively, and is used to supply liquid hydrogen to the first Dewar 8 and the second Dewar 17. The gas replenishment cylinder group 2 is connected to the first hydrogen inlet of the first Dewar 8 and the second Dewar 17, respectively. The evacuation unit consists of two units, including a first evacuation unit 6 and a second evacuation unit 15, which are connected in parallel. The first evacuation unit 6 is connected to the first Dewar 17. The first hydrogen outlet of the rocket tank 8 is connected to the first hydrogen outlet of the second evacuation unit 15, which is connected to the first hydrogen outlet of the second Dewar 17. The evacuation unit is used to reduce the pressure inside the first Dewar 8 or the second Dewar 17, so that the temperature of the liquid hydrogen inside the first Dewar 8 or the second Dewar 17 is reduced to the triple point temperature, and some of the liquid hydrogen is converted into solid hydrogen. The gas replenishment cylinder group 2 is used to introduce slightly positive pressure hydrogen into the first Dewar 8 or the second Dewar 17 to form plasma hydrogen. The first inlet of the rocket tank 24 is connected to the first liquid hydrogen outlet of the first Dewar 8 and the second Dewar 17 respectively. The first Dewar 8 and the second Dewar 17 are used to transport plasma hydrogen to the rocket tank 24. The first Dewar 8 and the second Dewar 17 operate alternately to achieve continuous preparation of plasma hydrogen.

[0031] The hydrogen slurry preparation system of this application delivers liquid hydrogen to the first Dewar 8 via a liquid hydrogen tanker 3. The evacuation unit performs evacuation, depressurization, and cooling operations on the interior of the first Dewar 8 to induce solid hydrogen to appear at the liquid hydrogen interface inside the first Dewar. When the solid hydrogen layer reaches a preset thickness, the gas replenishment cylinder group 2 delivers slightly positive pressure hydrogen into the first Dewar. The high-temperature hydrogen gas (slight positive pressure, 300K) relative to solid hydrogen (7kPa, 14K) directly acts on the surface of the solid hydrogen. Through the combined action of thermal oscillation and pressure wave oscillation generated by instantaneous pressurization, the solid hydrogen block or large block is broken into uniformly sized micro-spherical solid hydrogen particles, which are uniformly suspended in the liquid hydrogen to form a hydrogen slurry product. This results in uniform hydrogen slurry, which improves the quality of the hydrogen slurry and shortens the melting time of the solid hydrogen, thereby significantly improving the preparation efficiency of hydrogen slurry. Compared to existing techniques for preparing hydrogen slurry, such as freeze-thaw, spiral scraping, and helium injection, the freeze-instantaneous pressurization method overcomes the drawbacks of long preparation time and high cost, achieving the effect of safe, large-scale preparation of hydrogen slurry in a short time. This application also utilizes a dual-tank structure, allowing the first Dewar 8 and the second Dewar 17 to operate alternately, enabling continuous preparation of hydrogen slurry.

[0032] Specifically, the first liquid hydrogen outlet of the first Dewar 8 is connected to the first inlet of the rocket tank 24 via the thirty-fifth valve 48, the plasma hydrogen pump 23 and the thirty-seventh valve 60 in sequence, and the first liquid hydrogen outlet of the second Dewar 17 is connected to the first inlet of the rocket tank 24 via the thirty-sixth valve 56 and the pipeline containing the thirty-fifth valve 48 and the plasma hydrogen pump 23.

[0033] Specifically, the preparation components also include a first heat exchanger 7, a first valve 40, a second valve 41, a third valve 42, a fourth valve 43, a second heat exchanger 16, a fifth valve 51, a sixth valve 52, a seventh valve 53, an eighth valve 54, a ninth valve 45, a variable-direction liquid hydrogen pump 14, and a tenth valve 46. The supply components also include an eleventh valve 32, a twelfth valve 37, a thirteenth valve 50, a hydrogen cylinder group 1, a fourteenth valve 31, a fifteenth valve 66, a sixteenth valve 67, a thirty-first valve 33, a thirty-second valve 39, and a thirty-third valve 55. The slurry hydrogen preparation system also includes a precooling component, an emission component, and a recovery component. The precooling component includes a helium supply tank 5 and a helium circulation pipeline. The emission component includes a one-way valve 65, a flame arrester 28, a twenty-fourth valve 68, a hydrogen combustion component 27, a twenty-fifth valve 63, and a helium emission component 29. The recovery component includes a twenty-sixth valve 69, a twenty-seventh valve 70, a hydrogen compressor group 13, and a helium compressor group.

[0034] Specifically, the hydrogen outlet of the first Dewar 8 is divided into three routes. The first hydrogen outlet is connected to the first heat exchanger 7 via the first valve 40 and then to the first evacuation unit 6. The second hydrogen outlet is connected to the flame arrester 28 via the second valve 41 and the one-way valve 65. The pipeline containing the second valve 41 is a hydrogen natural venting pipeline. The third hydrogen outlet is connected to the flame arrester 28 via the third valve 42 and the one-way valve 65. The third hydrogen outlet is also connected to the flame arrester 28 via the fourth valve 43 and the one-way valve 65. The third valve 42 and the fourth valve 43 are connected in parallel. Furthermore, the third valve 42 is a safety valve and the fourth valve 43 is a rupture valve, forming a safety valve / rupture valve pipeline to achieve the purpose of safety and explosion protection.

[0035] The hydrogen outlet of the second Dewar 17 is divided into three routes. The first hydrogen outlet is connected to the second heat exchanger 16 via the fifth valve 51 and finally to the second evacuation unit 15. The second hydrogen outlet is connected to the flame arrester 28 via the sixth valve 52 and the one-way valve 65. The pipeline containing the sixth valve 52 is the hydrogen natural venting pipeline. The third hydrogen outlet is connected to the flame arrester 28 via the seventh valve 53 and the one-way valve 65. The third hydrogen outlet is also connected to the flame arrester 28 via the eighth valve 54 and the one-way valve 65. The seventh valve 53 and the eighth valve 54 are connected in parallel. Furthermore, the seventh valve 53 is a safety valve and the eighth valve 54 is a rupture valve, forming a safety valve / rupture valve pipeline to achieve the purpose of safety and explosion protection.

[0036] The first Dewar 8 is connected in series with the ninth valve 45, the variable liquid hydrogen pump 14, the tenth valve 46, and the second Dewar 17. For example, when the second Dewar 17 acts as a storage Dewar to receive the returned liquid hydrogen and the liquid hydrogen from the liquid hydrogen tanker 3, if the rocket tank 24 is fully refueled and there is still residual slurry hydrogen in the first Dewar 8, the slurry hydrogen in the first Dewar 8 can be injected into the second Dewar 17 through the variable liquid hydrogen pump 14.

[0037] Furthermore, the first Dewar 8 and the second Dewar 17 are connected by pipelines equipped with safety valves and rupture valves. When the pressure inside the Dewar exceeds the set pressure of the safety valve, the safety valve will open, and hydrogen gas will be discharged through the safety valve into the flame arrester 28. If a sudden pressure increase occurs inside the Dewar and the safety valve is insufficient to meet the rapid pressure relief requirement, the gas will break through the rupture valve plate and be discharged into the flame arrester 28.

[0038] The first outlet of the rocket propellant tank 24 is also connected to the inlet of the flame arrester 28 via the thirty-eighth valve 62. The outlet of the flame arrester 28 then splits into two paths: one path connects to the hydrogen combustion assembly 27 via the twenty-fourth valve 68, and the other path connects to the hydrogen compressor unit 13 via the twenty-sixth valve 69. The hydrogen compressor unit 13 then connects to the replenishment cylinder group 2 and the hydrogen cylinder group 1 via the twenty-seventh valve 70. The second outlet of the rocket propellant tank 24 is connected to the helium emission assembly 29 via the twenty-fifth valve 63. The flame arrester 28 is used to prevent flame propagation, achieving explosion-proof safety operation.

[0039] Specifically, the evacuation unit is a vacuum pump / ejector to perform evacuation / ejection pressure reduction and cooling operations on the first Dewar 8 or the second Dewar 17.

[0040] Liquid hydrogen tanker 3 connects to the first Dewar 8 via valve 31 (31st valve 33), valve 32 (32nd valve 39), and then to the second Dewar 17 via valve 33 (33rd valve 55). The replenishment cylinder group 2 connects to the first hydrogen inlet of the first Dewar 8 via valve 11 (32nd valve 32) and valve 12 (37th valve 37), and to the first hydrogen inlet of the second Dewar 17 via valve 11 (32nd valve 32) and valve 13 (50th valve 50). Hydrogen cylinder group 1 and replenishment cylinder group 2 are connected in parallel. Hydrogen cylinder group 1 connects to the first hydrogen outlet of the first Dewar 8 via valve 14 (31st valve 31) and evacuation unit 6, and to the first hydrogen outlet of the second Dewar 17 via valve 14 (31st valve 31) and evacuation unit 15. The first evacuation unit 6 and the second... A thirty-fourth valve 44 is installed between the evacuation units 15, and a fifteenth valve 66 is installed between the second evacuation unit 15 and the flame arrester 28. A sixteenth valve 67 is connected in parallel at both ends of the second evacuation unit 15. When the evacuation units use a vacuum pump for evacuation, this arrangement allows the hydrogen output from the first Dewar 8 to reach the flame arrester 28 after passing through the first evacuation unit 6 and the second evacuation unit 15. When the evacuation units use an ejector for evacuation, the high-pressure hydrogen output from the hydrogen cylinder group 1 and the low-pressure hydrogen output from the first Dewar 8 are mixed in the first evacuation unit 6 to become medium-pressure hydrogen. This medium-pressure hydrogen serves as the high-pressure working gas flow of the second evacuation unit 15 to eject the low-pressure hydrogen in the second Dewar 17. Finally, the mixed hydrogen passes through the fifteenth valve 66 and enters the flame arrester 28.

[0041] The outlet of the helium supply tank 5 is divided into two paths after passing through the seventeenth valve 34. One path passes through the eighteenth valve 35 and merges into the pipeline where the eleventh valve 32 is located. The helium passes through the twelfth valve 37 and the thirteenth valve 50 respectively and enters the first Dewar 8 and the second Dewar 17. The helium and hydrogen replenishment share the same pipeline. The helium is used as a pressurizing gas and can also be used as a compression gas during the process of adding fuel to the rocket storage tank 24.

[0042] Another path connects to the helium circulation pipeline via the nineteenth valve 36. The helium circulation pipeline is connected sequentially to the twentieth valve 38, the first heat exchanger 9, the twenty-first valve 47, the second heat exchanger 18, the twenty-second valve 59, the second inlet of the rocket storage tank 24, the third outlet of the rocket storage tank 24, the twenty-third valve 64, the helium compressor 30, and the twentieth valve 38. Before refueling begins, helium enters the first heat exchanger 9 through the twentieth valve 38 to exchange heat with the first Dewar 8, then enters the second heat exchanger 18 through the twenty-first valve 47 to exchange heat with the second Dewar 17, and finally enters the rocket storage tank 24 through the twenty-second valve 59 for pre-cooling. After a period of time, the helium enters the helium compressor 30 through the twenty-third valve 64, and the compressed helium re-enters the twentieth valve 38, thus completing one helium pre-cooling cycle, which is used for pre-cooling and maintaining a slight positive pressure in the rocket storage tank 24.

[0043] Furthermore, the helium gas is introduced from the bottom of the rocket storage tank 24, which can provide a pre-cooling effect and also serve as a pressure-holding gas to ensure a slightly positive pressure environment inside the rocket storage tank 24. In addition, during the fueling process and the parking phase after fueling, the injection of helium gas can maintain the solid hydrogen content of the rocket fuel in the rocket storage tank 24.

[0044] Furthermore, the fourth outlet of the rocket tank 24 is connected to the second Dewar 17 via the twenty-eighth valve 61, the screen 26, the thirty-ninth valve 58, the liquid hydrogen pump 22, and then to the first Dewar 8 via the twenty-ninth valve 57.

[0045] Specifically, the first Dewar 8 is equipped with a first pressure gauge 10, a first thermometer 11, a first density meter 12 and a first level gauge, and the second Dewar 17 is equipped with a second pressure gauge 19, a second thermometer 20, a second density meter 21 and a second level gauge to measure the pressure, temperature and density inside the first Dewar 8 and the second Dewar 17. The rocket tank 24 is equipped with a third density meter 25.

[0046] The slurry hydrogen production system of this application also includes a PLC controller 4, which is connected to a first pressure gauge 10, a first thermometer 11, a first density meter 12, a second pressure gauge 19, a second thermometer 20, a second density meter 21, a third density meter 25, and all valves. The PLC controller 4 is used to issue action commands to each valve in the system based on the collected data such as temperature, pressure, liquid level, and density, to detect the real-time dynamics of slurry hydrogen production, and to make timely adjustment strategies.

[0047] Furthermore, the PLC controller in this application employs negative feedback regulation automatic control. By collecting information on temperature, pressure, liquid level, solid hydrogen layer thickness, and real-time density of the hydrogen slurry within the Dewar, it adjusts the opening degree of each valve and the cooling supply unit, thereby achieving remote automatic control. Through experimental calculations, the system estimates the relationship between liquid hydrogen mass, solid hydrogen freezing layer thickness, liquid level, and hydrogen slurry density, thus achieving the effect of accurately preparing hydrogen slurry with a specified solid content in a single operation.

[0048] Specifically, the first Dewar 8 and the second Dewar 17 are both high-vacuum multilayer insulating Dewars; the fourteenth valve 31 and the seventeenth valve 34 are pressure reducing valves; the eleventh valve 32 is a secondary pressure reducing valve; and the thirty-first valve 33, the thirty-second valve 39, and the thirty-third valve 55 are cryogenic shut-off valves. Specifically, the densitometer can be one of a capacitance densitometer, a sound velocity densitometer, a microwave densitometer, or a radiation attenuation densitometer, etc.; temperature and pressure measurements are performed using conventional methods.

[0049] The first heat exchanger 7 and the second heat exchanger 16 are low-temperature heat exchangers, including one of plate heat exchangers, tube heat exchangers, and tube-fin heat exchangers, which raise the temperature of the extracted hydrogen gas to above -40°C.

[0050] This application employs a dual-tank structure to achieve high-quality and efficient preparation, continuous refueling, and stable operation. A single-tank structure is insufficient for continuous refueling, and during refueling and storage, heat leakage from the tank causes significant melting of the propellant hydrogen, reducing its solids content and making long-term storage impossible. To address these issues, the system utilizes a dual-tank structure with switching modes for continuous preparation / refueling of propellant hydrogen, meeting the demand for large quantities of propellant hydrogen and ensuring the stability of the propellant hydrogen solids content within the rocket's propellant tank.

[0051] In some embodiments, when the first Dewar 8 prepares slurry hydrogen, the second Dewar 17 is used as a storage Dewar. Liquid hydrogen from the liquid hydrogen tanker 3 enters the first Dewar 8 through the thirty-first valve 33. During this process, the thirty-second valve 39 and the second valve 41 are opened, and the thirty-third valve 55 is closed to achieve natural venting of hydrogen in the first Dewar 8 and rapid addition of liquid hydrogen. The liquid hydrogen addition process is determined based on the pressure / temperature / liquid level signals transmitted to the PLC control system. After the liquid hydrogen addition is completed, the PLC control closes the thirty-second valve 39 to cut off the liquid hydrogen supply and closes the second valve 41 to cut off the natural venting pipeline. Subsequently, the evacuation preparation operation is performed. The PLC controller 4 determines, based on the pressure and temperature data inside the first Dewar 8, that after the freezing process is completed, hydrogen from the gas replenishment cylinder group 2 is needed for instantaneous pressurization. With valves 11 and 12 open, the hydrogen in the replenishment cylinder group 2 is reduced to atmospheric pressure after passing through the double-stage pressure reduction of valve 11 32. At this time, the 300K, slightly positive pressure hydrogen enters the first Dewar 8 and acts on the solid hydrogen layer in the triple point state. Through the dual effects of thermal oscillation and pressure wave oscillation generated by instantaneous pressurization, the solid hydrogen block or large block is broken, thereby forming uniformly sized tiny spherical solid hydrogen particles, which are uniformly suspended in liquid hydrogen to form slurry hydrogen product. During this period, valve 13 50 is kept closed. The slurry hydrogen prepared by the first Dewar 8 is injected into the rocket storage tank 24 by the slurry hydrogen pump 23 or under the pressure of helium gas through the pipeline where valve 35 48 is located.During the refueling process, heat leakage causes solid hydrogen to melt and the density of the slurry hydrogen to decrease. After a period of storage, the slurry hydrogen begins to melt and gradually separates into layers. The slurry hydrogen with higher solid content gradually settles to the bottom layer, while the upper layer is low-density slurry hydrogen / liquid hydrogen. Since the fourth outlet of the rocket storage tank 24 is located in the middle of the rocket storage tank 24, the low-density slurry hydrogen / liquid hydrogen in the rocket storage tank 24 enters the bottom pipeline with a screen 26 through the fourth outlet and is pumped to the second Dewar 17 by the liquid hydrogen pump 22. During this process, the second Dewar 17 acts as a storage Dewar. The PLC controller 4 judges the slurry hydrogen refueling progress based on data such as the density inside the rocket storage tank 24 and controls the opening of the thirty-first valve 33 and the opening degree of the twenty-ninth valve 57 to realize the operation of refueling the second Dewar 17 with liquid hydrogen. That is, the second Dewar 17 simultaneously receives liquid hydrogen from the return liquid hydrogen from the rocket storage tank 24 and liquid hydrogen from the liquid hydrogen tanker 3, while maintaining the pumping of the second Dewar 17. During the depressurization and cooling operation, when the amount of slurry hydrogen in the first Dewar 8 decreases to a certain level, the eleventh valve 32 and the thirteenth valve 50 are opened. After the hydrogen in the gas replenishment cylinder group 2 is depressurized by the eleventh valve 32, the pressure drops to atmospheric pressure. At this time, 300K, slightly positive pressure hydrogen enters the second Dewar 17 and acts on the solid hydrogen layer in the triple point state. Through the dual effects of thermal oscillation and pressure wave oscillation generated by instantaneous pressurization, the whole or large solid hydrogen block is broken, thereby forming uniformly sized tiny spherical solid hydrogen particles, which are uniformly suspended in liquid hydrogen to form slurry hydrogen products. During this period, the twelfth valve 37 is kept closed. Meanwhile, the twenty-ninth valve 57 on the return pipeline from the rocket storage tank 24 to the second Dewar 17 is closed, the thirtieth valve 49 on the return pipeline from the rocket storage tank 24 to the first Dewar 8 is opened, and the thirty-second valve 39 is opened to allow liquid hydrogen from the liquid hydrogen tanker 3 to be added to the first Dewar 8. The functions of the two Dewars are switched. The hydrogen prepared by the second Dewar 17 is injected into the rocket storage tank 24 by the hydrogen pump 23 or under the pressure of helium gas through the pipeline where the thirty-sixth valve 56 is located. This completes a dual-tank switching preparation, storage and injection process, which can also ensure the solid content of hydrogen in the rocket storage tank 24 during the parking stage.

[0052] The evacuation unit can employ, but is not limited to, ejectors, variable frequency water ring pump units, and variable frequency rotary vane pumps. It uses evacuation, depressurization, and flash evaporation to lower the temperature within the hydrogen slurry preparation Dewar to the triple point, thus freezing the liquid hydrogen into solid hydrogen. A PLC controls the valve opening and the hydrogen pumping rate, thereby controlling the speed and thickness of the solid hydrogen frozen layer formation, ultimately producing the required solid content hydrogen slurry. When the pumping volume requirement is large or the operating environment is harsh, an ejector can be used as the evacuation unit. Opening the first valve 40, the thirty-fourth valve 44, and the fifteenth valve 66, and opening the fourteenth valve 31, allows the high-pressure hydrogen from hydrogen cylinder group 1 to enter the ejector after depressurization via the fourteenth valve 31, serving as the high-pressure working gas flow. The evacuation unit is used to mix the low-pressure hydrogen output from the first Dewar 8 or the second Dewar 17 with the high-pressure hydrogen output from hydrogen cylinder group 1, and then deliver the mixed medium-pressure hydrogen to the flame arrester 28. When the evacuation unit uses a variable frequency water ring pump unit, variable frequency rotary vane pump, or other vacuum pumps, the hydrogen in hydrogen cylinder group 1 is not needed, so the fourteenth valve 31 remains closed. For example, when the first Dewar is used to prepare the Dewar, the thirty-fourth valve 44 and the fifteenth valve 66 are opened. The hydrogen in the first Dewar 8 enters the first heat exchanger 7 through the first valve 40 for reheating, then passes through the first evacuation unit 6 and flows along the pipelines containing the thirty-fourth valve 44 and the fifteenth valve 66 into the pipeline containing the one-way valve 65, and finally enters the flame arrester 28.

[0053] In some embodiments, for rapid fueling and launch missions, two precooling methods can be used. The first is plasma hydrogen precooling: the first Dewar 8 or the second Dewar 17 serves as the fully precooling Dewar for the rocket tank 24, while the other plasma hydrogen Dewar serves as the plasma hydrogen supply Dewar. Taking the first Dewar 8 as the fully precooling Dewar and the second Dewar 17 as the plasma hydrogen supply Dewar as an example, assuming that plasma hydrogen preparation has been underway for some time and the second Dewar 17 already contains a certain amount of plasma hydrogen with a solid content, and the first Dewar 8 contains a certain amount of liquid hydrogen or plasma hydrogen with a low solid content, during the precooling stage, the thirty-fifth valve 48 is opened, allowing the liquid hydrogen or plasma hydrogen with a low solid content in the first Dewar 8 to enter the rocket tank 24. The liquid is heated and vaporized, lowering the temperature inside the rocket tank 24. The hydrogen is recovered or burned off through the flame arrester. After the liquid hydrogen or plasma hydrogen with a low solid content is introduced, it stays for a period of time and then flows back to the first Dewar 8 through the twenty-eighth valve 61 and the thirtieth valve 49, repeating this process. Several rounds of pre-cooling operations ensure that rocket tank 24 is fully pre-cooled. At this point, valve 56 is opened, allowing high-solids-content hydrogen to be injected into rocket tank 24 in one go. Because rocket tank 24 is already thoroughly cooled, the loss of hydrogen solids content during refueling is minimal, ensuring sufficient hydrogen solids content in rocket tank 24 for a single refueling operation to meet the requirements of rapid refueling and launch missions. The second method is helium pre-cooling: the first dewar 8 serves as the hydrogen preparation dewar, and the second dewar 17 serves as the liquid hydrogen / low-solids-content hydrogen receiving dewar. Helium in helium supply tank 5 undergoes heat exchange in the first heat exchanger 9 and the second heat exchanger 18 before finally entering rocket tank 24 for pre-cooling. Helium that has completed one round of pre-cooling enters helium compressor 30 through valve 64, and the compressed helium then passes through valve 38 to begin the next helium pre-cooling cycle. Helium is used as the cooling medium, and through continuous circulation, the rocket propellant tank temperature is pre-cooled to near the triple point of liquid hydrogen, meeting the pre-conditions for adding plasma hydrogen to the rocket propellant tank. During this process, the first Dewar 8 and the second Dewar 17 are continuously evacuated, depressurized, and cooled, following the evacuation procedure in the plasma hydrogen preparation steps. The PLC controls valve 36; when the circulating helium is insufficient, valve 36 opens to appropriately replenish the pipeline. Once the rocket propellant tank 24 is pre-cooled to the liquid hydrogen temperature range by the helium, valve 38 is closed to cut off the pre-cooling circulation of helium within the Dewar-rocket propellant tank, preventing the prepared plasma hydrogen from melting due to the heat introduced by the helium. Valve 39, valve 55, valve 41, and valve 40 are closed, while valves 32 and 37 are opened to pressurize the first Dewar 8, preparing plasma hydrogen in one go. After plasma hydrogen preparation is complete, valves 48 and 60 are opened for rapid plasma hydrogen injection.

[0054] In some embodiments, when a mission requires parking, the rocket tank 24 is not launched immediately after refueling. To ensure the solids content of the propellant hydrogen in the rocket tank 24, low-solids-content propellant hydrogen in the rocket tank 24 is transferred to a propellant hydrogen dewar, while another propellant hydrogen dewar is responsible for transferring high-solids-content propellant hydrogen to the rocket tank 24. This dynamic refueling and stabilization system ensures a high solids content of propellant hydrogen in the rocket tank 24. For example, a first dewar 8 serves as the refueling dewar, and a second dewar 17 serves as the storage dewar. During the refueling process of the first dewar 8, the second dewar 17 receives liquid hydrogen from the liquid hydrogen tanker and low-solids-content propellant hydrogen / liquid hydrogen returning from the rocket tank 24, maintaining the evacuation, depressurization, and cooling operation of the second dewar 17. When the plasma hydrogen in the first Dewar 8 decreases to a certain level, the functions of the three Dewars—33rd valve 55, 29th valve 57, 6th valve 52, and 5th valve 51—are switched off. The second Dewar 17 becomes the filling Dewar, and the sixth valve 52, thirty-first valve 33, and thirty-third valve 55 are opened to replenish liquid hydrogen into the second Dewar 17 to the required amount. After the liquid hydrogen filling is completed, the thirty-third valve 55, twenty-ninth valve 57, and sixth valve 52 are closed to cut off the liquid hydrogen filling and evacuation operation. The eleventh valve 32 and thirteenth valve 50 are opened to perform a pressurization operation to prepare plasma hydrogen in one go. During this period, the thirtieth valve 49 is opened to transport the low-solids-content plasma hydrogen / liquid hydrogen returning from the rocket tank 24 to the first Dewar 8. This cycle can maintain the solids content of plasma hydrogen in the rocket tank 24 during the parking phase.

[0055] In some embodiments, the rocket storage tank 24 can also be replaced by equipment such as a plasma hydrogen tanker for different applications.

[0056] In some embodiments, for the slurry hydrogen preparation Dewar, when liquid hydrogen is rapidly added, the valve on the corresponding hydrogen natural vent pipe needs to be opened to allow the evaporated hydrogen to be discharged smoothly, and the natural vent pipe is connected to the flame arrester; for the slurry hydrogen storage Dewar, when it receives liquid hydrogen from the liquid hydrogen tanker 3 and liquid hydrogen reflux from the rocket storage tank, the valve on the corresponding hydrogen natural vent pipe needs to be opened to allow the evaporated hydrogen to be discharged smoothly, and the natural vent pipe is connected to the flame arrester 28.

[0057] A preparation method based on the above-described slurry hydrogen preparation system includes the following steps:

[0058] S1. Purge the entire slurry hydrogen preparation system with inert gas: Before starting slurry hydrogen preparation, introduce nitrogen into the system to fill the entire device and purge multiple times; then introduce helium and purge again.

[0059] S2. Preparation of Slurry Hydrogen: After purging, the liquid hydrogen in the liquid hydrogen tanker 3 enters the first Dewar 8 through valves 31 (33) and 32 (39). During this process, valve 41 remains open and valve 55 (33) remains closed. When there is enough liquid hydrogen in the first Dewar 8, valves 32 (39) and 41 (2) are closed. When the evacuation unit is a vacuum pump such as a water ring pump, valve 31 (41) is closed and valve 67 (67) is opened. The evacuation unit removes the gas from the first Dewar 8, reducing the pressure inside. The temperature in the first Dewar 8 is lowered to the triple point temperature through evacuation, depressurization, and flash evaporation. At this point, a solid hydrogen layer begins to appear at the gas-liquid interface. Evacuation continues. The vacuum level is kept constant. The thickness of the solid hydrogen layer is determined by the liquid level, pressure, and temperature data in the first Dewar 8. When the required solid hydrogen layer thickness is reached, the eleventh valve 32 and the twelfth valve 37 are opened. The high-pressure hydrogen in the gas replenishment cylinder group 2 is reduced to a slightly positive pressure through the eleventh valve 32 and then enters the first Dewar 8 through the twelfth valve 37. The 300K, slightly positive pressure hydrogen acts on the solid hydrogen layer in the triple point state. The thermal oscillation and pressure wave oscillation generated by the instantaneous pressurization break up the whole or large solid hydrogen block, thereby forming uniformly sized tiny spherical solid hydrogen particles. These particles are then uniformly suspended in the liquid hydrogen to form a slurry hydrogen product, completing one single tank slurry hydrogen preparation.

[0060] S3. Pre-cool the rocket storage tank 24.

[0061] S31. Open valves 33, 39, 55, 41, and 52 to add liquid hydrogen to the first Dewar 8 and the second Dewar 17. The first Dewar 8 is used as a slurry hydrogen preparation Dewar, and the second Dewar 17 is used as a liquid hydrogen / low solids content slurry hydrogen receiving Dewar. The liquid hydrogen filling degree of the first Dewar 8 should be higher than that of the second Dewar 17.

[0062] If using the first precooling method – helium precooling – the procedure is as follows:

[0063] S321. Open valves 17 (34), 19 (36), 20 (38), 21 (47), and 22 (59). Helium from helium supply tank 5 passes through these valves and enters the first heat exchanger 9 and the second heat exchanger 18 for heat exchange, finally entering rocket storage tank 24 for pre-cooling. The pre-cooled helium then passes through valve 23 (64) into helium compressor 30. The compressed helium then passes through valve 20 (38) again to start the next helium pre-cooling cycle. Helium is used as the cooling medium, continuously circulating and cooling until the rocket storage tank temperature is pre-cooled to near the triple point of liquid hydrogen, meeting the pre-conditions for adding propellant hydrogen to the rocket storage tank. During this process, the first dewar 8 and the second dewar 17 are continuously evacuated, depressurized, and cooled, following the evacuation procedure in the propellant hydrogen preparation steps. The PLC controls valve 19 (36). When the circulating helium is insufficient, valve 19 (36) opens to appropriately replenish the pipeline.

[0064] Liquid hydrogen is added to the first Dewar 8 and the second Dewar 17 to their respective target values. While helium pre-cools the rocket storage tank 24 to the liquid hydrogen temperature range, the twentieth valve 38 is closed to cut off the helium pre-cooling cycle within the Dewar-rocket storage tank 24, preventing the prepared plasma hydrogen from melting due to the heat introduced by the helium. The thirtieth valve 39, the thirty-third valve 55, the second valve 41, and the first valve 40 are closed, while the eleventh valve 32 and the twelfth valve 37 are opened to pressurize the first Dewar 8, preparing plasma hydrogen in a single operation.

[0065] After the preparation of plasma hydrogen in the first Dewar 8 is completed (S341), valves 35 (48) and 37 (60) are opened to inject plasma hydrogen. The plasma hydrogen can be injected by helium compression or plasma hydrogen pump 23. For helium compression, helium in the helium precooling cycle can be used for pressurization. Valve 37 (34), 18 (35), and 12 (37) need to be opened. Helium in helium supply tank 5 enters the first Dewar 8 through the above valves to compress the plasma hydrogen. For plasma hydrogen pump 23 compression, plasma hydrogen pump 23 needs to be opened to extract plasma hydrogen from the first Dewar 8 and inject it into rocket storage tank 24.

[0066] S351. During the fueling process into rocket propellant tank 24, open valve 25 (63). Pre-cooled helium gas inside the propellant tank is gradually released as propellant hydrogen is added, maintaining a slight positive pressure in the propellant tank's gas pillow area. After propellant hydrogen fueling is complete, close valve 25 (63). Proceed to S4.

[0067] If the second precooling method—plasma hydrogen precooling—is used, the operation is as follows:

[0068] S322. Open valves 17 (34), 19 (36), 20 (38), 21 (47), and 22 (59). Helium from helium supply tank 5 passes through these valves and enters the first heat exchanger 9 and the second heat exchanger 18 for heat exchange, finally entering rocket storage tank 24. Here, helium is not used as a pre-cooling medium, but as a pressure-maintaining medium for rocket storage tank 24, ensuring that rocket storage tank 24 maintains a slight positive pressure throughout the plasma hydrogen refueling process. Therefore, helium circulation is not required, and helium compressor 30 is not started. During this period, evacuation, depressurization, and cooling are maintained for the first dewar 8 and the second dewar 17, specifically following the evacuation procedure in the plasma hydrogen preparation steps.

[0069] Liquid hydrogen is added to the first Dewar 8 and the second Dewar 17 to their respective target values. The 32nd valve 39, the 33rd valve 55, the second valve 41, and the first valve 40 are closed. The 32nd valve 39 and the 12th valve 37 are opened to pressurize the first Dewar 8, preparing plasma hydrogen in one operation. The 35th valve 48 and the 37th valve 60 are opened to add plasma hydrogen. Plasma hydrogen can be added using helium compression or the plasma hydrogen pump 23. For helium compression, helium from the helium precooling cycle can be used for pressurization, requiring the opening of the 17th valve 34, the 18th valve 35, and the 12th valve 37. Helium from the helium supply tank 5 enters the first Dewar 8 through these valves to compress the plasma hydrogen. For plasma hydrogen pump 23 compression, the pump 23 needs to be activated to extract plasma hydrogen from the first Dewar 8 and inject it into the rocket storage tank 24. As plasma hydrogen is continuously added, the helium in the rocket storage tank is gradually released, maintaining a slightly positive pressure in the rocket storage tank's gas pillow area. The plasma hydrogen entering the rocket tank 24 serves as a pre-cooling medium. Under the influence of ambient heat leakage, it gradually melts into low-solids plasma hydrogen or liquid hydrogen. The thirty-eighth valve 62 is opened to release hydrogen gas. The low-solids plasma hydrogen or liquid hydrogen passes through the twenty-eighth valve 61, the twenty-ninth valve 57, and the twenty-ninth valve 58. Liquid hydrogen passes through the above valves and enters the second Dewar 17, thus completing one plasma hydrogen pre-cooling process.

[0070] S342. During this process, the helium in the rocket storage tank 24 is reduced in mass due to the addition of hydrogen to the plasma. The seventeenth valve 34 and the nineteenth valve 36 are opened to replenish helium from the helium supply tank 5.

[0071] S352. After several rounds of pre-cooling of the propellant hydrogen, the rocket tank 24 is completely cooled and can then be continuously refueled with propellant hydrogen; proceed to S4.

[0072] S4. Hydrogen Filling: During the filling process of the first Dewar 8, the second Dewar 17 receives liquid hydrogen from the liquid hydrogen tanker 3 and low-solids-content hydrogen / liquid hydrogen returning from the rocket storage tank 24, maintaining the evacuation, depressurization, and cooling operation of the second Dewar 17. When the hydrogen in the first Dewar 8 decreases to a certain level, the thirty-third valve 55, the twenty-ninth valve 57, the sixth valve 52, and the fifth valve 51 are closed, and the functions of the first Dewar 8 and the second Dewar 17 are switched. The second Dewar 17 becomes the preparation Dewar, and the sixth valve 52, the thirty-first valve 33, and the thirty-third valve 55 are opened to replenish the second Dewar 17 to the required amount for preparation. After the liquid hydrogen filling is completed, the thirty-third valve 55, the twenty-ninth valve 57, and the sixth valve 52 are closed to cut off the liquid hydrogen filling and evacuation operation, and the eleventh valve 32 and the thirteenth valve 50 are opened to perform a pressurization operation to prepare hydrogen in one go. At this point, the thirtieth valve 49 is opened, allowing the low-solids-content slurry hydrogen / liquid hydrogen returning from the rocket storage tank 24 to be transported to the first Dewar 8. This completes the function switch between the two tanks, enabling continuous preparation and continuous refueling of slurry hydrogen.

[0073] The above are merely preferred embodiments of the present invention and do not limit the scope of the patent. Any equivalent structural transformations made using the contents of the specification and drawings of the present invention under the inventive concept of the present invention, or direct / indirect applications in other related technical fields, are included within the scope of patent protection of the present invention.

Claims

1. A slurry hydrogen preparation system, characterized in that, include: A fabrication assembly, the fabrication assembly comprising a first Dewar and a second Dewar connected in parallel; The supply assembly includes a gas replenishment cylinder group and a liquid hydrogen tanker. The liquid hydrogen tanker is connected to the first liquid hydrogen inlet of the first Dewar and the second Dewar, respectively. The liquid hydrogen tanker is used to supply liquid hydrogen to the first Dewar and the second Dewar. The gas replenishment cylinder group is connected to the first hydrogen inlet of the first Dewar and the second Dewar, respectively. The system includes two evacuation units connected in parallel, each connected to the first hydrogen outlet of the first Dewar and the second Dewar, respectively. The evacuation units are used to reduce the pressure inside the first or second Dewar, thereby lowering the temperature of the liquid hydrogen inside the first or second Dewar to the triple point temperature and converting some of the liquid hydrogen into solid hydrogen. The gas replenishment cylinder group is used to introduce slightly positive pressure hydrogen into the first or second Dewar to form slurry hydrogen. The rocket storage tank has a first inlet connected to the first liquid hydrogen outlets of the first Dewar and the second Dewar, respectively. The first Dewar and the second Dewar are used to transport slurry hydrogen to the rocket storage tank. The first Dewar and the second Dewar operate alternately to achieve continuous production of slurry hydrogen. The plasma hydrogen preparation system also includes a precooling component, which includes a helium supply tank and a helium circulation pipeline. The outlet of the helium supply tank is connected to the helium circulation pipeline, and the outlet of the helium supply tank is connected to the first hydrogen inlet of the first Dewar and the second Dewar, respectively, to purge the first Dewar and the second Dewar with helium. The outlet of the helium supply tank is also connected to the helium circulation pipeline to output helium to the helium circulation pipeline. The helium circulation pipeline is connected to a first heat exchanger, a second heat exchanger, and the rocket storage tank in sequence. The helium is used to continuously circulate in the helium circulation pipeline. The first heat exchanger is located inside the first Dewar, and the second heat exchanger is located inside the second Dewar. The first heat exchanger is used to supply helium for heat exchange with the first Dewar, and the second heat exchanger is used to supply helium output from the first heat exchanger for heat exchange with the second Dewar, so as to achieve precooling of the rocket storage tank by the helium. The supply assembly also includes a hydrogen cylinder group, which is connected in parallel with the replenishment cylinder group. The hydrogen cylinder group is connected to the first hydrogen outlet of the first Dewar and the second Dewar respectively through two vacuum units. When the vacuum unit uses an ejector, the hydrogen cylinder group provides working airflow to the vacuum unit. The working airflow mixes with the hydrogen output from the first Dewar or the second Dewar and then enters the flame arrester.

2. The slurry hydrogen preparation system according to claim 1, characterized in that, It also includes an emission assembly, which comprises a flame arrester, a hydrogen combustion assembly, and a helium emission assembly. The inlet of the flame arrester is connected to the second hydrogen outlet of the first Dewar and the second Dewar, the outlet of the evacuation unit, and the first outlet of the rocket tank, respectively. The outlet of the flame arrester is connected to the hydrogen combustion assembly. The helium emission assembly is connected to the second outlet of the rocket tank.

3. The slurry hydrogen preparation system according to claim 2, characterized in that, It also includes a recovery component, which includes a hydrogen compressor unit. The outlet of the flame arrester is connected to the inlet of the hydrogen compressor unit, and the outlet of the hydrogen compressor unit is connected to the gas replenishment cylinder group to realize the recovery and utilization of hydrogen.

4. A method for preparing hydrogen slurry based on the hydrogen slurry preparation system according to any one of claims 1-3, characterized in that, Includes the following steps: The entire slurry hydrogen preparation system was purged with inert gas; Preparation of slurry hydrogen: Liquid hydrogen from the liquid hydrogen tanker is transported to the first Dewar. The first Dewar is evacuated using the evacuation unit to reduce the pressure inside the first Dewar and lower the temperature inside the first Dewar to the triple point temperature. At this point, a solid hydrogen layer begins to appear at the liquid hydrogen interface. Evacuation continues until the vacuum level is constant. When the solid hydrogen layer reaches a preset thickness, the hydrogen gas transported by the gas replenishment cylinder group is depressurized to a slightly positive pressure and then transported to the first Dewar. The slightly positive pressure hydrogen gas acts on the solid hydrogen layer, and under the action of thermoacoustic vibration, the sheet-like or block-like solid hydrogen blocks are transformed into uniformly sized tiny spherical solid hydrogen particles, thereby obtaining uniform slurry hydrogen.

5. The preparation method according to claim 4, characterized in that, The step of preparing slurry hydrogen also includes: adding slurry hydrogen; The steps for adding hydrogen slurry include: transporting hydrogen slurry to the rocket storage tank; the hydrogen slurry melts due to heat leakage in the rocket storage tank, causing a decrease in its solid content or conversion into liquid hydrogen; forming a mixture of hydrogen slurry with reduced solid content and liquid hydrogen in the rocket storage tank; transporting the mixture to the second Dewar and evacuating, depressurizing, and cooling the second Dewar; controlling the liquid hydrogen tanker to transport liquid hydrogen to the second Dewar; when the amount of hydrogen slurry in the first Dewar decreases to a preset value, controlling the gas replenishment cylinder group to pressurize the second Dewar, so that the second Dewar prepares hydrogen slurry and transports the prepared hydrogen slurry to the rocket storage tank; then controlling the rocket storage tank to transport the mixture to the first Dewar; simultaneously controlling the liquid hydrogen tanker to add liquid hydrogen to the first Dewar; and maintaining the evacuation unit to evacuate, depressurize, and cool the first Dewar, thereby achieving alternating operation of the first and second Dewars, and thus achieving continuous preparation and addition of hydrogen slurry.

6. The preparation method according to claim 5, characterized in that, The step of injecting hydrogen slurry includes pre-cooling the rocket tank.

7. The preparation method according to claim 6, characterized in that, The pre-cooling step of the rocket storage tank includes: passing helium gas from the helium supply tank into the first heat exchanger and the second heat exchanger sequentially through the helium gas circulation channel for heat exchange, and finally into the rocket storage tank to pre-cool the rocket storage tank. The pre-cooled helium gas then re-enters the first heat exchanger through the helium gas circulation channel to pre-cool the rocket storage tank until the internal temperature of the rocket storage tank is pre-cooled to the triple point temperature of liquid hydrogen, so that the rocket storage tank can meet the conditions for adding propellant hydrogen.

8. The preparation method according to claim 6, characterized in that, The pre-cooling step of the rocket tank includes: helium gas from the helium supply tank is introduced into the rocket tank after heat exchange in the first heat exchanger and the second heat exchanger to maintain the internal pressure of the rocket tank at a slightly positive pressure; liquid hydrogen or slurry hydrogen from the first Dewar is delivered to the rocket tank to pre-cool the rocket tank; then the pre-cooled liquid hydrogen or slurry hydrogen is returned from the rocket tank to the first Dewar to perform a pre-cooling cycle until the internal temperature of the rocket tank is pre-cooled to the triple point temperature of liquid hydrogen, so that the rocket tank can meet the conditions for slurry hydrogen injection.

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