WO2024041146A1 - Integrated system and method for mars surface carrier rocket propellant in-situ preparation - Google Patents

Abstract

Disclosed in the present invention are an integrated system and a method for Mars surface carrier rocket propellant in-situ preparation. In the present invention, a methane propellant is prepared from carbon dioxide in the atmosphere of Mars, and a liquid oxygen propellant and oxygen required by a life support system are prepared by means of water electrolysis in water-containing minerals of Mars, such that the present invention has a high degree of fit with requirements of liquid oxygen methane carrier rockets and Mars exploration tasks. In the present invention, product water of a liquid methane preparation process is conveyed to a water electrolysis system, so that the exploitation amount of the water-containing minerals can be reduced by half, that is, oxygen in carbon dioxide of Mars is used as an important source of a liquid oxygen propellant.

Description

An integrated system and method for in-situ preparation of propellant for Mars surface launch vehicles Technical field

The invention relates to the technical field of Mars exploration, and specifically relates to an integrated system and method for in-situ preparation of propellant for Mars surface launch vehicles.

Background technique

In-situ preparation of Mars propellant refers to the exploration, acquisition and utilization of natural resources on Mars to prepare launch vehicle propellant in situ on Mars. It is a highly sustainable and low-cost deep space exploration solution that can effectively reduce the burden on resources carried. It is a key technical means to realize extraterrestrial activities such as extraterrestrial manned exploration and future space colonization. The main component of the Martian surface atmosphere is carbon dioxide, accounting for 95.32% of the total. It is the most potential raw material for the in-situ preparation of Mars propellant. According to NASA calculations, manned Mars exploration requires the production of 7 tons of methane propellant, 23 tons of liquid oxygen propellant, and 5 tons of oxygen for life support within 16 months, for a total of 35 tons.

However, as there have been no return-type Mars exploration activities, the in-situ preparation of propellants on the Mars surface is still in the technical exploration stage, including using carbon dioxide in the Martian atmosphere to prepare methane, kerosene and other hydrocarbon fuel propellants. However, there is still no significant progress. Clear technical solutions.

Contents of the invention

The purpose of the present invention is to solve the problem in the prior art that it is difficult to prepare propellant raw materials that meet the needs of manned Mars exploration, and to provide an integrated system and method for in-situ preparation of propellant for a Mars surface launch vehicle. The invention uses carbon dioxide in the Martian atmosphere to prepare liquid methane propellant, and electrolyzes water in Martian water-containing minerals to prepare liquid oxygen propellant, thereby achieving simultaneous and efficient preparation of liquid methane propellant and liquid oxygen propellant.

The specific technical solutions adopted by the present invention are as follows:

In a first aspect, the invention provides an integrated system for in-situ preparation of propellant for Mars surface launch vehicles, which includes a liquid methane preparation pipeline, a liquid oxygen preparation pipeline, a mixed gas pipeline, a water vapor pipeline, a hydrogen pipeline and an oxygen gas pipeline. pipeline;

The liquid methane preparation pipeline is connected in sequence to a carbon dioxide capture system, a Sabatier reduction system, Sabatier reaction gas separation system and liquid methane storage tank;

The liquid oxygen preparation pipeline is connected in sequence to a water-containing mineral transportation system, a water vapor extraction system, an electrolyzed water system, an oxygen liquefaction system, and a liquid oxygen storage tank;

The mixed gas pipeline is connected to the Sabatier reaction gas separation system and the Sabatier reduction system;

The water vapor pipeline connects the Sabatier reaction gas separation system and the electrolyzed water system;

The hydrogen pipeline connects the electrolyzed water system and the Sabatier reduction system;

The oxygen pipeline connects the electrolyzed water system and external aerobic equipment;

The carbon dioxide capture system is used to capture carbon dioxide from the Martian atmosphere and input it into the Sabatier reduction system as raw material;

The Sabatier reduction system is used to use carbon dioxide and hydrogen as raw materials to generate methane and water through the Sabatier reduction reaction;

The Sabatier reaction gas separation system is used to separate the components of the reaction gas output from the Sabatier reduction system. The separated unreacted carbon dioxide and hydrogen mixture is returned to the Sabatier reduction system through the mixed gas pipeline and used as raw material again. The separated methane is used as raw material. Liquid methane is stored in the liquid methane storage tank, and the separated water enters the electrolyzed water system through the water vapor pipeline;

The water-containing mineral transportation system is used to input the water-containing minerals collected on Mars into the water vapor extraction system, and the water vapor extraction system extracts the water and inputs it into the electrolyzed water system;

The electrolytic water system is used to electrolyze water to produce hydrogen and oxygen. The produced hydrogen is input into the Sabatier reduction system as raw material through the hydrogen pipeline, and the produced oxygen is input into the oxygen liquefaction system for liquefaction and then stored in the liquid oxygen storage. In the tank, the other line is input to the external aerobic equipment through the oxygen pipeline.

As a preference of the above first aspect, the carbon dioxide capture system includes a carbon dioxide liquefaction pipeline, a first interstage cooler and a second interstage cooler;

The first intercooler and the second intercooler are each provided with a first passage and a second passage forming heat exchange contact;

The inlet end of the carbon dioxide liquefaction pipeline is used to pass into the Martian atmosphere, and the outlet end is connected to a low-temperature gas-liquid separator; the carbon dioxide liquefaction pipeline is connected in sequence from the inlet end to the outlet end to a filter, an electric heater, and a first-stage room. The first passage of the cooler, the low-temperature fan, the first-stage compressor, the second passage of the first-stage intercooler, the second-stage compressor, the first passage of the second-stage intercooler, the water vapor adsorber, and the carbon dioxide condensation and cryogenic gas-liquid separators;

The gas phase outlet of the low-temperature gas-liquid separator is emptied, the liquid phase outlet is connected to the second passage of the second interstage cooler through the output pipeline, and the second passage outlet of the second interstage cooler is connected to the liquid methane preparation pipe. road connection.

As a preferred aspect of the above first aspect, the Sabatier reduction system includes an insulated reactor shell, and the reaction chamber inside the reactor shell is provided with an air inlet and an air outlet;

The reaction chamber is divided into a high-temperature reaction zone and a gradient temperature field reaction zone through an annular insulated partition plate;

The high-temperature reaction zone has a built-in heater for heating the raw material gas of the Sabatier reaction to the initial reaction temperature, and the surface of the heater is coated with a Sabatier reaction catalyst;

The gradient temperature field reaction zone is provided with a first metal porous medium layer, a second metal porous medium layer and a third metal porous medium layer in sequence along the air inlet direction, and the first metal porous medium layer, the second metal porous medium layer and the third metal porous media layer have decreasing porosity, and the media surface is coated with a Sabatier reaction catalyst; the three metal porous media layers all exchange heat with the external Martian atmosphere through a flat heat pipe that penetrates the reactor shell, so that the three layers The Sabatier reaction heat in the metallic porous medium layer can be transferred to the Martian atmosphere;

After the raw material gas is introduced from the air inlet, it sequentially flows through the heater surface in the high-temperature reaction zone and the first metal porous medium layer, the second metal porous medium layer and the third metal layer in the gradient temperature field reaction zone. The porous medium layer is then discharged from the air outlet.

As a preference of the above first aspect, the Sabatier reaction gas separation system includes a reaction gas separation pipeline, a water vapor condenser, a precooler, a carbon dioxide condenser and a liquid methane reflux pipeline;

The water vapor condenser, precooler and carbon dioxide condenser are respectively provided with a first passage and a second passage that constitute heat exchange contact;

The inlet end of the reaction gas separation pipeline is used to pass into the Sabatier device reaction gas, and the outlet end is connected to the liquid methane storage tank; the reaction gas separation pipeline is sequentially connected to the first passage of the water vapor condenser from the inlet end to the outlet end. , the first gas-liquid separator, the first passage of the precooler, the first passage of the carbon dioxide condenser, the second gas-liquid separator, the heat exchange pipeline in the methane liquefaction cold box, the third gas-liquid separator and the third gas-liquid separator. A low-temperature stop valve; the second passage of the water vapor condenser and the precooler are both used to pass into the Martian atmosphere to cool the first passage; the methane liquefaction cold box is equipped with a low-temperature refrigerator, and the cold head of the low-temperature refrigerator is connected to The heat exchange pipeline in the methane liquefaction cold box forms heat exchange contact, and the temperature of the cold head can liquefy the methane in the reaction gas of the Sabatier device flowing through the heat exchange pipeline;

The inlet end of the liquid methane reflux pipeline is connected to the reaction gas separation pipeline between the third gas-liquid separator and the first low-temperature stop valve, and the outlet end is connected to the reaction gas between the second gas-liquid separator and the methane liquefaction cold box. gas Separation pipeline; the liquid methane return pipeline is connected in sequence from the inlet end to the outlet end to the second low temperature stop valve, the second passage of the carbon dioxide condenser and the third low temperature stop valve.

As a preferred aspect of the above first aspect, in the oxygen liquefaction system, the cold energy of the Martian atmosphere is used to pre-cool the oxygen, and then the oxygen is cooled and liquefied by a cryogenic refrigerator.

As a preference of the above first aspect, the cryogenic refrigerator is a Stirling cryogenic refrigerator.

As a preferred aspect of the above first aspect, the water vapor extraction system is a microwave heating device, which obtains pure water vapor by microwave heating of water-containing minerals.

As a preferred option of the above first aspect, the water electrolysis system adopts a photocatalytic assisted water electrolysis system.

As a preferred aspect of the above first aspect, the external aerobic equipment is a life support system.

In a second aspect, the present invention provides a method for in-situ preparation of propellant for a Mars surface launch vehicle using the system described in any one of the above-mentioned aspects of the first aspect, which includes:

S1. Enrich the Martian atmosphere and obtain high-purity carbon dioxide gas through the carbon dioxide capture system, and then transport the carbon dioxide to the Sabatier reduction system through the liquid methane preparation pipeline;

S2. Transport the hydrated minerals on the surface of Mars to the water vapor extraction system through the hydrated mineral transport system. The water vapor extraction system extracts water vapor from the hydrated minerals and transports it to the electrolyzed water system;

S3. The electrolysis water system electrolyzes water to produce hydrogen and oxygen. The hydrogen is transported to the Sabatier reduction system through the hydrogen pipeline. The oxygen is divided into two outputs. One is transported to the oxygen liquefaction system through the liquid oxygen preparation pipeline and is supplied by the oxygen The liquefaction system liquefies the oxygen and stores it in a liquid oxygen storage tank, and the other is transported to the life support system through an oxygen pipeline;

S4. The Sabatier reduction system uses the carbon dioxide gas transported by the carbon dioxide capture system and the hydrogen gas transported by the electrolysis water system as raw materials. Under the action of the catalyst, methane and water are generated through the Sabatier reaction to generate four components including methane, water vapor, carbon dioxide and hydrogen. The reaction gas is transported to the Sabatier reaction gas separation system to separate the four components. The separated carbon dioxide and hydrogen are returned to the Sabatier reduction system, and are combined with the carbon dioxide gas delivered by the carbon dioxide capture system and the hydrogen delivered by the electrolyzed water system. The mixture is used as raw material gas again, and the separated methane is stored in the liquid methane storage tank in the form of liquid methane. The separated water enters the electrolysis water system through the water vapor pipeline and is electrolyzed together with the water extracted by the water vapor extraction system.

Compared with the existing technology, the present invention has outstanding and beneficial technical effects: it proposes an integrated system for in-situ preparation of propellant for the Mars surface launch vehicle, which can realize the simultaneous preparation of propellant required for the launch vehicle; utilizing Carbon dioxide in the Martian atmosphere is used to prepare methane propellant, and water electrolysis in Mars' water-bearing minerals is used to prepare liquid oxygen propellant and oxygen required for life support systems. This is highly consistent with the needs of liquid oxygen methane launch vehicles and Mars exploration missions; according to It is calculated that for every 1kg of methane obtained through the reduction reaction, the corresponding product water can obtain 2kg of oxygen through electrolysis. The present invention transports the product water from the liquid methane preparation process to the electrolytic water system, so the mining volume of water-containing minerals can be reduced by half. The oxygen element in Martian carbon dioxide will be used as an important source of liquid oxygen propellant.

The concept, specific structure and technical effects of the present invention will be further described below in conjunction with the accompanying drawings to fully understand the purpose, features and effects of the present invention.

Description of drawings

Figure 1 is a schematic structural diagram of an integrated system for in-situ preparation of propellant for Mars surface launch vehicles;

Figure 2 is a schematic diagram of a preferred method of a carbon dioxide capture system;

Figure 3 is a schematic diagram of a preferred method of the Sabatier reduction system;

Figure 4 is a schematic diagram of a preferred method of the Sabatier reaction gas separation system.

The reference numbers in the figure are: liquid methane preparation pipeline 1, liquid oxygen preparation pipeline 2, carbon dioxide/hydrogen mixing pipeline 3, water vapor pipeline 4, hydrogen pipeline 5, oxygen pipeline 6, carbon dioxide capture system 7, Sabatier reduction system 8, Sabatier reaction gas separation system 9, life support system 10, liquid methane storage tank 11, hydrous mineral mining system 12, water vapor extraction system 13, electrolyzed water system 14, oxygen liquefaction system 15, liquid oxygen storage tank 16 .

Detailed ways

The present invention will be further elaborated and described below in conjunction with the accompanying drawings and specific embodiments. The technical features of various embodiments of the present invention can be combined accordingly as long as they do not conflict with each other.

In order to make the above objects, features and advantages of the present invention more obvious and easy to understand, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the invention. However, the present invention can be implemented in many other ways different from those described here. Those skilled in the art can make similar improvements without departing from the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below. The technical features in various embodiments of the present invention can be combined accordingly as long as they do not conflict with each other.

In the description of the present invention, it will be understood that when an element is referred to as being "connected" to another element, it may be directly connected to the other element or indirectly connected through the presence of intervening elements. On the contrary, when the component is When an element is connected "directly" to another element there are no intervening elements present.

In the description of the present invention, it should be understood that the terms "first" and "second" are only used for distinction and description purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of indicated technical features. . Therefore, features defined as "first" and "second" may explicitly or implicitly include at least one of these features.

As shown in Figure 1, in a preferred embodiment of the present invention, an integrated system for in-situ preparation of propellant for Mars surface launch vehicles is provided. Its components include a liquid methane preparation pipeline 1 and a liquid oxygen preparation pipeline. 2. Carbon dioxide/hydrogen mixing pipeline 3. Water vapor pipeline 4. Hydrogen pipeline 5. Oxygen pipeline 6. Carbon dioxide capture system 7. Sabatier reduction system 8. Sabatier reaction gas separation system 9. Life support system 10. Liquid methane Storage tank 11, hydrous mineral mining system 12, water vapor extraction system 13, electrolyzed water system 14, oxygen liquefaction system 15, liquid oxygen storage tank 16. In this system, carbon dioxide in the Martian atmosphere can be used to prepare liquid methane propellant, and liquid oxygen propellant can be prepared by electrolyzing water in water-containing minerals on Mars, achieving the simultaneous and efficient preparation of liquid methane propellant and liquid oxygen propellant.

In the entire system, each subsystem is connected through the liquid methane preparation pipeline 1, the liquid oxygen preparation pipeline 2, the mixed gas pipeline 3, the water vapor pipeline 4, the hydrogen pipeline 5 and the oxygen pipeline 6, thereby achieving collaborative work. . Among them, the liquid methane preparation pipeline 1 is connected in sequence to the carbon dioxide capture system 7, the Sabatier reduction system 8, the Sabatier reaction gas separation system 9 and the liquid methane storage tank 11. The liquid oxygen preparation pipeline 2 is connected to the water-containing mineral transportation system 12, the water vapor extraction system 13, the electrolyzed water system 14, the oxygen liquefaction system 15 and the liquid oxygen storage tank 16 in sequence. The mixed gas pipeline 3 is connected to the Sabatier reaction gas separation system 9 and the Sabatier reduction system 8 . The water vapor pipeline 4 connects the Sabatier reaction gas separation system 9 and the electrolyzed water system 14. The hydrogen pipeline 5 connects the electrolyzed water system 14 and the Sabatier reduction system 8 . The oxygen pipeline 6 connects the electrolyzed water system 14 and external aerobic equipment. The external aerobic equipment can be any equipment that requires oxygen on Mars. In this embodiment, the external aerobic equipment is the life support system 10 on Mars.

Each subsystem in the above-mentioned integrated system, except for pipelines and storage tanks, is the key to realizing the functions of the integrated system. The respective functions and cooperation relationships are described below.

The carbon dioxide capture system 7 is used to capture carbon dioxide from the Martian atmosphere and input it into the Sabatier reduction system 8 as raw material. Since more than 95% of the components in the Martian atmosphere are carbon dioxide, the carbon dioxide capture system 7 can use the Martian atmosphere as raw material to obtain carbon dioxide from it through adsorption, freezing, and other methods.

Sabatier reduction system 8 is used to use carbon dioxide and hydrogen as raw materials, through Sabatier reduction reaction Methane and water should be produced. The Sabatier reduction system 8 is a device commonly used in aerospace equipment, which can produce methane through the Sabatier reduction reaction. Sabatier reduction system 8 can theoretically be implemented using any Sabatier reaction device.

The Sabatier reaction gas separation system 9 is used to separate the components of the reaction gas output by the Sabatier reduction system 8. The separated unreacted carbon dioxide and hydrogen mixture is returned to the Sabatier reduction system 8 through the mixed gas pipeline 3 and used as raw material again. Methane is stored in the liquid methane storage tank 11 in the form of liquid methane, and the separated water enters the electrolyzed water system 14 through the water vapor pipeline 4 . For the separation of different components in the Sabatier reaction gas separation system 9, the difference in liquefaction temperature between different components can be used to perform step-by-step separation.

The water-containing mineral transport system 12 is used to transport the water-containing minerals collected on Mars into the water vapor extraction system 13 , and the water vapor extraction system 13 extracts the moisture therein and transports it into the electrolyzed water system 14 . The hydrous mineral transport system 12 can adopt any transmission equipment, and its front end can be connected to a hydrous mineral collection device. The water vapor extraction system 13 preferably uses a microwave heating device to obtain pure water vapor by microwave heating of water-containing minerals.

The electrolyzed water system 14 is used to electrolyze water to produce hydrogen and oxygen. The produced hydrogen is input into the Sabatier reduction system 8 through the hydrogen pipeline 5 as a raw material, and the produced oxygen is input into the oxygen liquefaction system 15 for liquefaction and then stored in the liquid. In the oxygen storage tank 16, the other line is input to the life support system 10 through the oxygen pipeline 6.

In the present invention, the water electrolysis system 14 can be any device in the prior art that electrolyzes water to produce hydrogen and oxygen. Considering the efficiency of electrolyzing water, auxiliary systems such as photocatalysis can be configured on the basis of traditional devices to fully utilize solar energy to improve the operating efficiency of the system. That is, the water electrolysis system 14 can adopt a photocatalytic assisted water electrolysis system.

In the present invention, the oxygen liquefaction system 15 uses the cold energy of the Martian atmosphere to pre-cool the oxygen, and then cools and liquefies the oxygen through a cryogenic refrigerator. The specific low-temperature refrigerator used is preferably a Stirling low-temperature refrigerator that is small in size and light in weight. Of course, pressure can also be assisted during the oxygen cooling and liquefaction process to improve the liquefaction efficiency.

The operation process of the above-mentioned Mars surface launch vehicle propellant in-situ preparation integrated system is as follows:

(1) The carbon dioxide capture system 7 enriches the Martian atmosphere and obtains high-purity carbon dioxide gas, and then transports the carbon dioxide to the Sabatier reduction system 8 through the liquid methane preparation pipeline 1.

(2) The Sabatier reduction system 8 includes three inputs, which are the two inputs delivered by the carbon dioxide capture system 7. A mixture of carbon dioxide gas, hydrogen transmitted by the electrolysis water system 14 and carbon dioxide and hydrogen transmitted by the Sabatier reaction gas separation system 9, and then carbon dioxide and hydrogen generate methane and water under the action of the catalyst, because the conversion rate of the Sabatier reaction is affected by temperature , so carbon dioxide and hydrogen will not react completely. The reaction gas delivered by the Sabatier reduction system 8 to the Sabatier reaction gas separation system 9 contains four substances: methane, water vapor, carbon dioxide and hydrogen.

(3) The Sabatier reaction gas separation system 9 separates the reaction gas, and then transports unreacted carbon dioxide and hydrogen to the Sabatier reduction system 8 through the carbon dioxide/hydrogen mixing pipeline 3 for further reaction, and transports water vapor to the electrolysis through the water vapor pipeline 4 The water system 14 performs electrolysis and transports methane in the form of liquid methane to the liquid methane storage tank 11 for storage.

(5) The water-containing mineral transport system 12 mines water-containing minerals on the surface of Mars, and after preliminary processing, transports them to the water vapor extraction system 13. The water vapor extraction system 13 uses microwave heating and other methods to process the water-containing minerals to obtain water vapor with a purity that meets the requirements. And transport it to the electrolyzed water system 14.

(6) The electrolyzed water system 14 includes two inputs, which are the mineral extraction water delivered by the water vapor extraction system 13 and the product water delivered by the Sabatier reaction gas separation system 9. Subsequently, the water will be electrolyzed into hydrogen and oxygen, and the hydrogen will pass through the hydrogen pipeline. 5 is transported to the Sabatier reduction system 8 to participate in the reduction reaction. The oxygen is divided into two outputs, one is transported to the oxygen liquefaction system 15 through the liquid oxygen preparation pipeline 2, and the other is transported to the life support system 10 through the oxygen pipeline 6.

(7) The oxygen liquefaction system 15 liquefies the oxygen provided by the electrolyzed water system 14 and transports the liquid oxygen to the liquid oxygen storage tank 16 for storage.

In addition, in another preferred embodiment of the present invention, a specific implementation of the carbon dioxide capture system 7 is further provided. As shown in Figure 2, its components include a filter 7-2, an electric heater 7-3, First-stage intercooler 7-4, low-temperature fan 7-5, first-stage compressor 7-6, second-stage compressor 7-7, second-stage intercooler 7-8, water vapor adsorber 7-9 , carbon dioxide condenser 7-10, low temperature gas-liquid separator 7-11 and output pipeline 7-12. The connection relationship between each component is as follows:

The first intercooler 7-4 and the second intercooler 7-8 are each provided with a first passage and a second passage forming heat exchange contact.

The inlet end of the carbon dioxide liquefaction pipeline 7-1 is used to pass into the Martian atmosphere, and the outlet end is connected to the low-temperature gas-liquid separator 7-11; the carbon dioxide liquefaction pipeline 7-1 is connected to the filter 7-1 in sequence from the inlet end to the outlet end. 2. Electric heater 7-3, first passage of first-stage intercooler 7-4, low-temperature fan 7-5, first-stage compressor 7-6, the second passage of the first-stage intercooler 7-4, the second-stage compressor 7-7, the first passage of the second-stage intercooler 7-8, the water vapor adsorber 7-9, and the carbon dioxide condensation 7-10 and low-temperature gas-liquid separator 7-11.

The gas phase outlet of the low-temperature gas-liquid separator 7-11 is emptied, and the liquid phase outlet is connected to the second passage of the second-stage intercooler 7-8 through the output pipeline 7-12. The second passage of the second-stage intercooler 7-8 is The outlet of the second channel is connected to the liquid methane preparation pipeline 1.

The selection of the above equipment can be adjusted according to actual needs. In this embodiment, the filter is preferably an electrostatic precipitator, and the first-stage compressor 7-6 and the second-stage compressor 7-7 can be a positive displacement compressor. And the outlet pressure of the second stage compressor 7-7 should be higher than the triple point pressure of carbon dioxide. The low-temperature gas-liquid separator 7-11 can use a centrifugal gas-liquid separator. The first intercooler 7-4 and the second intercooler 7-8 may use gas-to-gas plate heat exchangers. Carbon dioxide condensers 7-10 can use finned tube heat exchangers, and the cold source can be the Martian atmosphere at night which is lower than the carbon dioxide condensation temperature, or other low-temperature working fluids can be used when the Martian atmospheric temperature is higher than the carbon dioxide condensation temperature. Auxiliary.

The specific method for continuous carbon dioxide capture on the surface of Mars based on the above carbon dioxide capture system 7 is as follows:

Start the electric heater 7-3, the low-temperature fan 7-5, the first-stage compressor 7-6, the second-stage compressor 7-7 and the low-temperature gas-liquid separator 7-11 in sequence, so that the Martian atmosphere can be heated by the low-temperature fan 7-5. 5 enters the carbon dioxide liquefaction pipeline 7-1, first flows through the filter 7-2 to remove impurities such as dust and becomes pure raw material gas, and then enters the electric heater 7-3 and the first-stage intercooler 7-4 in sequence The first pass is preheated. It is particularly important to note that the electric heater 7-3 is only turned on when the system starts. After stable operation, the first intercooler 7-4 provides the heat required for preheating, and the electric heater 3 does not need to be turned on. The preheated raw material gas is pulled by the low-temperature fan 7-5 and enters the first-stage compressor 7-6 to complete the first pressurization, forming a primary pressurized raw material gas. After the supercharging is completed, the temperature of the primary supercharged raw gas will rise sharply. The high-temperature primary supercharged raw gas enters the second passage of the first-stage intercooler 7-4 and interacts with the first channel of the first-stage intercooler 7-4. After the raw material gas that is not preheated in the passage undergoes heat exchange and cooling, it then enters the second-stage compressor 7-7 for a second pressurization to obtain a secondary pressurized raw gas. After the supercharging is completed, the temperature of the secondary supercharged raw gas will rise sharply. The high-temperature secondary supercharged raw gas enters the first passage of the second-stage intercooler 7-8 and interacts with the second-stage intercooler 7-8. The liquid carbon dioxide flowing into the first passage is cooled by heat exchange, and the raw material gas whose temperature is maintained above 273.15K is obtained. It then enters the water vapor adsorber 7-9 in the carbon dioxide liquefaction pipeline 7-1 to remove water vapor, and obtains high-purity carbon dioxide raw gas. . The high-purity carbon dioxide raw gas continues to enter the carbon dioxide condenser 7-10 to liquefy the carbon dioxide, but this time When carbon dioxide enters the queue for liquefaction, there may be some impurity gases with lower liquefaction temperatures such as nitrogen and argon in the carbon dioxide feed gas that have not yet been liquefied, so what flows out from the carbon dioxide condenser 7-10 is. The gas-liquid two-phase mixture enters the low-temperature gas-liquid separator 7-11 for gas-liquid separation, the impurity gas is discharged directly, and the liquid carbon dioxide is input into the second passage of the second interstage cooler 7-8 through the output pipeline 7-12, and The secondary pressurized feed gas is re-vaporized after heat exchange and enters the liquid methane preparation pipeline 1 for subsequent Sabatier reaction.

The adsorbents that can be filled in the water vapor adsorbers 7-9 are adsorbents with strong adsorption capacity for water such as aluminum oxide. However, adsorption saturation may occur after the water vapor adsorber 7-9 has been running for a period of time. It can be temporarily shut down, the water vapor adsorber 7-9 can be replaced, or the internal adsorption medium can be heated and regenerated.

It should also be noted that if the pressure of the carbon dioxide gas entering the liquid methane preparation pipeline 1 does not meet the subsequent reaction requirements, it needs to be pressurized. The specific pressurization method belongs to the existing technology.

In addition, in another preferred embodiment of the present invention, a specific implementation method of the Sabatier reduction system 8 is further provided. As shown in Figure 3, its components include a Sabatier reactor shell 8-1, an insulation material 8-2, Sabatier reactor inner shell 8-3, heater 8-9, insulation partition plate 8-10, first metal porous medium layer 8-11, second metal porous medium layer 8-12, third metal porous medium layer 8 -13. Flat heat pipe.

The Sabatier reduction system 8 includes a thermally insulated reactor shell, and the reaction chamber inside the reactor shell is provided with an air inlet and an air outlet. The reactor thermal insulation shell is made of a Sabatier reactor outer shell 8-1 and a Sabatier reactor inner shell 8-3 nested inside and outside, and the inner and outer shell interlayers are filled with thermal insulation material 8-2. The reaction chamber is divided into a high-temperature reaction zone 8-4 and a gradient temperature field reaction zone 8-5 through annular thermal insulation partitions 8-10. The thermal insulation material 8-2 can use vacuum insulation panels. For the entire reaction chamber, since the temperature of the high-temperature reaction zone 8-4 is higher, the Sabatier reaction here has a higher reaction rate. However, if the temperature is too high, the conversion rate of the reaction will decrease. Therefore, it is necessary to increase the conversion rate of the reaction by setting up a gradient temperature field reaction zone 8-5.

The high-temperature reaction zone 8-4 has a built-in heater 8-9 for heating the raw material gas of the Sabatier reaction to the initial reaction temperature. The surface of the heater 8-9 is coated with a Sabatier reaction catalyst. The heaters 8-9 may use solar energy as a heat source.

The gradient temperature field reaction zone 8-5 is provided with a first metal porous medium layer 8-11, a second metal porous medium layer 8-12 and a third metal porous medium layer 8-13 in sequence along the air inlet direction, and the first metal porous medium layer The porous media layers 8-11, the second metal porous media layers 8-12, and the third metal porous media layers 8-13 have decreasing porosity, and the surfaces of the media are all coated with Sabatier reaction catalysts; the three metal porous media layers are all passed through Reactor shell flat The plate heat pipe forms a heat exchange with the external Martian atmosphere, allowing the Sabatier reaction heat in the three metal porous media layers to be transferred to the Martian atmosphere.

In the reaction chamber, after the raw material gas is introduced from the air inlet, it flows through the surface of the heater 8-9 in the high-temperature reaction zone 8-4 and the first metal porous medium layer in the gradient temperature field reaction zone 8-5. 8-11. The second metal porous dielectric layer 8-12 and the third metal porous dielectric layer 8-13 are then discharged from the air outlet.

The above-mentioned flat heat pipe includes a flat heat pipe evaporation section 8-6, a flat heat pipe insulating section 8-7 and a flat heat pipe condensation section 8-8 connected in sequence. The flat heat pipe evaporation section 8-6 is located in the gradient temperature field reaction zone 8 -5 and is connected to and forms heat exchange contact with the first metal porous medium layer 8-11, the second metal porous medium layer 8-12, and the third metal porous medium layer 8-13. The flat heat pipe condensation section 8-8 is located The outside of the reactor shell is in contact with the Martian atmosphere. The flat heat pipe insulating section 8-7 penetrates through the reactor shell and is connected to the flat heat pipe evaporation section 8-6 and the flat heat pipe condensation section 8-8 at both ends.

In order to improve the heat exchange efficiency as much as possible, the flat heat pipe is arranged in an annular shape in the gradient temperature field reaction zone 8-5, and the flat heat pipe evaporation section 8-6 is wrapped around the outer periphery of the three metal porous media layers. Moreover, the connection positions between the flat heat pipe evaporation section 8-6 and the first metal porous dielectric layer 8-11, the second metal porous dielectric layer 8-12 and the third metal porous dielectric layer 8-13 can be further filled with holes for eliminating contact. Thermal resistance of thermal conductive media.

In the present invention, the first metal porous dielectric layer 8-11, the second metal porous dielectric layer 8-12 and the third metal porous dielectric layer 8-13

In the above-mentioned first metal porous medium layer 8-11, second metal porous medium layer 8-12 and third metal porous medium layer 8-13, each metal porous medium layer uses a metal porous medium as a metal skeleton, and then The Sabatier reaction catalyst is attached to the surface of the metal skeleton, and the Sabatier reaction heat can be quickly transferred to the negative heat evaporation section of the flat heat pipe through the porous metal skeleton. The specific metal framework and catalyst form are not limited. As a preferred implementation method of the embodiment of the present invention, each metal porous medium layer can use copper foam with good thermal conductivity and high melting point as the metal skeleton, and the Sabatier reaction catalyst coated on the surface of the copper foam can use a Ru-based catalyst. Ru-based catalysts are beneficial to reducing the starting temperature of the Sabatier reaction. Since the spatial thermal conductivity of metal porous media increases as the porosity decreases, the lower the porosity, the higher the thermal conductivity. Therefore, the more heat is dissipated through the flat heat pipe, the lower the temperature of the metal porous media layer itself is. . Therefore, the first metal porous medium layer 8-11, the second metal porous medium layer 8-12 and the third metal porous medium layer 8-13 can form a gradient temperature field in which the temperature gradually decreases along the flow direction of the raw material gas. The first metal porous media The reaction rates of the layers 8-11, the second metal porous dielectric layer 8-12, and the third metal porous dielectric layer 8-13 gradually decrease, but the conversion rate of the Sabatier reaction gradually increases.

It should be noted that the specific porosity of the three metal porous media layers is not limited, as long as the three meet the requirements of gradually decreasing porosity, and the specific porosity of each can be optimized and designed according to the actual reaction situation.

The specific process of carbon dioxide hydromethanation on the surface of Mars based on the above-mentioned Sabatier reactor is as follows:

The raw material gas is passed into the reaction chamber inside the reactor shell from the air inlet. First, the raw material gas is heated to the Sabatier reaction starting temperature by the heater 8-9 in the high-temperature reaction zone 8-4, thereby heating The reduction reaction occurs under the action of the Sabatier reaction catalyst coated on the surface of vessels 8-9, converting part of the feed gas into methane and water. At this time, the Sabatier reaction rate in the high-temperature reaction zone 8-4 is higher, but the conversion rate of the feed gas is lower.

Then the partially converted raw material gas continues to flow into the gradient temperature field reaction zone 8-5, and sequentially flows through the first metal porous medium layer 8-11 with decreasing porosity, the second metal porous medium layer 8-12 and the third metal The porous media layers 8-13 continue to perform third-level conversion and release reaction heat under the action of the Sabatier reaction catalyst coated on the media surface. In the process of the raw material gas passing through the gradient temperature field reaction zone 8-5, the raw material gas first contacts the high-porosity metal porous medium 8-11. Under the action of the metal skeleton surface catalyst, the raw material gas continues to transform and release reactions. Heat, due to the high porosity, the temperature of the area where the high-porosity metal porous medium 8-11 is located is higher; then it comes into contact with the intermediate-porosity metal porous medium 8-12, and under the action of the metal skeleton surface catalyst, the raw gas The conversion continues and the reaction heat is released. Due to the moderate porosity, the temperature of the area where the intermediate porosity metal porous medium 8-12 is located continues to decrease; finally it comes into contact with the low porosity metal porous medium 8-13, and the catalyst on the surface of the metal skeleton Under the action, the raw material gas continues to transform and releases reaction heat. Due to the low porosity, the temperature of the area where the low-porosity metal porous medium 8-13 is located is relatively low. The areas where high porosity metal porous media 8-11, intermediate porosity metal porous media 8-12, and low porosity metal porous media 8-13 are located form a temperature field with gradually decreasing temperatures, which can achieve high reaction rates to high conversions efficient transition. Moreover, during the reaction process, the reaction heat in the first metal porous media layer 8-11, the second metal porous media layer 8-12, and the third metal porous media layer 8-13 are all transferred to the reactor shell through the flat heat pipe. In the external Martian atmosphere; finally, the converted reaction gas materials are collected from the gas outlet.

In addition, in another preferred embodiment of the present invention, a specific implementation method of the Sabatier reaction gas separation system 9 is further provided. As shown in Figure 4, its components include a reaction gas separation pipeline 9-1, a water vapor condenser 9-2, first gas-liquid separator 9-3, precooler 9-4, carbon dioxide condenser 9-5, second gas-liquid separator 9-6, methane liquefaction cold box 9-7, low-temperature refrigerator 9 -8. The third gas-liquid separator 9-9, the first low-temperature stop valve 9-10, the liquid methane return pipeline 9-12, the second low-temperature stop valve 9-13, and the third low-temperature stop valve 9-11.

The water vapor condenser 9-2, the precooler 9-4 and the carbon dioxide condenser 9-5 are respectively provided with a first passage and a second passage that constitute heat exchange contact;

The inlet end of the reaction gas separation pipeline 9-1 is used to pass into the Sabatier device reaction gas, and the outlet end is connected to the liquid methane storage tank 11. The reaction gas separation pipeline 9-1 is connected in sequence from the inlet end to the outlet end to the first passage of the water vapor condenser 9-2, the first gas-liquid separator 9-3, the first passage of the precooler 9-4, The first passage of the carbon dioxide condenser 9-5, the second gas-liquid separator 9-6, the heat exchange pipeline in the methane liquefaction cold box 9-7, the third gas-liquid separator 9-9 and the first low-temperature stop valve 9-10; The second passage of the water vapor condenser 9-2 and the precooler 9-4 is used to pass into the Martian atmosphere to cool the first passage; the methane liquefaction cold box 9-7 is provided with a low-temperature refrigerator 9 -8, and the cold head of the low-temperature refrigerator 9-8 forms heat exchange contact with the heat exchange pipeline in the methane liquefaction cold box 9-7, and the temperature of the cold head can liquefy the reaction gas in the Sabatier device flowing through the heat exchange pipeline. of methane.

The inlet end of the liquid methane return pipeline 9-12 is connected to the reaction gas separation pipeline 9-1 between the third gas-liquid separator 9-9 and the first low-temperature stop valve 9-10, and the outlet end is connected to the second gas-liquid separation pipeline. The reaction gas separation pipeline 9-1 between the reactor 9-6 and the methane liquefaction cold box 9-7. The liquid methane return pipeline 9-12 is connected in sequence from the inlet end to the outlet end of the second low temperature stop valve 9-13, the second passage of the carbon dioxide condenser 9-5 and the third low temperature stop valve 9-11.

The selection and specific form of each of the above components can be adjusted according to actual needs. In this embodiment, the low-temperature refrigerator 9-8 adopts a Stirling-type low-temperature refrigerator, and the first gas-liquid separator 9-3 and the second Both the gas-liquid separator 9-6 and the third gas-liquid separator 9-9 can be centrifugal gas-liquid separators. The water vapor condenser 9-2 and the precooler 9-4 adopt fin tube heat exchangers. The carbon dioxide condenser 9-5 uses a liquid-liquid plate heat exchanger. The heat exchange pipeline in the methane liquefaction cold box 9-7 is connected to the cold head of the low-temperature refrigerator 9-8 in the form of a coil, and the heat-conducting medium is filled between the two.

Based on the above-mentioned Sabatier reaction gas separation system 9, the specific process of component separation and liquefaction of the reaction gas of the Sabatier device is as follows:

Real-time monitoring of the Martian atmospheric temperature. When the Martian atmospheric temperature can condense the carbon dioxide in the reaction gas, the first operation mode is used to separate and liquefy the Sabatier device reaction gas. When the Martian atmospheric temperature cannot condense the carbon dioxide in the reaction gas, the second operation mode is used. Sabatier device separates and liquefies the reaction gas.

The first operating mode is as follows:

S11. Start the first gas-liquid separator 9-3, the second gas-liquid separator 9-6, the low-temperature refrigerator 9-8, and the third gas-liquid separator 9-9, and open the first low-temperature stop valve 9-10. Close the second low temperature stop valve 9-13 and the third low temperature stop valve 9-11; input the Martian atmosphere into the second passage of the water vapor condenser 9-2 and the second passage of the precooler 9-4 respectively through the fan, and then The respective first passages provide cooling capacity;

S12. Input the original reaction gas from the Sabatier device into the reaction gas separation pipeline 9-1, and adjust the Mars atmosphere flow rate input to the second passage of the water vapor condenser 9-2 so that the water vapor in the original reaction gas flows through the water vapor. During the first passage of the condenser 9-2, the cold energy of the Martian atmosphere is absorbed to complete the liquefaction, thereby becoming the first gas-liquid two-phase mixture not lower than 273.15K; the first gas-liquid two-phase mixture continues to enter the first gas-liquid mixture After the liquid water is separated and recovered in the separator 9-3, the first remaining reaction gas containing only three substances: carbon dioxide, methane and hydrogen is obtained;

S13. Continue to pass the first remaining reaction gas into the first passage of the precooler 9-4, and adjust the Martian atmosphere flow rate input to the second passage of the precooler 9-4 to absorb the carbon dioxide in the first remaining reaction gas. The coldness of the Martian atmosphere then liquefies, thus becoming a second gas-liquid two-phase mixture; the second gas-liquid two-phase mixture continues to pass through the first passage of the carbon dioxide condenser 9-5 and enters the second gas-liquid separator 9-6 for separation. Recover liquid carbon dioxide to obtain a second remaining reaction gas containing only methane and hydrogen;

S14. Continue to pass the second remaining reaction gas into the methane liquefaction cold box 9-7. By controlling the cold head temperature of the low-temperature refrigerator 9-8, the methane in the second remaining reaction gas is liquefied after exchanging heat with the cold head, thereby Becomes the third gas-liquid two-phase mixture; the third gas-liquid two-phase mixture continues to enter the third gas-liquid separator 9-9 to separate liquid methane and hydrogen, the hydrogen is directly discharged and recycled, while the liquid methane is stored in the liquid methane storage tank 11 in;

The second operating mode is as follows:

S21. Start the first gas-liquid separator 9-3, the second gas-liquid separator 9-6, the low-temperature refrigerator 9-8, and the third gas-liquid separator 9-9, and open the first low-temperature stop valve 9-10, The second low-temperature cut-off valve 9-13 and the third low-temperature cut-off valve 9-11 are used to input the Martian atmosphere into the second passage of the water vapor condenser 9-2 and the second passage of the precooler 9-4 respectively through the fan, thereby providing the respective The first passage provides cooling capacity;

S22. Input the original reaction gas from the Sabatier device into the reaction gas separation pipeline 9-1, and pass Adjust the flow rate of the Martian atmosphere input to the second passage of the water vapor condenser 9-2 so that the water vapor in the original reaction gas absorbs the cold energy of the Martian atmosphere and completes liquefaction when flowing through the first passage of the water vapor condenser 9-2, thus becoming It is the first gas-liquid two-phase mixture not lower than 273.15K; after the first gas-liquid two-phase mixture continues to enter the first gas-liquid separator 9-3 to separate and recover liquid water, it only contains three types of carbon dioxide, methane and hydrogen. The first remaining reactant gas of the substance;

S23. Continue to pass the first remaining reactant gas into the first passage of the precooler 9-4, and adjust the flow rate of the Martian atmosphere input into the second passage of the precooler 9-4 to cool the first remaining reactant gas to a temperature close to that of Mars. The temperature of the atmosphere then enters the first passage of the carbon dioxide condenser 9-5, continues to absorb the cooling capacity of the liquid methane in the second passage of the carbon dioxide condenser 9-5, and then completes the liquefaction of the carbon dioxide, thus becoming the second gas-liquid two-phase mixture. ; The second gas-liquid two-phase mixture continues to enter the second gas-liquid separator 9-6 to separate and recover liquid carbon dioxide, and obtain a second residual reaction gas containing only methane and hydrogen;

S24. After mixing the second remaining reaction gas with the endothermic vaporized methane in the liquid methane return line 9-12, continue to flow into the methane liquefaction cold box 9-7, by controlling the cold head temperature of the low-temperature refrigerator 9-8 , causing the methane in the second remaining reaction gas to liquefy after exchanging heat with the cold head, thereby becoming the third gas-liquid two-phase mixture; the third gas-liquid two-phase mixture continues to enter the third gas-liquid separator 9-9 to separate the liquid state Methane and hydrogen, hydrogen is directly discharged and recycled, while the liquid methane part is returned to the second passage of the carbon dioxide condenser 9-5 through the liquid methane return line 9-12 for liquefying carbon dioxide, and the remaining liquid methane is directly stored in the liquid methane storage Jar 11 in.

Finally, the present invention also provides a method for in-situ preparation of propellant for Mars surface launch vehicles using the integrated system shown in Figure 1, which includes the following steps:

S1. Enrich the Martian atmosphere and obtain high-purity carbon dioxide gas through the carbon dioxide capture system 7, and then transport the carbon dioxide to the Sabatier reduction system 8 through the liquid methane preparation pipeline 1;

S2. Transport the hydrated minerals on the surface of Mars to the water vapor extraction system 13 through the hydrated mineral transport system 12. The water vapor extraction system 13 extracts water vapor from the hydrated minerals and transports it to the electrolyzed water system 14;

S3. The electrolysis water system 14 electrolyzes water to produce hydrogen and oxygen. The hydrogen is transported to the Sabatier reduction system 8 through the hydrogen pipeline 5. The oxygen is divided into two outputs, and one is transported to the oxygen liquefaction through the liquid oxygen preparation pipeline 2. The system 15 liquefies the oxygen and stores it in the liquid oxygen storage tank 16 through the oxygen liquefaction system 15, and the other is transported to the life support system 10 through the oxygen pipeline 6;

S4, Sabatier reduction system 8 uses the carbon dioxide gas transported by the carbon dioxide capture system 7 and the hydrogen gas transported by the electrolysis water system 14 as raw materials, and generates methane and water through the Sabatier reaction under the action of the catalyst to generate four gases including methane, water vapor, carbon dioxide and hydrogen. The reaction gas of three components is transported to the Sabatier reaction gas separation system 9 to separate the four components. The separated carbon dioxide and hydrogen are returned to the Sabatier reduction system 8 and combined with the carbon dioxide gas and carbon dioxide gas transported by the carbon dioxide capture system 7 The hydrogen transmitted by the electrolyzed water system 14 is mixed and used as raw material gas again, and the separated methane is stored in the liquid methane storage tank 11 in the form of liquid methane. The separated water enters the electrolyzed water system 14 through the water vapor pipeline 4 and is combined with the water vapor extraction system. 13 The extracted water is electrolyzed together.

The above-described embodiment is only a preferred solution of the present invention, but it is not intended to limit the present invention. Those of ordinary skill in the relevant technical fields can also make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any technical solution obtained by adopting equivalent substitution or equivalent transformation shall fall within the protection scope of the present invention.

Claims (10)

1. An integrated system for in-situ preparation of propellant for Mars surface launch vehicles, characterized by including a liquid methane preparation pipeline (1), a liquid oxygen preparation pipeline (2), a mixed gas pipeline (3), and a water vapor pipeline (4 ), hydrogen pipeline (5) and oxygen pipeline (6);

   The liquid methane preparation pipeline (1) is connected in sequence to the carbon dioxide capture system (7), the Sabatier reduction system (8), the Sabatier reaction gas separation system (9) and the liquid methane storage tank (11);

   The liquid oxygen preparation pipeline (2) is connected in sequence to a water-containing mineral transport system (12), a water vapor extraction system (13), an electrolyzed water system (14), an oxygen liquefaction system (15) and a liquid oxygen storage tank (16);

   The mixed gas pipeline (3) connects the Sabatier reaction gas separation system (9) and the Sabatier reduction system (8);

   The water vapor pipeline (4) connects the Sabatier reaction gas separation system (9) and the electrolyzed water system (14);

   The hydrogen pipeline (5) connects the electrolytic water system (14) and the Sabatier reduction system (8);

   The oxygen pipeline (6) connects the electrolyzed water system (14) and external aerobic equipment;

   The carbon dioxide capture system (7) is used to capture carbon dioxide from the Martian atmosphere and input it into the Sabatier reduction system (8) as raw material;

   The Sabatier reduction system (8) is used to use carbon dioxide and hydrogen as raw materials to generate methane and water through Sabatier reduction reaction;

   The Sabatier reaction gas separation system (9) is used to separate the components of the reaction gas output from the Sabatier reduction system (8), and the separated unreacted carbon dioxide and hydrogen mixture is returned to the Sabatier reduction system through the mixed gas pipeline (3) (8) Reuse as raw material, the separated methane is stored in the liquid methane storage tank (11) in the form of liquid methane, and the separated water enters the electrolytic water system (14) through the water vapor pipeline (4);

   The water-containing mineral transport system (12) is used to input the water-containing minerals collected on Mars into the water vapor extraction system (13), and the water vapor extraction system (13) extracts the water and inputs it into the electrolyzed water system (14);

   The electrolytic water system (14) is used to electrolyze water to produce hydrogen and oxygen. The produced hydrogen is input into the Sabatier reduction system (8) through the hydrogen pipeline (5) as a raw material, and the produced oxygen is input all the way to oxygen liquefaction. The system (15) liquefies and stores it in the liquid oxygen storage tank (16), and the other line is input to external aerobic equipment through the oxygen pipeline (6).
2. The Mars surface launch vehicle propellant in-situ preparation integrated system as claimed in claim 1, wherein Characteristically, the carbon dioxide capture system (7) includes a carbon dioxide liquefaction pipeline (7-1), a first interstage cooler (7-4) and a second interstage cooler (7-8);

   The first intercooler (7-4) and the second intercooler (7-8) are both provided with a first passage and a second passage that constitute heat exchange contact;

   The inlet end of the carbon dioxide liquefaction pipeline (7-1) is used to pass into the Martian atmosphere, and the outlet end is connected to the low-temperature gas-liquid separator (7-11); the carbon dioxide liquefaction pipeline (7-1) runs from the inlet end to the outlet end. The filter (7-2), the electric heater (7-3), the first passage of the first-stage intercooler (7-4), the low-temperature fan (7-5), and the first-stage compressor are connected in sequence. (7-6), the second passage of the first-stage intercooler (7-4), the second-stage compressor (7-7), the first passage of the second-stage intercooler (7-8), water vapor Adsorber (7-9), carbon dioxide condenser (7-10) and low-temperature gas-liquid separator (7-11);

   The gas phase outlet of the low-temperature gas-liquid separator (7-11) is emptied, and the liquid phase outlet is connected to the second passage of the second-stage intercooler (7-8) through the output pipeline (7-12). The second passage outlet of the intercooler (7-8) is connected to the liquid methane preparation pipeline (1).
3. The Mars surface launch vehicle propellant in-situ preparation integrated system according to claim 1, characterized in that the Sabatier reduction system (8) includes an insulated reactor shell, and the reaction chamber inside the reactor shell is equipped with air inlet and outlet;

   The reaction chamber is divided into a high-temperature reaction zone (8-4) and a gradient temperature field reaction zone (8-5) through an annular insulated partition plate (8-10);

   The high-temperature reaction zone (8-4) has a built-in heater (8-9) for heating the raw material gas of the Sabatier reaction to the initial reaction temperature, and the surface of the heater (8-9) is coated with a Sabatier reaction catalyst;

   The gradient temperature field reaction zone (8-5) is sequentially provided with a first metal porous medium layer (8-11), a second metal porous medium layer (8-12) and a third metal porous medium layer along the air inlet direction. (8-13), and the porosity of the first metal porous dielectric layer (8-11), the second metal porous dielectric layer (8-12) and the third metal porous dielectric layer (8-13) decreases, and the medium surface is uniform Coated with Sabatier reaction catalyst; the three metal porous media layers all exchange heat with the external Martian atmosphere through flat heat pipes that penetrate the reactor shell, so that the Sabatier reaction heat in the three metal porous media layers can be transferred to the Martian atmosphere;

   After the raw material gas is introduced from the air inlet, it sequentially flows through the surface of the heater (8-9) in the high-temperature reaction zone (8-4) and the first heater in the gradient temperature field reaction zone (8-5). The metal porous dielectric layer (8-11), the second metal porous dielectric layer (8-12) and the third metal porous dielectric layer (8-13) are then discharged from the air outlet. out.
4. The Mars surface launch vehicle propellant in-situ preparation integrated system according to claim 1, characterized in that the Sabatier reaction gas separation system (9) includes a reaction gas separation pipeline (9-1), a water vapor condenser ( 9-2), precooler (9-4), carbon dioxide condenser (9-5) and liquid methane return line (9-12);

   The water vapor condenser (9-2), the precooler (9-4) and the carbon dioxide condenser (9-5) are respectively provided with a first passage and a second passage that constitute heat exchange contact;

   The inlet end of the reaction gas separation pipeline (9-1) is used to pass into the Sabatier device reaction gas, and the outlet end is connected to the liquid methane storage tank (11); the reaction gas separation pipeline (9-1) is from the inlet end to The outlet ends are connected in sequence to the first passage of the water vapor condenser (9-2), the first gas-liquid separator (9-3), the first passage of the precooler (9-4), and the carbon dioxide condenser (9- 5) of the first passage, the second gas-liquid separator (9-6), the heat exchange pipeline in the methane liquefaction cold box (9-7), the third gas-liquid separator (9-9) and the first low temperature The stop valve (9-10); the second passage of the water vapor condenser (9-2) and the precooler (9-4) are used to pass into the Martian atmosphere to cool the first passage; the methane liquefaction cold box (9 -7) is provided with a low-temperature refrigerator (9-8), and the cold head of the low-temperature refrigerator (9-8) forms heat exchange contact with the heat exchange pipeline in the methane liquefaction cold box (9-7), and the cold The head temperature can liquefy the methane in the reaction gas of the Sabatier device flowing through the heat exchange pipeline;

   The inlet end of the liquid methane return pipeline (9-12) is connected to the reaction gas separation pipeline (9-1) between the third gas-liquid separator (9-9) and the first low-temperature stop valve (9-10) ), the outlet end is connected to the reaction gas separation pipeline (9-1) between the second gas-liquid separator (9-6) and the methane liquefaction cold box (9-7); the liquid methane return pipeline (9-12) The second low temperature stop valve (9-13), the second passage of the carbon dioxide condenser (9-5) and the third low temperature stop valve (9-11) are connected in sequence from the inlet end to the outlet end.
5. The integrated system for in-situ preparation of propellant for Mars surface launch vehicles according to claim 1, characterized in that, in the oxygen liquefaction system (15), the cold energy of the Martian atmosphere is used to pre-cool the oxygen, and then the oxygen is pre-cooled through low-temperature cooling. The machine cools and liquefies the oxygen.
6. The integrated system for in-situ preparation of propellant for Mars surface launch vehicles according to claim 5, wherein the cryogenic refrigerator is a Stirling cryogenic refrigerator.
7. The Mars surface launch vehicle propellant in-situ preparation integrated system according to claim 1, characterized in that the water vapor extraction system (13) is a microwave heating device, and pure water vapor is obtained by microwave heating of water-containing minerals.
8. The Mars surface launch vehicle propellant in-situ preparation integrated system as claimed in claim 1, wherein The characteristic is that the electrolyzed water system (14) adopts a photocatalytic assisted water electrolyzed system.
9. The Mars surface launch vehicle propellant in-situ integrated preparation system according to claim 1, characterized in that the external aerobic equipment is a life support system (10).
10. A method for in-situ preparation of Mars surface launch vehicle propellant using the system according to any one of claims 1 to 9, characterized in that it includes:

    S1. Enrich the Martian atmosphere and obtain high-purity carbon dioxide gas through the carbon dioxide capture system (7), and then transport the carbon dioxide to the Sabatier reduction system (8) through the liquid methane preparation pipeline (1);

    S2. Transport the hydrated minerals on the surface of Mars to the water vapor extraction system (13) through the hydrated mineral transport system (12). The water vapor extraction system (13) extracts water vapor from the hydrated minerals and transports it to the electrolyzed water system. (14);

    S3. The electrolysis water system (14) electrolyzes water to produce hydrogen and oxygen. The hydrogen is transported to the Sabatier reduction system (8) through the hydrogen pipeline (5). The oxygen is divided into two outputs, one of which passes through the liquid oxygen preparation pipe. The oxygen liquefaction system (15) liquefies the oxygen and stores it in the liquid oxygen storage tank (16), and the other is transported to the life support system (10) through the oxygen pipeline (6). );

    S4. The Sabatier reduction system (8) uses the carbon dioxide gas transported by the carbon dioxide capture system (7) and the hydrogen gas transported by the electrolysis water system (14) as raw materials. Under the action of the catalyst, methane and water are generated through the Sabatier reaction to generate methane, The reaction gas consists of four components: water vapor, carbon dioxide and hydrogen. The reaction gas is transported to the Sabatier reaction gas separation system (9) to separate the four components. The separated carbon dioxide and hydrogen are returned to the Sabatier reduction system (8) and combined with The carbon dioxide gas delivered by the carbon dioxide capture system (7) and the hydrogen delivered by the electrolytic water system (14) are mixed and reused as raw material gas, and the separated methane is stored in the liquid methane storage tank (11) in the form of liquid methane. Water enters the electrolytic water system (14) through the water vapor pipeline (4) and is electrolyzed together with the water extracted by the water vapor extraction system (13).