WO2024041146A1 - Integrated system and method for mars surface carrier rocket propellant in-situ preparation - Google Patents
Integrated system and method for mars surface carrier rocket propellant in-situ preparation Download PDFInfo
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- WO2024041146A1 WO2024041146A1 PCT/CN2023/101629 CN2023101629W WO2024041146A1 WO 2024041146 A1 WO2024041146 A1 WO 2024041146A1 CN 2023101629 W CN2023101629 W CN 2023101629W WO 2024041146 A1 WO2024041146 A1 WO 2024041146A1
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- Prior art keywords
- pipeline
- sabatier
- carbon dioxide
- water
- gas
- Prior art date
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- 238000002360 preparation method Methods 0.000 title claims abstract description 58
- 239000003380 propellant Substances 0.000 title claims abstract description 44
- 238000011065 in-situ storage Methods 0.000 title claims abstract description 25
- 238000000034 method Methods 0.000 title claims abstract description 24
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 claims abstract description 260
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 231
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 196
- 239000007788 liquid Substances 0.000 claims abstract description 135
- 239000001569 carbon dioxide Substances 0.000 claims abstract description 130
- 229910002092 carbon dioxide Inorganic materials 0.000 claims abstract description 130
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 67
- 239000001301 oxygen Substances 0.000 claims abstract description 67
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 67
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims abstract description 36
- 229910052500 inorganic mineral Inorganic materials 0.000 claims abstract description 35
- 239000011707 mineral Substances 0.000 claims abstract description 35
- 238000005868 electrolysis reaction Methods 0.000 claims abstract description 19
- 229910052751 metal Inorganic materials 0.000 claims description 83
- 239000002184 metal Substances 0.000 claims description 83
- 238000006243 chemical reaction Methods 0.000 claims description 78
- 239000012495 reaction gas Substances 0.000 claims description 78
- 239000007789 gas Substances 0.000 claims description 68
- 239000001257 hydrogen Substances 0.000 claims description 62
- 229910052739 hydrogen Inorganic materials 0.000 claims description 62
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 60
- 238000006722 reduction reaction Methods 0.000 claims description 57
- 230000009467 reduction Effects 0.000 claims description 50
- 238000000926 separation method Methods 0.000 claims description 50
- 239000002994 raw material Substances 0.000 claims description 41
- 238000003860 storage Methods 0.000 claims description 32
- 238000000605 extraction Methods 0.000 claims description 27
- 230000032258 transport Effects 0.000 claims description 27
- 239000000203 mixture Substances 0.000 claims description 19
- 239000012071 phase Substances 0.000 claims description 16
- 238000010438 heat treatment Methods 0.000 claims description 11
- 239000003054 catalyst Substances 0.000 claims description 10
- 239000007809 chemical reaction catalyst Substances 0.000 claims description 10
- 230000009471 action Effects 0.000 claims description 9
- 238000001816 cooling Methods 0.000 claims description 6
- 230000007423 decrease Effects 0.000 claims description 6
- 239000000284 extract Substances 0.000 claims description 6
- 238000005192 partition Methods 0.000 claims description 4
- 230000001699 photocatalysis Effects 0.000 claims description 4
- 239000007791 liquid phase Substances 0.000 claims description 3
- 235000015842 Hesperis Nutrition 0.000 abstract 1
- 235000012633 Iberis amara Nutrition 0.000 abstract 1
- 239000010410 layer Substances 0.000 description 57
- 238000009833 condensation Methods 0.000 description 7
- 230000005494 condensation Effects 0.000 description 7
- 238000001704 evaporation Methods 0.000 description 6
- 230000008020 evaporation Effects 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 230000003247 decreasing effect Effects 0.000 description 5
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- 150000002431 hydrogen Chemical class 0.000 description 5
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- 238000001179 sorption measurement Methods 0.000 description 4
- 239000012535 impurity Substances 0.000 description 3
- 239000012774 insulation material Substances 0.000 description 3
- 238000005065 mining Methods 0.000 description 3
- 239000000376 reactant Substances 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- 239000003463 adsorbent Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
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- 238000010992 reflux Methods 0.000 description 2
- 239000004215 Carbon black (E152) Substances 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 229910001882 dioxygen Inorganic materials 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
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- 239000000446 fuel Substances 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
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- 229910052757 nitrogen Inorganic materials 0.000 description 1
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 1
- 238000007146 photocatalysis Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06D—MEANS FOR GENERATING SMOKE OR MIST; GAS-ATTACK COMPOSITIONS; GENERATION OF GAS FOR BLASTING OR PROPULSION (CHEMICAL PART)
- C06D5/00—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets
- C06D5/08—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more liquids
-
- C—CHEMISTRY; METALLURGY
- C07—ORGANIC CHEMISTRY
- C07C—ACYCLIC OR CARBOCYCLIC COMPOUNDS
- C07C1/00—Preparation of hydrocarbons from one or more compounds, none of them being a hydrocarbon
- C07C1/02—Preparation of hydrocarbons from one or more compounds, none of them being a hydrocarbon from oxides of a carbon
- C07C1/12—Preparation of hydrocarbons from one or more compounds, none of them being a hydrocarbon from oxides of a carbon from carbon dioxide with hydrogen
-
- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25B—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES FOR THE PRODUCTION OF COMPOUNDS OR NON-METALS; APPARATUS THEREFOR
- C25B1/00—Electrolytic production of inorganic compounds or non-metals
- C25B1/01—Products
- C25B1/02—Hydrogen or oxygen
- C25B1/04—Hydrogen or oxygen by electrolysis of water
-
- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25B—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES FOR THE PRODUCTION OF COMPOUNDS OR NON-METALS; APPARATUS THEREFOR
- C25B15/00—Operating or servicing cells
- C25B15/08—Supplying or removing reactants or electrolytes; Regeneration of electrolytes
- C25B15/081—Supplying products to non-electrochemical reactors that are combined with the electrochemical cell, e.g. Sabatier reactor
-
- C—CHEMISTRY; METALLURGY
- C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
- C25B—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES FOR THE PRODUCTION OF COMPOUNDS OR NON-METALS; APPARATUS THEREFOR
- C25B15/00—Operating or servicing cells
- C25B15/08—Supplying or removing reactants or electrolytes; Regeneration of electrolytes
- C25B15/083—Separating products
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/30—Hydrogen technology
- Y02E60/36—Hydrogen production from non-carbon containing sources, e.g. by water electrolysis
Definitions
- 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.
- 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.
- 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.
- 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 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.
- the other line is input to the external aerobic equipment through the oxygen pipeline.
- 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 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.
- 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;
- the raw material gas 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.
- 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.
- 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.
- the cryogenic refrigerator is a Stirling cryogenic refrigerator.
- the water vapor extraction system is a microwave heating device, which obtains pure water vapor by microwave heating of water-containing minerals.
- the water electrolysis system adopts a photocatalytic assisted water electrolysis system.
- the external aerobic equipment is a life support system.
- 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:
- 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;
- 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.
- the present invention 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.
- 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.
- 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
- 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 .
- 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.
- 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.
- carbon dioxide in the Martian atmosphere can be used to prepare liquid methane propellant
- 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.
- 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.
- 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.
- 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 .
- 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.
- the oxygen storage tank 16 the other line is input to the life support system 10 through the oxygen pipeline 6.
- 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.
- 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.
- pressure can also be assisted during the oxygen cooling and liquefaction process to improve the liquefaction efficiency.
- 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.
- 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.
- 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.
- 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.
- 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.
- 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.
- a specific implementation of the carbon dioxide capture system 7 is further provided.
- 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.
- 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 filter is preferably an electrostatic precipitator
- the first-stage compressor 7-6 and the second-stage compressor 7-7 can be a positive displacement compressor.
- 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 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
- 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.
- a specific implementation method of the Sabatier reduction system 8 is further provided.
- 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 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 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 As shown in Figure 3, its components include a Saba
- 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.
- the Sabatier reaction 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.
- 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.
- 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.
- 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.
- 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.
- 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.
- 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 raw material gas is passed into the reaction chamber inside the reactor shell from the air inlet.
- 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.
- the Sabatier reaction rate in the high-temperature reaction zone 8-4 is higher, but the conversion rate of the feed gas is lower.
- 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.
- 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.
- 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.
- 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.
- a specific implementation method of the Sabatier reaction gas separation system 9 is further provided.
- 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 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 methan
- 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 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 low-temperature refrigerator 9-8 adopts a Stirling-type low-temperature refrigerator
- 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.
- the first operation mode is used to separate and liquefy the Sabatier device reaction gas.
- the second operation mode is used.
- Sabatier device separates and liquefies the reaction gas.
- the first operating mode is as follows:
- the second operating mode is as follows:
- 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:
- 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;
- 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.
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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
本发明涉及火星探测技术领域,具体涉及一种火星表面运载火箭推进剂原位制备一体化系统及方法。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.
火星推进剂原位制备是指勘探、获取和利用火星的天然资源在火星上原地制备运载火箭推进剂,是一种可持续性强和成本低的深空探测解决方案,能够有效降低对携带资源和地球补给的依赖,是实现地外载人探测和未来太空殖民等地外活动的关键技术手段。火星表面大气的主要成分是二氧化碳,占总量的95.32%,是最具潜力的火星推进剂原位制备原料。根据NASA计算,载人火星探测需要在16个月内生产7吨甲烷推进剂和23吨液氧推进剂,以及5吨氧气用于生命维持,共计35吨。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.
然而由于暂未有返回式的火星探索活动,所以火星表面推进剂原位制备仍然处于技术探索阶段,包括利用火星大气中的二氧化碳制备甲烷、煤油等碳氢燃料推进剂,但目前仍未有十分明确的技术方案。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.
发明内容Contents of the invention
本发明的目的在于解决现有技术中难以制备满足载人火星探测需要的推进剂原料的问题,并提供一种火星表面运载火箭推进剂原位制备一体化系统及方法。本发明利用火星大气中的二氧化碳制备液态甲烷推进剂,通过电解火星含水矿物质中的水来制备液氧推进剂,实现液态甲烷推进剂和液氧推进剂的同步高效制备。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.
本发明所采用的具体技术方案如下:The specific technical solutions adopted by the present invention are as follows:
第一方面,本发明提供了一种火星表面运载火箭推进剂原位制备一体化系统,其包括液态甲烷制备管路、液氧制备管路、混合气管路、水汽管路、氢气管路和氧气管路;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;
所述液态甲烷制备管路依次连接二氧化碳捕集系统、Sabatier还原系统、
Sabatier反应气分离系统和液态甲烷储罐;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;
所述液氧制备管路依次连接含水矿物质输送系统、水汽提取系统、电解水系统、氧气液化系统和液氧储罐;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;
所述混合气管路连接Sabatier反应气分离系统和Sabatier还原系统;The mixed gas pipeline is connected to the Sabatier reaction gas separation system and the Sabatier reduction system;
所述水汽管路连接Sabatier反应气分离系统和电解水系统;The water vapor pipeline connects the Sabatier reaction gas separation system and the electrolyzed water system;
所述氢气管路连接电解水系统和Sabatier还原系统;The hydrogen pipeline connects the electrolyzed water system and the Sabatier reduction system;
所述氧气管路连接电解水系统和外部需氧设备;The oxygen pipeline connects the electrolyzed water system and external aerobic equipment;
所述二氧化碳捕集系统用于从火星大气中捕集二氧化碳,并输入Sabatier还原系统中作为原料;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;
所述Sabatier还原系统用于以二氧化碳和氢气作为原料,通过Sabatier还原反应生成甲烷和水;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;
所述Sabatier反应气分离系统用于对Sabatier还原系统输出的反应气进行组分分离,分离得到的未反应的二氧化碳和氢气混合物通过混合气管路返回至Sabatier还原系统重新作为原料,分离得到的甲烷以液态甲烷形式存储于液态甲烷储罐中,分离得到的水通过水汽管路进入电解水系统中;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;
所述含水矿物质输送系统用于将火星上采集的含水矿物输入水汽提取系统,由水汽提取系统提取其中的水分并输入电解水系统中;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;
所述电解水系统用于对水进行电解制取氢气和氧气,制取的氢气通过氢气管路输入Sabatier还原系统中作为原料,制取的氧气一路输入氧气液化系统进行液化后存储至液氧储罐中,另一路通过氧气管路输入外部需氧设备。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.
作为上述第一方面的优选,所述二氧化碳捕集系统包括二氧化碳液化管路、第一级间冷却器和第二级间冷却器;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;
所述第一级间冷却器和第二级间冷却器中均设有构成换热接触的第一通路和第二通路;The first intercooler and the second intercooler are each provided with a first passage and a second passage forming heat exchange contact;
所述二氧化碳液化管路的入口端用于通入火星大气,出口端连接低温气液分离器;二氧化碳液化管路在入口端至出口端之间依次连接过滤器、电加热器、第一级间冷却器的第一通路、低温风机、第一级压缩机、第一级间冷却器的第二通路、第二级压缩机、第二级间冷却器的第一通路、水汽吸附器、二氧化碳冷凝器和低温气液分离器;
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;
所述低温气液分离器的气相出口排空,液相出口通过输出管路连接第二级间冷却器的第二通路,第二级间冷却器的第二通路出口与所述液态甲烷制备管路连接。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.
作为上述第一方面的优选,所述Sabatier还原系统包括绝热的反应器壳体,反应器壳体内部的反应腔设有进气口和出气口;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;
所述反应腔通过环形的绝热分隔板分为高温反应区和梯度温度场反应区;The reaction chamber is divided into a high-temperature reaction zone and a gradient temperature field reaction zone through an annular insulated partition plate;
所述高温反应区内置有用于将Sabatier反应的原料气加热到初始反应温度的加热器,加热器表面涂敷有Sabatier反应催化剂;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;
所述梯度温度场反应区中沿进气方向依次设有第一金属多孔介质层、第二金属多孔介质层和第三金属多孔介质层,且第一金属多孔介质层、第二金属多孔介质层和第三金属多孔介质层的孔隙率递减,介质表面均涂敷有Sabatier反应催化剂;三层金属多孔介质层均通过贯通反应器壳体的平板式热管与外部火星大气构成换热,使三层金属多孔介质层中的Sabatier反应热能够传递至火星大气;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;
所述原料气从所述进气口通入后,依次流经高温反应区中的加热器表面以及梯度温度场反应区中的第一金属多孔介质层、第二金属多孔介质层和第三金属多孔介质层,再从所述出气口排出。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.
作为上述第一方面的优选,所述Sabatier反应气分离系统包括反应气分离管路、水汽冷凝器、预冷器、二氧化碳冷凝器和液态甲烷回流管路;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;
其中水汽冷凝器、预冷器和二氧化碳冷凝器中分别设有构成换热接触的第一通路和第二通路;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;
所述反应气分离管路的入口端用于通入Sabatier装置反应气,出口端接入液态甲烷储罐;反应气分离管路从入口端到出口端之间依次连接水汽冷凝器的第一通路、第一气液分离器、预冷器的第一通路、二氧化碳冷凝器的第一通路、第二气液分离器、甲烷液化冷箱中的换热管路、第三气液分离器和第一低温截止阀;水汽冷凝器和预冷器的第二通路均用于通入火星大气从而对第一通路进行冷却;甲烷液化冷箱上设有低温冷机,且低温冷机的冷头与甲烷液化冷箱中的换热管路构成换热接触,且冷头温度能液化流经换热管路的Sabatier装置反应气内的甲烷;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;
所述液态甲烷回流管路的入口端连接第三气液分离器和第一低温截止阀之间的反应气分离管路,出口端连接第二气液分离器和甲烷液化冷箱之间的反应气
分离管路;液态甲烷回流管路从入口端到出口端之间依次连接第二低温截止阀、二氧化碳冷凝器的第二通路和第三低温截止阀。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.
作为上述第一方面的优选,所述氧气液化系统中预先利用火星大气的冷能对氧气进行预冷,然后通过低温冷机对氧气进行降温液化。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.
作为上述第一方面的优选,所述低温冷机为斯特林低温冷机。As a preference of the above first aspect, the cryogenic refrigerator is a Stirling cryogenic refrigerator.
作为上述第一方面的优选,所述水汽提取系统为微波加热装置,通过对含水矿物质进行微波加热的方式获取纯净水汽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.
作为上述第一方面的优选,所述电解水系统采用光催化辅助的电解水系统。As a preferred option of the above first aspect, the water electrolysis system adopts a photocatalytic assisted water electrolysis system.
作为上述第一方面的优选,所述外部需氧设备为生命维持系统。As a preferred aspect of the above first aspect, the external aerobic equipment is a life support system.
第二方面,本发明提供了一种利用上述第一方面任一方案所述系统的火星表面运载火箭推进剂原位制备方法,其包括: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、通过二氧化碳捕集系统富集火星大气并获取高纯的二氧化碳气体,随后将二氧化碳通过液态甲烷制备管路输送至Sabatier还原系统;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、通过含水矿物质输送系统将火星表面的含水矿物质输送至水汽提取系统,由水汽提取系统从含水矿物质中提取水汽,并将其输送至电解水系统;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、电解水系统对水进行电解,制取氢气和氧气,氢气通过氢气管路输送至Sabatier还原系统中,氧气分为两条输出,一条通过液氧制备管路输送至氧气液化系统并由氧气液化系统将氧气液化后存储至液氧储罐,另一条通过氧气管路输送至生命维持系统;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、Sabatier还原系统利用二氧化碳捕集系统输送的二氧化碳气体和电解水系统传输的氢气作为原料,在催化剂的作用下通过Sabatier反应生成甲烷和水,生成包含甲烷、水汽、二氧化碳和氢气四种组分的反应气,反应气输送至Sabatier反应气分离系统中对四种组分进行分离,其中分离的二氧化碳和氢气返回Sabatier还原系统中,与二氧化碳捕集系统输送的二氧化碳气体和电解水系统传输的氢气混合重新作为原料气,而分离得到的甲烷以液态甲烷形式存储于液态甲烷储罐中,分离得到的水通过水汽管路进入电解水系统中与水汽提取系统提取的水一起进行电解。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.
本发明相比现有技术突出且有益的技术效果是:提出了一种火星表面运载火箭推进剂原位制备一体化系统,可以实现运载火箭所需推进剂的同步制备;利用
火星大气中的二氧化碳制备甲烷推进剂,利用火星含水矿物质中的水电解制备液氧推进剂以及生命维持系统所需的氧气,与液氧甲烷运载火箭和火星探测任务需求的契合度高;根据计算,每通过还原反应获取1kg甲烷,对应的产物水即可通过电解获取2kg氧气,本发明将液态甲烷制备过程的产物水输送至电解水系统,所以可使含水矿物质的开采量减少一半,即将火星二氧化碳中的氧元素作为液氧推进剂的重要来源。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.
以下将结合附图对本发明的构思、具体结构及产生的技术效果做进一步说明,以充分的了解本发明的目的、特征和效果。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.
图1为一种火星表面运载火箭推进剂原位制备一体化系统的结构示意图;Figure 1 is a schematic structural diagram of an integrated system for in-situ preparation of propellant for Mars surface launch vehicles;
图2为二氧化碳捕集系统的一种优选方式示意图;Figure 2 is a schematic diagram of a preferred method of a carbon dioxide capture system;
图3为Sabatier还原系统的一种优选方式示意图;Figure 3 is a schematic diagram of a preferred method of the Sabatier reduction system;
图4为Sabatier反应气分离系统的一种优选方式示意图。Figure 4 is a schematic diagram of a preferred method of the Sabatier reaction gas separation system.
图中附图标记为:液态甲烷制备管路1、液氧制备管路2、二氧化碳/氢气混合管路3、水汽管路4、氢气管路5、氧气管路6、二氧化碳捕集系统7、Sabatier还原系统8、Sabatier反应气分离系统9、生命维持系统10、液态甲烷储罐11、含水矿物质开采系统12、水汽提取系统13、电解水系统14、氧气液化系统15、液氧储罐16。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 .
下面结合附图和具体实施方式对本发明做进一步阐述和说明。本发明中各个实施方式的技术特征在没有相互冲突的前提下,均可进行相应组合。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.
为使本发明的上述目的、特征和优点能够更加明显易懂,下面结合附图对本发明的具体实施方式做详细的说明。在下面的描述中阐述了很多具体细节以便于充分理解本发明。但是本发明能够以很多不同于在此描述的其它方式来实施,本领域技术人员可以在不违背本发明内涵的情况下做类似改进,因此本发明不受下面公开的具体实施例的限制。本发明各个实施例中的技术特征在没有相互冲突的前提下,均可进行相应组合。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.
在本发明的描述中,需要理解的是,当一个元件被认为是“连接”另一个元件,可以是直接连接到另一个元件或者是间接连接即存在中间元件。相反,当元件为
称作“直接”与另一元件连接时,不存在中间元件。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.
在本发明的描述中,需要理解的是,术语“第一”、“第二”仅用于区分描述目的,而不能理解为指示或暗示相对重要性或者隐含指明所指示的技术特征的数量。由此,限定有“第一”、“第二”的特征可以明示或者隐含地包括至少一个该特征。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.
如图1所示,在本发明的一个较佳实施例中,提供了一种火星表面运载火箭推进剂原位制备一体化系统,其组成元件包括液态甲烷制备管路1、液氧制备管路2、二氧化碳/氢气混合管路3、水汽管路4、氢气管路5、氧气管路6、二氧化碳捕集系统7、Sabatier还原系统8、Sabatier反应气分离系统9、生命维持系统10、液态甲烷储罐11、含水矿物质开采系统12、水汽提取系统13、电解水系统14、氧气液化系统15、液氧储罐16。该系统中可利用火星大气中的二氧化碳制备液态甲烷推进剂,通过电解火星含水矿物质中的水来制备液氧推进剂,实现液态甲烷推进剂和液氧推进剂的同步高效制备。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.
整个系统中,各子系统是通过液态甲烷制备管路1、液氧制备管路2、混合气管路3、水汽管路4、氢气管路5和氧气管路6来连接,从而实现协同工作的。其中,液态甲烷制备管路1依次连接二氧化碳捕集系统7、Sabatier还原系统8、Sabatier反应气分离系统9和液态甲烷储罐11。液氧制备管路2依次连接含水矿物质输送系统12、水汽提取系统13、电解水系统14、氧气液化系统15和液氧储罐16。混合气管路3连接Sabatier反应气分离系统9和Sabatier还原系统8。水汽管路4连接Sabatier反应气分离系统9和电解水系统14。氢气管路5连接电解水系统14和Sabatier还原系统8。氧气管路6连接电解水系统14和外部需氧设备。外部需氧设备可以是火星上需要好氧的任意设备,在本实施例中外部需氧设备为火星上的生命维持系统10。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.
上述一体化系统中除管路和存储罐体之外的各子系统,是实现该一体化系统功能的关键。下面分别对各自的功能和配合关系进行描述。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.
二氧化碳捕集系统7用于从火星大气中捕集二氧化碳,并输入Sabatier还原系统8中作为原料。由于火星大气中95%以上的组分是二氧化碳,因此二氧化碳捕集系统7可以利用火星大气为原料,以吸附法、冷冻法等方式从中获取二氧化碳。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还原系统8用于以二氧化碳和氢气作为原料,通过Sabatier还原反
应生成甲烷和水。Sabatier还原系统8是一种在航天设备中常见的装置,其能够通过Sabatier还原反应来制取甲烷。Sabatier还原系统8理论上可采用任意的Sabatier反应装置来实现。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.
Sabatier反应气分离系统9用于对Sabatier还原系统8输出的反应气进行组分分离,分离得到的未反应的二氧化碳和氢气混合物通过混合气管路3返回至Sabatier还原系统8重新作为原料,分离得到的甲烷以液态甲烷形式存储于液态甲烷储罐11中,分离得到的水通过水汽管路4进入电解水系统14中。Sabatier反应气分离系统9中对于不同组分的分离,可以利用不同组分之间的液化温度差异来进行逐级分离。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.
含水矿物质输送系统12用于将火星上采集的含水矿物输入水汽提取系统13,由水汽提取系统13提取其中的水分并输入电解水系统14中。含水矿物质输送系统12可以采用任意的传送设备,而且其前端可以连接含水矿物质采集装置。水汽提取系统13优选采用微波加热装置,通过对含水矿物质进行微波加热的方式获取纯净水汽。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.
电解水系统14用于对水进行电解制取氢气和氧气,制取的氢气通过氢气管路5输入Sabatier还原系统8中作为原料,制取的氧气一路输入氧气液化系统15进行液化后存储至液氧储罐16中,另一路通过氧气管路6输入生命维持系统10。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.
在本发明中,电解水系统14可以是任意现有技术中的电解水制取氢气和氧气的装置。考虑到电解水的效率,可以在传统装置基础上配置光催化等辅助系统,充分利用太阳能提升系统运行效率,即电解水系统14可采用光催化辅助的电解水系统。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.
在本发明中,氧气液化系统15中预先利用火星大气的冷能对氧气进行预冷,然后通过低温冷机对氧气进行降温液化。具体采用的低温冷机优选为采用体积小、质量轻的斯特林低温冷机。当然,在氧气降温液化过程中也可以辅助进行加压,以提高液化效率。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.
上述火星表面运载火箭推进剂原位制备一体化系统的运行流程如下:The operation process of the above-mentioned Mars surface launch vehicle propellant in-situ preparation integrated system is as follows:
(1)二氧化碳捕集系统7富集火星大气并获取高纯的二氧化碳气体,随后将二氧化碳通过液态甲烷制备管路1输送至Sabatier还原系统8。(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)Sabatier还原系统8包含三条输入,分别为二氧化碳捕集系统7输送的二
氧化碳气体、电解水系统14传输的氢气和Sabatier反应气分离系统9输送的二氧化碳和氢气的混合气,随后二氧化碳和氢气在催化剂的作用下生成甲烷和水,由于Sabatier反应的转化率受温度影响,所以二氧化碳和氢气不会完全反应,Sabatier还原系统8输送至Sabatier反应气分离系统9的反应气包含甲烷、水汽、二氧化碳和氢气四种物质。(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)Sabatier反应气分离系统9进行反应气分离,随后将未反应的二氧化碳和氢气通过二氧化碳/氢气混合管路3输送至Sabatier还原系统8进行再次反应,将水汽通过水汽管路4输送至电解水系统14进行电解,将甲烷以液态甲烷形式输送至液态甲烷储罐11进行存储。(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)含水矿物质输送系统12开采火星表面的含水矿物质,初步处理后将其输送至水汽提取系统13,水汽提取系统13采用微波加热等方式处理含水矿物质,获取纯度符合要求的水汽,并将其输送至电解水系统14。(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)电解水系统14包含两条输入,分别为水汽提取系统13输送的矿物质提取水和Sabatier反应气分离系统9输送的产物水,随后水会电解为氢气和氧气,氢气通过氢气管路5输送至Sabatier还原系统8参与还原反应,氧气分为两条输出,一条通过液氧制备管路2输送至氧气液化系统15,另一条通过氧气管路6输送至生命维持系统10。(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)氧气液化系统15将电解水系统14提供的氧气完成液化,并将液氧输送至液氧储罐16进行存储。(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.
另外在本发明的另一优选实施例中,进一步提供了一种二氧化碳捕集系统7的具体实现方式,如图2所示,其组成元件包括过滤器7-2、电加热器7-3、第一级间冷却器7-4、低温风机7-5、第一级压缩机7-6、第二级压缩机7-7、第二级间冷却器7-8、水汽吸附器7-9、二氧化碳冷凝器7-10、低温气液分离器7-11和输出管路7-12。各组成元件之间的连接关系如下: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:
第一级间冷却器7-4和第二级间冷却器7-8中均设有构成换热接触的第一通路和第二通路。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.
二氧化碳液化管路7-1的入口端用于通入火星大气,出口端连接低温气液分离器7-11;二氧化碳液化管路7-1在入口端至出口端之间依次连接过滤器7-2、电加热器7-3、第一级间冷却器7-4的第一通路、低温风机7-5、第一级压缩机
7-6、第一级间冷却器7-4的第二通路、第二级压缩机7-7、第二级间冷却器7-8的第一通路、水汽吸附器7-9、二氧化碳冷凝器7-10和低温气液分离器7-11。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.
低温气液分离器7-11的气相出口排空,液相出口通过输出管路7-12连接第二级间冷却器7-8的第二通路,第二级间冷却器7-8的第二通路出口与所述液态甲烷制备管路1连接。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.
上述各设备的选型可根据实际需要调整,在本实施例中,过滤器优选采用静电除尘设备,第一级压缩机7-6和第二级压缩机7-7可采用容积式压缩机,且第二级压缩机7-7出口压力应高于二氧化碳的三相点压力。低温气液分离器7-11可采用离心式气液分离器。第一级间冷却器7-4和第二级间冷却器7-8可采用气-气板式换热器。二氧化碳冷凝器7-10可采用翅片管式换热器,其冷源可以是低于二氧化碳冷凝温度的夜间火星大气,或者在火星大气温度高于二氧化碳冷凝温度时亦可采用其他低温工质进行辅助。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.
基于上述二氧化碳捕集系统7进行火星表面二氧化碳连续捕集的具体方法如下: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:
依次启动电加热器7-3、低温风机7-5、第一级压缩机7-6、第二级压缩机7-7和低温气液分离器7-11,使火星大气在低温风机7-5的作用下进入二氧化碳液化管路7-1,首先流经过滤器7-2去除灰尘等杂质变成纯净原料气,随后依次进入电加热器7-3和第一级间冷却器7-4的第一通路进行预热。特别需要注意的是,电加热器7-3仅在系统启动时开启,在稳定运行后由第一级间冷却器7-4提供预热所需的热量,电加热器3可以无需开启。预热完成后的原料气在低温风机7-5牵引下进入第一级压缩机7-6中完成第一次增压,形成一次增压原料气。增压完成后的一次增压原料气温度会急剧上升,高温的一次增压原料气进入第一级间冷却器7-4的第二通路,与第一级间冷却器7-4的第一通路中未预热的原料气进行换热冷却后,再进入第二级压缩机7-7进行第二次增压,得到二次增压原料气。增压完成后的二次增压原料气温度又会急剧上升,高温的二次增压原料气进入第二级间冷却器7-8的第一通路,与第二级间冷却器7-8的第一通路中流入的液态二氧化碳进行换热冷却,得到温度维持在273.15K以上的原料气继续进入二氧化碳液化管路7-1中的水汽吸附器7-9去除水汽,得到高纯二氧化碳原料气。高纯二氧化碳原料气继续进入二氧化碳冷凝器7-10中对二氧化碳进行液化,但此
时进队二氧化碳进行液化,二氧化碳原料气中可能还有部分液化温度较低的杂质气如氮气和氩气等尚未液化,因此自二氧化碳冷凝器7-10流出的是。气液两相混合物进入低温气液分离器7-11进行气液分离,杂质气直接排出,液态二氧化碳则通过输出管路7-12输入第二级间冷却器7-8的第二通路,与二次增压原料气换热后重新汽化,进入液态甲烷制备管路1中用于进行后续的Sabatier反应。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.
水汽吸附器7-9中可填充的吸附剂为三氧化二铝等对水有强吸附能力的吸附剂。但水汽吸附器7-9运行一段时间后可能会出现吸附饱和,可临时进行停机,更换水汽吸附器7-9或者对内部吸附介质进行加热再生。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.
另外需要注意的是,进入液态甲烷制备管路1的二氧化碳气体,如果压力没有达到后续反应要求,则需要进行增压,具体增压方式属于现有技术。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.
另外在本发明的另一优选实施例中,进一步提供了一种Sabatier还原系统8的具体实现方式,如图3所示,其组成元件包括Sabatier反应器外壳8-1、绝热材料8-2、Sabatier反应器内壳8-3、加热器8-9、绝热分隔板8-10、第一金属多孔介质层8-11、第二金属多孔介质层8-12、第三金属多孔介质层8-13、平板式热管。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.
Sabatier还原系统8包括绝热的反应器壳体,反应器壳体内部的反应腔设有进气口和出气口。反应器绝热壳体由Sabatier反应器外壳8-1和Sabatier反应器内壳8-3内外嵌套而成,且内外壳夹层中填充有绝热材料8-2。反应腔通过环形的绝热分隔板8-10分为高温反应区8-4和梯度温度场反应区8-5。绝热材料8-2可采用真空绝热板。对于整个反应腔而言,由于高温反应区8-4的温度较高,所以此处的Sabatier反应具有较高的反应速率。但温度过高会导致反应的转化率下降,因此后续需要通过设置梯度温度场反应区8-5来提高反应转化率。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.
高温反应区8-4内置有用于将Sabatier反应的原料气加热到初始反应温度的加热器8-9,加热器8-9表面涂敷有Sabatier反应催化剂。加热器8-9可采用以太阳能作为热源的加热器。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.
梯度温度场反应区8-5中沿进气方向依次设有第一金属多孔介质层8-11、第二金属多孔介质层8-12和第三金属多孔介质层8-13,且第一金属多孔介质层8-11、第二金属多孔介质层8-12和第三金属多孔介质层8-13的孔隙率递减,介质表面均涂敷有Sabatier反应催化剂;三层金属多孔介质层均通过贯通反应器壳体的平
板式热管与外部火星大气构成换热,使三层金属多孔介质层中的Sabatier反应热能够传递至火星大气。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.
在该反应腔中,原料气从进气口通入后,依次流经高温反应区8-4中的加热器8-9表面以及梯度温度场反应区8-5中的第一金属多孔介质层8-11、第二金属多孔介质层8-12和第三金属多孔介质层8-13,再从出气口排出。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.
上述平板式热管包括顺次连接的平板式热管蒸发段8-6、平板式热管绝热段8-7和平板式热管冷凝段8-8,平板式热管蒸发段8-6位于梯度温度场反应区8-5中且与第一金属多孔介质层8-11、第二金属多孔介质层8-12、第三金属多孔介质层8-13连接并构成换热接触,平板式热管冷凝段8-8位于反应器壳体外部并接触火星大气,平板式热管绝热段8-7贯通穿过反应器壳体且两端分别连接平板式热管蒸发段8-6和平板式热管冷凝段8-8。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.
为了尽可能提高换热效率,平板式热管在梯度温度场反应区8-5中呈环形布置,平板式热管蒸发段8-6环绕包裹于三层金属多孔介质层的外周。而且,平板式热管蒸发段8-6与第一金属多孔介质层8-11、第二金属多孔介质层8-12和第三金属多孔介质层8-13的连接位置可进一步填充有用于消除接触热阻的导热介质。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.
本发明中,第一金属多孔介质层8-11、第二金属多孔介质层8-12和第三金属多孔介质层8-13In 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
在上述第一金属多孔介质层8-11、第二金属多孔介质层8-12和第三金属多孔介质层8-13中,每一层金属多孔介质层都以金属多孔介质作为金属骨架,然后在金属骨架表面附着Sabatier反应催化剂,Sabatier反应热可以通过多孔的金属骨架快速传递至平板热管负热蒸发段。具体的金属骨架和催化剂的形式不限。作为本发明实施例的一种较佳实现方式,各金属多孔介质层可采用导热性好、熔点高的泡沫铜作为金属骨架,且泡沫铜表面涂覆的Sabatier反应催化剂均可采用Ru基催化剂,Ru基催化剂有利于降低Sabatier反应启动温度。由于金属多孔介质的空间导热能力随孔隙率减小而增加,因此孔隙率越低,热传导能力越高,从而通过平板式热管散掉的热量越多,金属多孔介质层的自身温度也就越低。所以,第一金属多孔介质层8-11、第二金属多孔介质层8-12和第三金属多孔介质层8-13三者可以形成沿原料气流动方向温度逐渐降低的梯度温度场,第一金属多孔介质
层8-11、第二金属多孔介质层8-12和第三金属多孔介质层8-13三者的反应速率逐渐降低,但Sabatier反应的转化率却逐渐提高。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.
需要说明的是,三层金属多孔介质层中的具体孔隙率并不限制,三者满足孔隙率逐渐降低的要求即可,各自的具体孔隙率可根据实际的反应情况进行优化设计。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.
基于上述Sabatier反应器的火星表面二氧化碳加氢甲烷化过程具体如下:The specific process of carbon dioxide hydromethanation on the surface of Mars based on the above-mentioned Sabatier reactor is as follows:
将原料气从所述进气口通入反应器壳体内部的反应腔中,首先在高温反应区8-4中通过加热器8-9将原料气加热升温至Sabatier反应启动温度,从而在加热器8-9表面涂敷的Sabatier反应催化剂作用下发生还原反应,使部分原料气转化为甲烷和水。此时高温反应区8-4中的Sabatier反应速率较高,但原料气的转化速率较低。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.
然后将部分转化的原料气继续通入梯度温度场反应区8-5中,依次流经孔隙率递减的第一金属多孔介质层8-11、第二金属多孔介质层8-12和第三金属多孔介质层8-13,在介质表面涂敷的Sabatier反应催化剂作用下继续进行三级转化并释放反应热。在该原料气穿过梯度温度场反应区8-5的过程中,原料气首先与高孔隙率金属多孔介质8-11接触,在金属骨架表面催化剂的作用下,原料气继续进行转化并释放反应热,由于孔隙率较高,所以高孔隙率金属多孔介质8-11所处的区域温度较高;随后与中间孔隙率金属多孔介质8-12接触,在金属骨架表面催化剂的作用下,原料气继续进行转化并释放反应热,由于孔隙率适中,所以中间孔隙率金属多孔介质8-12所处的区域温度继续降低;最后与低孔隙率金属多孔介质8-13接触,在金属骨架表面催化剂的作用下,原料气继续进行转化并释放反应热,由于孔隙率较低,所以低孔隙率金属多孔介质8-13所处的区域温度较较低。高孔隙率金属多孔介质8-11、中间孔隙率金属多孔介质8-12、低孔隙率金属多孔介质8-13所处的区域形成了温度逐渐降低的温度场,可以完成高反应速率到高转化率的高效过渡。而且在反应过程中,第一金属多孔介质层8-11、第二金属多孔介质层8-12、第三金属多孔介质层8-13中的反应热均通过平板式热管传递至反应器壳体外部的火星大气中;最终从出气口收集转化完毕的反应气物料。
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.
另外在本发明的另一优选实施例中,进一步提供了一种Sabatier反应气分离系统9的具体实现方式,如图4所示,其组成元件包括反应气分离管路9-1、水汽冷凝器9-2、第一气液分离器9-3、预冷器9-4、二氧化碳冷凝器9-5、第二气液分离器9-6、甲烷液化冷箱9-7、低温冷机9-8、第三气液分离器9-9、第一低温截止阀9-10、液态甲烷回流管路9-12、第二低温截止阀9-13、第三低温截止阀9-11。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.
其中水汽冷凝器9-2、预冷器9-4和二氧化碳冷凝器9-5中分别设有构成换热接触的第一通路和第二通路;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;
反应气分离管路9-1的入口端用于通入Sabatier装置反应气,出口端接入液态甲烷储罐11。反应气分离管路9-1从入口端到出口端之间依次连接水汽冷凝器9-2的第一通路、第一气液分离器9-3、预冷器9-4的第一通路、二氧化碳冷凝器9-5的第一通路、第二气液分离器9-6、甲烷液化冷箱9-7中的换热管路、第三气液分离器9-9和第一低温截止阀9-10;水汽冷凝器9-2和预冷器9-4的第二通路均用于通入火星大气从而对第一通路进行冷却;甲烷液化冷箱9-7上设有低温冷机9-8,且低温冷机9-8的冷头与甲烷液化冷箱9-7中的换热管路构成换热接触,且冷头温度能液化流经换热管路的Sabatier装置反应气内的甲烷。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.
液态甲烷回流管路9-12的入口端连接第三气液分离器9-9和第一低温截止阀9-10之间的反应气分离管路9-1,出口端连接第二气液分离器9-6和甲烷液化冷箱9-7之间的反应气分离管路9-1。液态甲烷回流管路9-12从入口端到出口端之间依次连接第二低温截止阀9-13、二氧化碳冷凝器9-5的第二通路和第三低温截止阀9-11。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.
其中上述各组成元件的选型和具体形式可根据实际需要调整,在本实施例中,低温冷机9-8采用斯特林型低温冷机,第一气液分离器9-3、第二气液分离器9-6、第三气液分离器9-9均可采用离心式气液分离器。水汽冷凝器9-2和预冷器9-4采用翅片管式换热器。二氧化碳冷凝器9-5采用液-液板式换热器。甲烷液化冷箱9-7中的换热管路采用盘管形式与低温冷机9-8的冷头衔接,且两者之间填充导热介质。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.
基于上述Sabatier反应气分离系统9,具体对Sabatier装置的反应气进行组分分离液化的过程如下:
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:
实时监测火星大气温度,在火星大气温度能够冷凝反应气中的二氧化碳时采用第一运行模式对Sabatier装置反应气进行分离液化,在火星大气温度无法冷凝反应气中的二氧化碳时采用第二运行模式对Sabatier装置反应气进行分离液化。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.
其中第一运行模式如下:The first operating mode is as follows:
S11、启动第一气液分离器9-3、第二气液分离器9-6、低温冷机9-8、第三气液分离器9-9,打开第一低温截止阀9-10,关闭第二低温截止阀9-13和第三低温截止阀9-11;通过风机将火星大气分别输入水汽冷凝器9-2的第二通路和预冷器9-4的第二通路,进而为各自的第一通路提供冷量;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、将来自Sabatier装置的原始反应气输入反应气分离管路9-1中,通过调节输入水汽冷凝器9-2的第二通路的火星大气流量,使得原始反应气中的水汽在流经水汽冷凝器9-2的第一通路过程中吸收火星大气的冷能完成液化,从而变为不低于273.15K的第一气液两相混合物;第一气液两相混合物继续进入第一气液分离器9-3中分离回收液态水后,得到仅包含二氧化碳、甲烷和氢气三种物质的第一剩余反应气;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、将第一剩余反应气继续通入预冷器9-4的第一通路,通过调节输入预冷器9-4的第二通路的火星大气流量,使得第一剩余反应气中的二氧化碳吸收火星大气的冷量后液化,从而变为第二气液两相混合物;第二气液两相混合物继续通过二氧化碳冷凝器9-5的第一通路进入第二气液分离器9-6中分离回收液态二氧化碳,得到仅包含甲烷和氢气两种物质的第二剩余反应气;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、将第二剩余反应气继续通入甲烷液化冷箱9-7,通过控制低温冷机9-8的冷头温度,使得第二剩余反应气中的甲烷与冷头换热后液化,从而变为第三气液两相混合物;第三气液两相混合物继续进入第三气液分离器9-9中分离液态甲烷和氢气,氢气直接排出回收,而液态甲烷则存储至液态甲烷储罐11中;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;
其中第二运行模式如下:The second operating mode is as follows:
S21、启动第一气液分离器9-3、第二气液分离器9-6、低温冷机9-8、第三气液分离器9-9,打开第一低温截止阀9-10、第二低温截止阀9-13和第三低温截止阀9-11;通过风机将火星大气分别输入水汽冷凝器9-2的第二通路和预冷器9-4的第二通路,进而为各自的第一通路提供冷量;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、将来自Sabatier装置的原始反应气输入反应气分离管路9-1中,通过
调节输入水汽冷凝器9-2的第二通路的火星大气流量,使得原始反应气中的水汽在流经水汽冷凝器9-2的第一通路过程中吸收火星大气的冷能完成液化,从而变为不低于273.15K的第一气液两相混合物;第一气液两相混合物继续进入第一气液分离器9-3中分离回收液态水后,得到仅包含二氧化碳、甲烷和氢气三种物质的第一剩余反应气;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、将第一剩余反应气继续通入预冷器9-4的第一通路,通过调节输入预冷器9-4的第二通路的火星大气流量,使得第一剩余反应气降温至接近火星大气的温度后进入二氧化碳冷凝器9-5的第一通路中,继续吸收二氧化碳冷凝器9-5的第二通路中的液态甲烷冷量后完成二氧化碳液化,从而变为第二气液两相混合物;第二气液两相混合物继续进入第二气液分离器9-6中分离回收液态二氧化碳,得到仅包含甲烷和氢气两种物质的第二剩余反应气;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、将第二剩余反应气与液态甲烷回流管路9-12中吸热汽化的甲烷混合后,继续通入甲烷液化冷箱9-7中,通过控制低温冷机9-8的冷头温度,使得第二剩余反应气中的甲烷与冷头换热后液化,从而变为第三气液两相混合物;第三气液两相混合物继续进入第三气液分离器9-9中分离液态甲烷和氢气,氢气直接排出回收,而液态甲烷部分通过液态甲烷回流管路9-12回流至二氧化碳冷凝器9-5的第二通路中用于液化二氧化碳,剩余部分液态甲烷直接存储至液态甲烷储罐11中。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.
最后,本发明中还提供了一种利用如图1所示一体化系统的火星表面运载火箭推进剂原位制备方法,其包括如下步骤: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、通过二氧化碳捕集系统7富集火星大气并获取高纯的二氧化碳气体,随后将二氧化碳通过液态甲烷制备管路1输送至Sabatier还原系统8;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、通过含水矿物质输送系统12将火星表面的含水矿物质输送至水汽提取系统13,由水汽提取系统13从含水矿物质中提取水汽,并将其输送至电解水系统14;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、电解水系统14对水进行电解,制取氢气和氧气,氢气通过氢气管路5输送至Sabatier还原系统8中,氧气分为两条输出,一条通过液氧制备管路2输送至氧气液化系统15并由氧气液化系统15将氧气液化后存储至液氧储罐16,另一条通过氧气管路6输送至生命维持系统10;
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还原系统8利用二氧化碳捕集系统7输送的二氧化碳气体和电解水系统14传输的氢气作为原料,在催化剂的作用下通过Sabatier反应生成甲烷和水,生成包含甲烷、水汽、二氧化碳和氢气四种组分的反应气,反应气输送至Sabatier反应气分离系统9中对四种组分进行分离,其中分离的二氧化碳和氢气返回Sabatier还原系统8中,与二氧化碳捕集系统7输送的二氧化碳气体和电解水系统14传输的氢气混合重新作为原料气,而分离得到的甲烷以液态甲烷形式存储于液态甲烷储罐11中,分离得到的水通过水汽管路4进入电解水系统14中与水汽提取系统13提取的水一起进行电解。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.
以上所述的实施例只是本发明的一种较佳的方案,然其并非用以限制本发明。有关技术领域的普通技术人员,在不脱离本发明的精神和范围的情况下,还可以做出各种变化和变型。因此凡采取等同替换或等效变换的方式所获得的技术方案,均落在本发明的保护范围内。
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)
- 一种火星表面运载火箭推进剂原位制备一体化系统,其特征在于,包括液态甲烷制备管路(1)、液氧制备管路(2)、混合气管路(3)、水汽管路(4)、氢气管路(5)和氧气管路(6);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);所述液态甲烷制备管路(1)依次连接二氧化碳捕集系统(7)、Sabatier还原系统(8)、Sabatier反应气分离系统(9)和液态甲烷储罐(11);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);所述液氧制备管路(2)依次连接含水矿物质输送系统(12)、水汽提取系统(13)、电解水系统(14)、氧气液化系统(15)和液氧储罐(16);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);所述混合气管路(3)连接Sabatier反应气分离系统(9)和Sabatier还原系统(8);The mixed gas pipeline (3) connects the Sabatier reaction gas separation system (9) and the Sabatier reduction system (8);所述水汽管路(4)连接Sabatier反应气分离系统(9)和电解水系统(14);The water vapor pipeline (4) connects the Sabatier reaction gas separation system (9) and the electrolyzed water system (14);所述氢气管路(5)连接电解水系统(14)和Sabatier还原系统(8);The hydrogen pipeline (5) connects the electrolytic water system (14) and the Sabatier reduction system (8);所述氧气管路(6)连接电解水系统(14)和外部需氧设备;The oxygen pipeline (6) connects the electrolyzed water system (14) and external aerobic equipment;所述二氧化碳捕集系统(7)用于从火星大气中捕集二氧化碳,并输入Sabatier还原系统(8)中作为原料;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;所述Sabatier还原系统(8)用于以二氧化碳和氢气作为原料,通过Sabatier还原反应生成甲烷和水;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;所述Sabatier反应气分离系统(9)用于对Sabatier还原系统(8)输出的反应气进行组分分离,分离得到的未反应的二氧化碳和氢气混合物通过混合气管路(3)返回至Sabatier还原系统(8)重新作为原料,分离得到的甲烷以液态甲烷形式存储于液态甲烷储罐(11)中,分离得到的水通过水汽管路(4)进入电解水系统(14)中;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);所述含水矿物质输送系统(12)用于将火星上采集的含水矿物输入水汽提取系统(13),由水汽提取系统(13)提取其中的水分并输入电解水系统(14)中;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);所述电解水系统(14)用于对水进行电解制取氢气和氧气,制取的氢气通过氢气管路(5)输入Sabatier还原系统(8)中作为原料,制取的氧气一路输入氧气液化系统(15)进行液化后存储至液氧储罐(16)中,另一路通过氧气管路(6)输入外部需氧设备。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).
- 如权利要求1所述的火星表面运载火箭推进剂原位制备一体化系统,其 特征在于,所述二氧化碳捕集系统(7)包括二氧化碳液化管路(7-1)、第一级间冷却器(7-4)和第二级间冷却器(7-8);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);所述第一级间冷却器(7-4)和第二级间冷却器(7-8)中均设有构成换热接触的第一通路和第二通路;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;所述二氧化碳液化管路(7-1)的入口端用于通入火星大气,出口端连接低温气液分离器(7-11);二氧化碳液化管路(7-1)在入口端至出口端之间依次连接过滤器(7-2)、电加热器(7-3)、第一级间冷却器(7-4)的第一通路、低温风机(7-5)、第一级压缩机(7-6)、第一级间冷却器(7-4)的第二通路、第二级压缩机(7-7)、第二级间冷却器(7-8)的第一通路、水汽吸附器(7-9)、二氧化碳冷凝器(7-10)和低温气液分离器(7-11);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);所述低温气液分离器(7-11)的气相出口排空,液相出口通过输出管路(7-12)连接第二级间冷却器(7-8)的第二通路,第二级间冷却器(7-8)的第二通路出口与所述液态甲烷制备管路(1)连接。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).
- 如权利要求1所述的火星表面运载火箭推进剂原位制备一体化系统,其特征在于,所述Sabatier还原系统(8)包括绝热的反应器壳体,反应器壳体内部的反应腔设有进气口和出气口;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;所述反应腔通过环形的绝热分隔板(8-10)分为高温反应区(8-4)和梯度温度场反应区(8-5);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);所述高温反应区(8-4)内置有用于将Sabatier反应的原料气加热到初始反应温度的加热器(8-9),加热器(8-9)表面涂敷有Sabatier反应催化剂;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;所述梯度温度场反应区(8-5)中沿进气方向依次设有第一金属多孔介质层(8-11)、第二金属多孔介质层(8-12)和第三金属多孔介质层(8-13),且第一金属多孔介质层(8-11)、第二金属多孔介质层(8-12)和第三金属多孔介质层(8-13)的孔隙率递减,介质表面均涂敷有Sabatier反应催化剂;三层金属多孔介质层均通过贯通反应器壳体的平板式热管与外部火星大气构成换热,使三层金属多孔介质层中的Sabatier反应热能够传递至火星大气;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;所述原料气从所述进气口通入后,依次流经高温反应区(8-4)中的加热器(8-9)表面以及梯度温度场反应区(8-5)中的第一金属多孔介质层(8-11)、第二金属多孔介质层(8-12)和第三金属多孔介质层(8-13),再从所述出气口排 出。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.
- 如权利要求1所述的火星表面运载火箭推进剂原位制备一体化系统,其特征在于,所述Sabatier反应气分离系统(9)包括反应气分离管路(9-1)、水汽冷凝器(9-2)、预冷器(9-4)、二氧化碳冷凝器(9-5)和液态甲烷回流管路(9-12);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);其中水汽冷凝器(9-2)、预冷器(9-4)和二氧化碳冷凝器(9-5)中分别设有构成换热接触的第一通路和第二通路;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;所述反应气分离管路(9-1)的入口端用于通入Sabatier装置反应气,出口端接入液态甲烷储罐(11);反应气分离管路(9-1)从入口端到出口端之间依次连接水汽冷凝器(9-2)的第一通路、第一气液分离器(9-3)、预冷器(9-4)的第一通路、二氧化碳冷凝器(9-5)的第一通路、第二气液分离器(9-6)、甲烷液化冷箱(9-7)中的换热管路、第三气液分离器(9-9)和第一低温截止阀(9-10);水汽冷凝器(9-2)和预冷器(9-4)的第二通路均用于通入火星大气从而对第一通路进行冷却;甲烷液化冷箱(9-7)上设有低温冷机(9-8),且低温冷机(9-8)的冷头与甲烷液化冷箱(9-7)中的换热管路构成换热接触,且冷头温度能液化流经换热管路的Sabatier装置反应气内的甲烷;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;所述液态甲烷回流管路(9-12)的入口端连接第三气液分离器(9-9)和第一低温截止阀(9-10)之间的反应气分离管路(9-1),出口端连接第二气液分离器(9-6)和甲烷液化冷箱(9-7)之间的反应气分离管路(9-1);液态甲烷回流管路(9-12)从入口端到出口端之间依次连接第二低温截止阀(9-13)、二氧化碳冷凝器(9-5)的第二通路和第三低温截止阀(9-11)。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.
- 如权利要求1所述的火星表面运载火箭推进剂原位制备一体化系统,其特征在于,所述氧气液化系统(15)中预先利用火星大气的冷能对氧气进行预冷,然后通过低温冷机对氧气进行降温液化。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.
- 如权利要求5所述的火星表面运载火箭推进剂原位制备一体化系统,其特征在于,所述低温冷机为斯特林低温冷机。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.
- 如权利要求1所述的火星表面运载火箭推进剂原位制备一体化系统,其特征在于,所述水汽提取系统(13)为微波加热装置,通过对含水矿物质进行微波加热的方式获取纯净水汽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.
- 如权利要求1所述的火星表面运载火箭推进剂原位制备一体化系统,其 特征在于,所述电解水系统(14)采用光催化辅助的电解水系统。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.
- 如权利要求1所述的火星表面运载火箭推进剂原位制备一体化系统,其特征在于,所述外部需氧设备为生命维持系统(10)。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).
- 一种利用如权利要求1~9任一所述系统的火星表面运载火箭推进剂原位制备方法,其特征在于,包括: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、通过二氧化碳捕集系统(7)富集火星大气并获取高纯的二氧化碳气体,随后将二氧化碳通过液态甲烷制备管路(1)输送至Sabatier还原系统(8);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、通过含水矿物质输送系统(12)将火星表面的含水矿物质输送至水汽提取系统(13),由水汽提取系统(13)从含水矿物质中提取水汽,并将其输送至电解水系统(14);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、电解水系统(14)对水进行电解,制取氢气和氧气,氢气通过氢气管路(5)输送至Sabatier还原系统(8)中,氧气分为两条输出,一条通过液氧制备管路(2)输送至氧气液化系统(15)并由氧气液化系统(15)将氧气液化后存储至液氧储罐(16),另一条通过氧气管路(6)输送至生命维持系统(10);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、Sabatier还原系统(8)利用二氧化碳捕集系统(7)输送的二氧化碳气体和电解水系统(14)传输的氢气作为原料,在催化剂的作用下通过Sabatier反应生成甲烷和水,生成包含甲烷、水汽、二氧化碳和氢气四种组分的反应气,反应气输送至Sabatier反应气分离系统(9)中对四种组分进行分离,其中分离的二氧化碳和氢气返回Sabatier还原系统(8)中,与二氧化碳捕集系统(7)输送的二氧化碳气体和电解水系统(14)传输的氢气混合重新作为原料气,而分离得到的甲烷以液态甲烷形式存储于液态甲烷储罐(11)中,分离得到的水通过水汽管路(4)进入电解水系统(14)中与水汽提取系统(13)提取的水一起进行电解。 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).
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