CN115304440A - Integrated system and method for in-situ preparation of propellant of Mars surface carrier rocket - Google Patents
Integrated system and method for in-situ preparation of propellant of Mars surface carrier rocket Download PDFInfo
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- 239000003380 propellant Substances 0.000 title claims abstract description 45
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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
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- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Metallurgy (AREA)
- Electrochemistry (AREA)
- Materials Engineering (AREA)
- Combustion & Propulsion (AREA)
- Inorganic Chemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Oil, Petroleum & Natural Gas (AREA)
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Abstract
The invention discloses an integrated system and a method for in-situ preparation of a propellant of a Mars surface carrier rocket. The method utilizes carbon dioxide in the atmosphere of the mars to prepare the methane propellant, utilizes water in the water-containing mineral substances of the mars to prepare the liquid oxygen propellant and oxygen required by a life support system, and has high conformity with the requirements of liquid oxygen methane carrier rockets and mars detection tasks. The invention conveys the product water in the liquid methane preparation process to the electrolytic water system, so the exploitation amount of water-containing mineral substances can be reduced by half, namely, the oxygen element in the carbon dioxide of the Mars is used as an important source of the liquid oxygen propellant.
Description
Technical Field
The invention relates to the technical field of Mars detection, in particular to an integrated system and method for in-situ preparation of a Mars surface carrier rocket propellant.
Background
The in-situ preparation of the Mars propellant refers to the exploration, acquisition and utilization of natural resources of Mars to prepare the carrier rocket propellant on the Mars in situ, is a deep space exploration solution with strong sustainability and low cost, can effectively reduce the dependence on carried resources and earth supply, and is a key technical means for realizing extraterrestrial manned exploration, future space colonizers and other extraterrestrial activities. The main component of the atmosphere on the surface of the mars is carbon dioxide, which accounts for 95.32 percent of the total amount and is the most potential raw material for in-situ preparation of the mars propellant. Manned Mars detection requires 7 tons of methane propellant and 23 tons of liquid oxygen propellant to be produced within 16 months, and 5 tons of oxygen for life support, totaling 35 tons, according to NASA calculations.
However, since there is no return type Mars exploration activity, the in-situ preparation of Mars surface propellant is still in the technical exploration stage, including the preparation of hydrocarbon fuel propellant such as methane, kerosene and the like by using carbon dioxide in the Mars atmosphere, but there is no very clear technical scheme at present.
Disclosure of Invention
The invention aims to solve the problem that propellant raw materials meeting the requirement of manned Mars detection are difficult to prepare in the prior art, and provides an integrated system and a method for in-situ preparation of a Mars surface carrier rocket propellant. The liquid methane propellant is prepared by utilizing carbon dioxide in the atmosphere of the mars, and the liquid oxygen propellant is prepared by electrolyzing water in the water-containing mineral substances of the mars, so that the synchronous and efficient preparation of the liquid methane propellant and the liquid oxygen propellant is realized.
The invention adopts the following specific technical scheme:
in a first aspect, the invention provides an integrated system for in-situ preparation of a propellant of a Mars surface carrier rocket, which comprises a liquid methane preparation pipeline, a liquid oxygen preparation pipeline, a mixed gas pipeline, a water vapor pipeline, a hydrogen pipeline and an oxygen pipeline;
the liquid methane preparation pipeline is sequentially connected with a carbon dioxide capture system, a Sabatier reduction system, a Sabatier reaction gas separation system and a liquid methane storage tank;
the liquid oxygen preparation pipeline is sequentially connected with the hydrous mineral substance conveying system, the water vapor extraction system, the water electrolysis system, the oxygen liquefaction system and the liquid oxygen storage tank;
the mixed gas pipeline is connected with the Sabatier reaction gas separation system and the Sabatier reduction system;
the water vapor pipeline is connected with the Sabatier reaction gas separation system and the electrolytic water system;
the hydrogen pipeline is connected with the electrolytic water system and the Sabatier reduction system;
the oxygen pipeline is connected with the electrolytic water system and the external aerobic equipment;
the carbon dioxide capture system is used for capturing carbon dioxide from Mars atmosphere and inputting the carbon dioxide into the Sabatier reduction system as a raw material;
the Sabatier reduction system is used for generating methane and water by taking carbon dioxide and hydrogen as raw materials through a Sabatier reduction reaction;
the Sabatier reaction gas separation system is used for carrying out component separation on reaction gas output by the Sabatier reduction system, a mixture of unreacted carbon dioxide and hydrogen obtained by separation is returned to the Sabatier reduction system through a mixed gas pipeline to be used as a raw material again, methane obtained by separation is stored in a liquid methane storage tank in a liquid methane form, and water obtained by separation enters an electrolytic water system through a water vapor pipeline;
the water-containing mineral conveying system is used for conveying the water-containing minerals collected on the mars into the water vapor extraction system, extracting water in the water vapor extraction system and conveying the water into the electrolytic water system;
the electrolytic water system is used for electrolyzing water to prepare hydrogen and oxygen, the prepared hydrogen is input into the Sabatier reduction system through a hydrogen pipeline to serve as a raw material, one path of the prepared oxygen is input into the oxygen liquefying system to be liquefied and then stored into the liquid oxygen storage tank, and the other path of the prepared oxygen is input into external aerobic equipment through an oxygen pipeline.
Preferably, the carbon dioxide capture system of the first aspect comprises a carbon dioxide liquefaction line, a first inter-cooler, and a second inter-cooler;
a first passage and a second passage which form heat exchange contact are arranged in the first-stage intercooler and the second-stage intercooler;
the inlet end of the carbon dioxide liquefaction pipeline is used for introducing spark atmosphere, and the outlet end of the carbon dioxide liquefaction pipeline is connected with the low-temperature gas-liquid separator; the carbon dioxide liquefaction pipeline is sequentially connected with a filter, an electric heater, a first passage of a first inter-stage cooler, a low-temperature fan, a first-stage compressor, a second passage of the first inter-stage cooler, a second-stage compressor, a first passage of a second inter-stage cooler, a water vapor adsorber, a carbon dioxide condenser and a low-temperature gas-liquid separator from an inlet end to an outlet end;
and a gas phase outlet of the low-temperature gas-liquid separator is emptied, a liquid phase outlet is connected with a second passage of the second inter-cooler through an output pipeline, and a second passage outlet of the second inter-cooler is connected with the liquid methane preparation pipeline.
As a preferred aspect of the first aspect, the Sabatier reduction system comprises a heat-insulated reactor shell, wherein a reaction chamber inside the reactor shell is provided with an air inlet and an air outlet;
the reaction cavity is divided into a high-temperature reaction zone and a gradient temperature field reaction zone by an annular heat insulation partition plate;
a heater for heating feed gas of the Sabatier reaction to an initial reaction temperature is arranged in the high-temperature reaction zone, and a Sabatier reaction catalyst is coated on the surface of the heater;
a first metal porous medium layer, a second metal porous medium layer and a third metal porous medium layer are sequentially arranged in the gradient temperature field reaction zone along the air inlet direction, the porosity of the first metal porous medium layer, the porosity of the second metal porous medium layer and the porosity of the third metal porous medium layer are decreased gradually, and the surface of each medium is coated with a Sabatier reaction catalyst; the three metal porous medium layers are subjected to heat exchange with external spark atmosphere through flat plate heat pipes penetrating through the reactor shell, so that Sabatier reaction heat in the three metal porous medium layers can be transferred to the spark atmosphere;
and after being introduced from the gas inlet, the raw material gas sequentially flows through the surface of the heater in the high-temperature reaction zone and the first metal porous medium layer, the second metal porous medium layer and the third metal porous medium layer in the gradient temperature field reaction zone and is discharged from the gas outlet.
As a preferred aspect of the first aspect, the Sabatier reaction gas separation system includes a reaction gas separation line, a water vapor condenser, a precooler, a carbon dioxide condenser, and a liquid methane return line;
wherein a first passage and a second passage which form heat exchange contact are respectively arranged in the water vapor condenser, the precooler and the carbon dioxide condenser;
the inlet end of the reaction gas separation pipeline is used for introducing the reaction gas of the Sabatier device, and the outlet end of the reaction gas separation pipeline is connected to a liquid methane storage tank; the reaction gas separation pipeline is sequentially connected with a first passage of a water vapor condenser, a first gas-liquid separator, a first passage of a precooler, a first passage of a carbon dioxide condenser, a second gas-liquid separator, a heat exchange pipeline in a methane liquefaction cold box, a third gas-liquid separator and a first low-temperature stop valve from an inlet end to an outlet end; the second passages of the water vapor condenser and the precooler are used for introducing mars atmosphere so as to cool the first passage; a low-temperature cooler is arranged on the methane liquefaction cold box, a cold head of the low-temperature cooler is in heat exchange contact with a heat exchange pipeline in the methane liquefaction cold box, and the temperature of the cold head can liquefy methane in the reaction gas of the Sabatier device flowing through the heat exchange pipeline;
the inlet end of the liquid methane return pipeline is connected with a reaction gas separation pipeline between the third gas-liquid separator and the first low-temperature stop valve, and the outlet end of the liquid methane return pipeline is connected with a reaction gas separation pipeline between the second gas-liquid separator and the methane liquefaction cold box; and the liquid methane return pipeline is sequentially connected with the second low-temperature stop valve, a second passage of the carbon dioxide condenser and a third low-temperature stop valve from the inlet end to the outlet end.
In the first aspect, the oxygen liquefaction system pre-cools the oxygen by using cold energy of Martian atmosphere, and then cools and liquefies the oxygen by the low-temperature cooler.
Preferably, in the first aspect, the low-temperature cooler is a stirling low-temperature cooler.
Preferably, the steam extraction system is a microwave heating device, and pure steam is obtained by microwave heating of the water-containing minerals
As a preferable aspect of the first aspect, the electrolytic water system employs a photocatalytic-assisted electrolytic water system.
Preferably, as for the first aspect above, the external aerobic apparatus is a life support system.
In a second aspect, the present invention provides a method for the in situ preparation of a propellant for a Mars surface launch vehicle using a system according to any of the aspects of the first aspect, comprising:
s1, enriching Mars atmosphere through a carbon dioxide capture system, obtaining high-purity carbon dioxide gas, and then conveying the carbon dioxide to a Sabatier reduction system through a liquid methane preparation pipeline;
s2, conveying the water-containing minerals on the surfaces of the mars to a water vapor extraction system through a water-containing mineral conveying system, extracting water vapor from the water-containing minerals through the water vapor extraction system, and conveying the water vapor to an electrolytic water system;
s3, electrolyzing water by an electrolytic water system to prepare hydrogen and oxygen, wherein the hydrogen is conveyed to a Sabatier reduction system through a hydrogen pipeline, the oxygen is divided into two outputs, one of the two outputs is conveyed to an oxygen liquefaction system through a liquid oxygen preparation pipeline, the oxygen liquefaction system liquefies the oxygen and then stores the oxygen in a liquid oxygen storage tank, and the other output is conveyed to a life support system through an oxygen pipeline;
s4, the Sabatier reduction system utilizes carbon dioxide gas conveyed by the carbon dioxide capture system and hydrogen transmitted by the water electrolysis system as raw materials, methane and water are generated through Sabatier reaction under the action of a catalyst, reaction gas containing four components of methane, water vapor, carbon dioxide and hydrogen is generated, the reaction gas is conveyed to the Sabatier reaction gas separation system to separate the four components, the separated carbon dioxide and hydrogen return to the Sabatier reduction system and are mixed with the carbon dioxide gas conveyed by the carbon dioxide capture system and the hydrogen transmitted by the water electrolysis system to be used as raw material gas again, the separated methane is stored in a liquid methane storage tank in a liquid methane form, and the separated water enters the water electrolysis system through a water vapor pipeline to be electrolyzed together with water extracted by the water vapor extraction system.
Compared with the prior art, the invention has the outstanding and beneficial technical effects that: the integrated system for in-situ preparation of the propellant of the Mars surface carrier rocket is provided, and synchronous preparation of the propellant required by the carrier rocket can be realized; the carbon dioxide in the atmosphere of the mars is used for preparing a methane propellant, the water in the water-containing mineral substances of the mars is used for preparing a liquid oxygen propellant and oxygen required by a life support system, and the engagement degree between the liquid oxygen methane carrier rocket and the mars detection task requirement is high; according to calculation, every time 1kg of methane is obtained through reduction reaction, the corresponding product water can obtain 2kg of oxygen through electrolysis, and the invention conveys the product water in the liquid methane preparation process to an electrolytic water system, so that the production amount of water-containing mineral substances can be reduced by half, namely, oxygen element in Martian carbon dioxide is used as an important source of liquid oxygen propellant.
The conception, the specific structure and the technical effects produced by the present invention will be further described in conjunction with the accompanying drawings so as to fully understand the objects, the features and the effects of the present invention.
Drawings
FIG. 1 is a schematic structural diagram of an integrated system for in-situ preparation of a propellant of a Mars surface launch vehicle;
FIG. 2 is a schematic diagram of a preferred mode of the carbon dioxide capture system;
FIG. 3 is a schematic diagram of a preferred embodiment of the Sabatier reduction system;
figure 4 is a schematic diagram of a preferred mode of the Sabatier reaction gas separation system.
The reference numbers in the figures are: the system comprises a liquid methane preparation pipeline 1, a liquid oxygen preparation pipeline 2, a carbon dioxide/hydrogen mixing pipeline 3, a water vapor pipeline 4, a hydrogen pipeline 5, an oxygen pipeline 6, a carbon dioxide capture system 7, a Sabatier reduction system 8, a Sabatier reaction gas separation system 9, a life support system 10, a liquid methane storage tank 11, a water-containing mineral mining system 12, a water vapor extraction system 13, an electrolytic water system 14, an oxygen liquefaction system 15 and a liquid oxygen storage tank 16.
Detailed Description
The invention will be further elucidated and described with reference to the drawings and the detailed description. The technical characteristics of the embodiments of the invention can be correspondingly combined without mutual conflict.
In order to make the aforementioned objects, features and advantages of the present invention more comprehensible, embodiments accompanying figures are described in detail below. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. The technical characteristics in the embodiments of the present invention can be combined correspondingly without mutual conflict.
In the description of the present invention, it should be understood that when an element is referred to as being "connected" to another element, it can be directly connected to the other element or be indirectly connected to the other element, i.e., intervening elements may be present. In contrast, when an element is referred to as being "directly connected" to another element, there are no intervening elements present.
In the description of the present invention, it is to be understood that the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implying any number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the feature.
As shown in fig. 1, in a preferred embodiment of the present invention, an integrated system for in-situ preparation of a propellant for a mars surface launch vehicle is provided, which comprises a liquid methane preparation line 1, a liquid oxygen preparation line 2, a carbon dioxide/hydrogen mixing line 3, a water vapor line 4, a hydrogen line 5, an oxygen line 6, a carbon dioxide capture system 7, a Sabatier reduction system 8, a Sabatier reaction gas separation system 9, a life support system 10, a liquid methane storage tank 11, a water-containing mineral mining system 12, a water vapor extraction system 13, an electrolytic water system 14, an oxygen liquefaction system 15, and a liquid oxygen storage tank 16. In the system, the liquid methane propellant can be prepared by utilizing carbon dioxide in the atmosphere of the mars, and the liquid oxygen propellant is prepared by electrolyzing water in the water-containing mineral substances of the mars, so that the synchronous and efficient preparation of the liquid methane propellant and the liquid oxygen propellant is realized.
In the whole system, all subsystems are connected through a liquid methane preparation pipeline 1, a liquid oxygen preparation pipeline 2, a mixed gas pipeline 3, a water vapor pipeline 4, a hydrogen pipeline 5 and an oxygen pipeline 6, so that the cooperative work is realized. Wherein, the liquid methane preparation pipeline 1 is connected with a carbon dioxide capture system 7, a Sabatier reduction system 8, a Sabatier reaction gas separation system 9 and a liquid methane storage tank 11 in sequence. The liquid oxygen preparation pipeline 2 is sequentially connected with a water-containing mineral substance conveying system 12, a water vapor extraction system 13, an electrolytic water system 14, an oxygen liquefaction system 15 and a liquid oxygen storage tank 16. The mixed gas pipeline 3 is connected with a Sabatier reaction gas separation system 9 and a Sabatier reduction system 8. The water vapor pipeline 4 is connected with the Sabatier reaction gas separation system 9 and the electrolytic water system 14. A hydrogen line 5 connects the electrolysis water system 14 and the Sabatier reduction system 8. The oxygen line 6 connects the electrolytic water system 14 with external aerobic equipment. The external aerobic device may be any device on the Mars that requires aerobic, in this embodiment the life support system 10 on the Mars.
The subsystems in the integrated system except the pipeline and the storage tank body are the key for realizing the functions of the integrated system. The respective functions and the cooperation relationship will be described below.
The carbon dioxide capture system 7 is used to capture carbon dioxide from the Mars atmosphere and is fed to the Sabatier reduction system 8 as a feedstock. Since more than 95% of the components in the spark atmosphere are carbon dioxide, the carbon dioxide capture system 7 can obtain carbon dioxide from the spark atmosphere by an adsorption method, a refrigeration method, or the like.
The Sabatier reduction system 8 is used to produce methane and water by Sabatier reduction using carbon dioxide and hydrogen as the feed. The Sabatier reduction system 8 is a common device in aerospace equipment that is capable of producing methane by a Sabatier reduction reaction. The Sabatier reduction system 8 can in principle be implemented using any Sabatier reaction apparatus.
The Sabatier reaction gas separation system 9 is used for performing component separation on reaction gas output by the Sabatier reduction system 8, a mixture of unreacted carbon dioxide and hydrogen obtained through separation returns to the Sabatier reduction system 8 through the mixed gas pipeline 3 to be used as a raw material again, methane obtained through separation is stored in the liquid methane storage tank 11 in a liquid methane form, and water obtained through separation enters the electrolytic water system 14 through the water vapor pipeline 4. For the separation of different components in the Sabatier reaction gas separation system 9, the liquefaction temperature difference between different components can be used for separation step by step.
The hydrous mineral transport system 12 is used to transport hydrous minerals collected on mars to the water vapor extraction system 13, from which water is extracted by the water vapor extraction system 13 and transported to the electrolyzed water system 14. The aqueous mineral delivery system 12 may employ any delivery device and may be connected at its forward end to an aqueous mineral collection device. The steam extraction system 13 preferably employs a microwave heating device to obtain pure steam by microwave heating of the water-containing minerals.
The electrolytic water system 14 is used for electrolyzing water to prepare hydrogen and oxygen, the prepared hydrogen is input into the Sabatier reduction system 8 through the hydrogen pipeline 5 to be used as a raw material, one path of the prepared oxygen is input into the oxygen liquefying system 15 to be liquefied and then stored into the liquid oxygen storage tank 16, and the other path of the prepared oxygen is input into the life support system 10 through the oxygen pipeline 6.
In the present invention, the electrolyzed water system 14 can be any prior art device for electrolyzing water to produce hydrogen and oxygen. In consideration of the efficiency of water electrolysis, auxiliary systems such as photocatalysis can be configured on the basis of the traditional device, and the operating efficiency of the system is improved by fully utilizing solar energy, namely the water electrolysis system 14 can adopt a photocatalysis-assisted water electrolysis system.
In the invention, the oxygen liquefaction system 15 pre-cools the oxygen by using the cold energy of Martian atmosphere in advance, and then cools and liquefies the oxygen by the low-temperature cooler. The particularly adopted low-temperature cooler is preferably a Stirling low-temperature cooler with small volume and light weight. Of course, the pressure can be increased in the process of reducing the temperature and liquefying the oxygen, so as to improve the liquefying efficiency.
The operation flow of the integrated system for in-situ preparation of the propellant of the Mars surface carrier rocket is as follows:
(1) The carbon dioxide capture system 7 enriches the Martian atmosphere and takes high purity carbon dioxide gas, which is then transported to the Sabatier reduction system 8 via the liquid methane production line 1.
(2) The Sabatier reduction system 8 comprises three inputs, namely carbon dioxide gas delivered by the carbon dioxide capture system 7, hydrogen delivered by the electrolytic water system 14 and a mixed gas of carbon dioxide and hydrogen delivered by the Sabatier reaction gas separation system 9, and then the carbon dioxide and the hydrogen generate methane and water under the action of a catalyst, the carbon dioxide and the hydrogen do not completely react due to the fact that the conversion rate of the Sabatier reaction is affected by temperature, and the reaction gas delivered to the Sabatier reaction gas separation system 9 by the Sabatier reduction system 8 contains four substances of methane, water vapor, carbon dioxide and hydrogen.
(3) The Sabatier reaction gas separation system 9 performs reaction gas separation, then unreacted carbon dioxide and hydrogen are conveyed to the Sabatier reduction system 8 through the carbon dioxide/hydrogen mixing pipeline 3 to perform secondary reaction, water vapor is conveyed to the water electrolysis system 14 through the water vapor pipeline 4 to be electrolyzed, and methane is conveyed to the liquid methane storage tank 11 in a liquid methane form to be stored.
(5) The hydrous mineral substance conveying system 12 is used for mining hydrous mineral substances on the surface of the mars, conveying the hydrous mineral substances to the water vapor extraction system 13 after primary treatment, treating the hydrous mineral substances by the water vapor extraction system 13 in a microwave heating mode and the like, obtaining water vapor with the purity meeting the requirement, and conveying the water vapor to the electrolytic water system 14.
(6) The electrolyzed water system 14 includes two inputs, mineral extract water delivered by the water vapor extraction system 13 and product water delivered by the Sabatier reaction gas separation system 9, the water is then electrolyzed into hydrogen and oxygen, the hydrogen is delivered to the Sabatier reduction system 8 via the hydrogen line 5 to participate in the reduction reaction, the oxygen is divided into two outputs, one is delivered to the oxygen liquefaction system 15 via the liquid oxygen production line 2, and the other is delivered to the life support system 10 via the oxygen line 6.
(7) The oxygen liquefaction system 15 completes liquefaction of the oxygen provided by the electrolytic water system 14 and delivers the liquid oxygen to the liquid oxygen storage tank 16 for storage.
In addition, in another preferred embodiment of the present invention, there is further provided a specific implementation manner of the carbon dioxide capture system 7, as shown in fig. 2, the components of which include a filter 7-2, an electric heater 7-3, a first stage intercooler 7-4, a low temperature fan 7-5, a first stage compressor 7-6, a second stage compressor 7-7, a second stage intercooler 7-8, a water vapor adsorber 7-9, a carbon dioxide condenser 7-10, a low temperature gas-liquid separator 7-11 and an output pipeline 7-12. The connection relationship between the constituent elements is as follows:
the first-stage intercooler 7-4 and the second-stage intercooler 7-8 are respectively provided with a first passage and a second passage which form heat exchange contact.
The inlet end of the carbon dioxide liquefaction pipeline 7-1 is used for introducing mars atmosphere, and the outlet end is connected with the low-temperature gas-liquid separator 7-11; the carbon dioxide liquefaction pipeline 7-1 is sequentially connected with a filter 7-2, an electric heater 7-3, a first passage of a first inter-stage cooler 7-4, a low-temperature fan 7-5, a first-stage compressor 7-6, a second passage of the first inter-stage cooler 7-4, a second-stage compressor 7-7, a first passage of a second inter-stage cooler 7-8, a water vapor adsorber 7-9, a carbon dioxide condenser 7-10 and a low-temperature gas-liquid separator 7-11 from an inlet end to an outlet end.
The gas phase outlet of the low-temperature gas-liquid separator 7-11 is emptied, the liquid phase outlet is connected with the second passage of the second inter-cooler 7-8 through the output pipeline 7-12, and the second passage outlet of the second inter-cooler 7-8 is connected with the liquid methane preparation pipeline 1.
The selection of the above devices can be adjusted according to actual needs, in this embodiment, the filter preferably adopts an electrostatic dust removal device, the first stage compressor 7-6 and the second stage compressor 7-7 can adopt a positive displacement compressor, and the outlet pressure of the second stage compressor 7-7 is higher than the triple point pressure of carbon dioxide. The low-temperature gas-liquid separator 7-11 can adopt a centrifugal gas-liquid separator. The first stage intercooler 7-4 and the second stage intercooler 7-8 may employ a gas-gas plate heat exchanger. The carbon dioxide condenser 7-10 can adopt a finned tube heat exchanger, and a cold source of the finned tube heat exchanger can be Mars atmosphere at night with the temperature lower than the condensation temperature of the carbon dioxide, or other low-temperature working media can be adopted for assistance when the temperature of the Mars atmosphere is higher than the condensation temperature of the carbon dioxide.
The specific method for continuously capturing carbon dioxide on the surface of the spark based on the carbon dioxide capturing system 7 is as follows:
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 are sequentially started, so that the Mars atmosphere enters the carbon dioxide liquefaction pipeline 7-1 under the action of the low-temperature fan 7-5, firstly flows through the filter 7-2 to remove impurities such as dust and the like to become pure raw material gas, and then sequentially enters the electric heater 7-3 and the first passage of the first-stage inter-cooler 7-4 to be preheated. It is particularly noted that the electric heater 7-3 is turned on only at the start of the system, and the heat required for preheating is supplied from the first inter-stage cooler 7-4 after steady operation, and the electric heater 3 may not need to be turned on. The preheated feed gas enters a first-stage compressor 7-6 under the traction of a low-temperature fan 7-5 to complete first pressurization, so that a first pressurized feed gas is formed. The temperature of the primary pressurized feed gas after pressurization is completed can be rapidly increased, the high-temperature primary pressurized feed gas enters the second passage of the first inter-stage cooler 7-4, exchanges heat with the feed gas which is not preheated in the first passage of the first inter-stage cooler 7-4 for cooling, and then enters the second-stage compressor 7-7 for secondary pressurization, so that secondary pressurized feed gas is obtained. After the pressurization is finished, the temperature of the secondary pressurized feed gas rises sharply, the high-temperature secondary pressurized feed gas enters the first passage of the second-stage intercooler 7-8 and exchanges heat with liquid carbon dioxide flowing in the first passage of the second-stage intercooler 7-8 for cooling, the obtained feed gas with the temperature maintained above 273.15K continuously enters the water vapor adsorber 7-9 in the carbon dioxide liquefaction pipeline 7-1 to remove water vapor, and the high-purity carbon dioxide feed gas is obtained. The high-purity carbon dioxide raw material gas continuously enters the carbon dioxide condenser 7-10 to liquefy the carbon dioxide, but at the moment, the carbon dioxide entering the condenser is liquefied, and part of impurity gases with lower liquefying temperature, such as nitrogen, argon and the like, in the carbon dioxide raw material gas are not liquefied, so that the carbon dioxide flows out of the carbon dioxide condenser 7-10. The gas-liquid two-phase mixture enters a low-temperature gas-liquid separator 7-11 for gas-liquid separation, impurity gas is directly discharged, and liquid carbon dioxide is input into a second passage of a second-stage intercooler 7-8 through an output pipeline 7-12, exchanges heat with secondary pressurized feed gas, is re-vaporized, and enters a liquid methane preparation pipeline 1 for subsequent Sabatier reaction.
The adsorbents which can be filled in the water vapor adsorber 7-9 are alumina and other adsorbents with strong water adsorption capacity. However, the water vapor adsorber 7-9 may be saturated after operating for a period of time, and the machine may be stopped temporarily to replace the water vapor adsorber 7-9 or to heat and regenerate the internal adsorption medium.
In addition, it should be noted that the carbon dioxide gas entering the liquid methane preparation pipeline 1 needs to be pressurized if the pressure does not meet the requirement of the subsequent reaction, and the specific pressurization mode belongs to the prior art.
In addition, in another preferred embodiment of the present invention, a specific implementation manner of the Sabatier reduction system 8 is further provided, as shown in fig. 3, the components thereof include an outer Sabatier reactor shell 8-1, a heat insulating material 8-2, an inner Sabatier reactor shell 8-3, a heater 8-9, a heat insulating partition plate 8-10, a first metal porous medium layer 8-11, a second metal porous medium layer 8-12, a third metal porous medium layer 8-13, and a flat plate heat pipe.
The Sabatier reduction system 8 comprises a thermally insulated reactor housing, the reaction chamber inside the reactor housing being provided with an air inlet and an air outlet. The reactor heat insulation shell is formed by internally and externally nesting a Sabatier reactor outer shell 8-1 and a Sabatier reactor inner shell 8-3, and a heat insulation material 8-2 is filled in an interlayer of the inner shell and the outer shell. The reaction chamber is divided into a high-temperature reaction zone 8-4 and a gradient temperature field reaction zone 8-5 by an annular heat insulation partition plate 8-10. The heat insulating material 8-2 may be a vacuum heat insulating plate. The Sabatier reaction herein has a higher reaction rate for the entire reaction chamber due to the higher temperature of the high temperature reaction zone 8-4. However, the conversion rate of the reaction is reduced due to the over-high temperature, so that the conversion rate of the reaction is increased by arranging the reaction zone 8-5 with the gradient temperature field.
A heater 8-9 for heating the feed gas of the Sabatier reaction to the initial reaction temperature is arranged in the high-temperature reaction zone 8-4, and the surface of the heater 8-9 is coated with a Sabatier reaction catalyst. The heaters 8 to 9 may employ a heater using solar energy as a heat source.
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 are sequentially arranged in the gradient temperature field reaction zone 8-5 along the air inlet direction, the porosity of the first metal porous medium layer 8-11, the porosity of the second metal porous medium layer 8-12 and the porosity of the third metal porous medium layer 8-13 are decreased gradually, and the surfaces of the media are coated with a Sabatier reaction catalyst; the three metal porous medium layers are in heat exchange with external spark atmosphere through flat plate heat pipes penetrating through the reactor shell, so that Sabatier reaction heat in the three metal porous medium layers can be transferred to the spark atmosphere.
In the reaction cavity, after being introduced from the gas inlet, the feed gas sequentially flows through the surface of a heater 8-9 in the high-temperature reaction zone 8-4, 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 the gradient temperature field reaction zone 8-5, and then is discharged from the gas outlet.
The flat-plate heat pipe comprises a flat-plate heat pipe evaporation section 8-6, a flat-plate heat pipe heat insulation section 8-7 and a flat-plate heat pipe condensation section 8-8 which are connected in sequence, wherein the flat-plate heat pipe evaporation section 8-6 is positioned in a gradient temperature field reaction zone 8-5 and is connected 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 to form heat exchange contact, the flat-plate heat pipe condensation section 8-8 is positioned outside a reactor shell and is in contact with Mars atmosphere, and the flat-plate heat pipe heat insulation section 8-7 penetrates through the reactor shell and is respectively connected with the flat-plate heat pipe evaporation section 8-6 and the flat-plate heat pipe condensation section 8-8 at two ends.
In order to improve the heat exchange efficiency as much as possible, the flat-plate heat pipe is annularly arranged in the gradient temperature field reaction zone 8-5, and the evaporation section 8-6 of the flat-plate heat pipe is wrapped around the periphery of the three metal porous medium layers. Moreover, the connection positions of the evaporation section 8-6 of the flat-plate heat pipe, 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 be further filled with heat conducting media for eliminating contact thermal resistance.
In the invention, 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 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, each metal porous medium layer takes a metal porous medium as a metal framework, then a Sabatier reaction catalyst is attached to the surface of the metal framework, and the Sabatier reaction heat can be quickly transferred to the negative heat evaporation section of the flat heat pipe through the porous metal framework. The specific metal framework and the form of the catalyst are not limited. As a better implementation mode of the embodiment of the invention, each metal porous dielectric layer can adopt foam copper with good heat conductivity and high melting point as a metal framework, and Sabatier reaction catalysts coated on the surface of the foam copper can adopt Ru-based catalysts which are beneficial to reducing the Sabatier reaction starting temperature. Since the space heat conduction capacity of the metal porous medium is increased along with the reduction of the porosity, the lower the porosity is, the higher the heat conduction capacity is, so that the more heat is dissipated through the flat plate type heat pipe, and the lower the temperature of the metal porous medium layer 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 with gradually reduced temperature along the flowing direction of the raw material gas, the reaction rates of 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 are gradually reduced, but the conversion rate of the Sabatier reaction is gradually improved.
It should be noted that the specific porosity in the three metal porous dielectric layers is not limited, and the three metal porous dielectric layers can meet the requirement of gradually decreasing the porosity, and the respective specific porosity can be optimally designed according to the actual reaction condition.
The carbon dioxide hydrogenation methanation process on the surface of the mars based on the Sabatier reactor is as follows:
and introducing the raw gas into a reaction cavity in the reactor shell from the gas inlet, firstly heating the raw gas to the starting temperature of the Sabatier reaction in a high-temperature reaction zone 8-4 through a heater 8-9, and thus, carrying out a reduction reaction under the action of the Sabatier reaction catalyst coated on the surface of the heater 8-9, so that part of the raw gas is converted into methane and water. In this case, the Sabatier reaction rate in the high temperature reaction zone 8-4 is higher, but the feed gas conversion rate is lower.
And then continuously introducing the partially converted feed gas into a gradient temperature field reaction zone 8-5, sequentially flowing through 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 with gradually decreased porosity, continuously performing three-stage conversion under the action of a Sabatier reaction catalyst coated on the surface of the medium, and releasing reaction heat. In the process that the raw gas passes through the gradient temperature field reaction zone 8-5, the raw gas is firstly contacted with the high-porosity metal porous medium 8-11, the raw gas is continuously converted and releases reaction heat under the action of the metal framework surface catalyst, and the temperature of the area where the high-porosity metal porous medium 8-11 is positioned is higher due to higher porosity; then contacting with the intermediate porosity metal porous medium 8-12, under the action of the metal framework surface catalyst, the raw material gas is continuously converted and releases reaction heat, and the temperature of the area where the intermediate porosity metal porous medium 8-12 is located is continuously reduced due to moderate porosity; and finally, the low-porosity metal porous medium is contacted with the low-porosity metal porous medium 8-13, the feed gas is continuously converted and reaction heat is released under the action of the metal framework surface catalyst, and the temperature of the area where the low-porosity metal porous medium 8-13 is located is lower due to lower porosity. The regions where the high-porosity metal porous media 8-11, the middle-porosity metal porous media 8-12 and the low-porosity metal porous media 8-13 are located form a temperature field with gradually reduced temperature, and efficient transition from high reaction rate to high conversion rate can be completed. In the reaction process, reaction heat in 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 is transferred to the spark atmosphere outside the reactor shell through the flat plate type heat pipe; and finally, collecting the reaction gas material after the conversion from the gas outlet.
In addition, in another preferred embodiment of the present invention, a specific implementation manner of the Sabatier reaction gas separation system 9 is further provided, as shown in fig. 4, the components of which include a reaction gas separation pipeline 9-1, a water vapor condenser 9-2, a first gas-liquid separator 9-3, a precooler 9-4, a carbon dioxide condenser 9-5, a second gas-liquid separator 9-6, a methane liquefaction cold box 9-7, a low-temperature cooler 9-8, a third gas-liquid separator 9-9, a first low-temperature stop valve 9-10, a liquid methane return pipeline 9-12, a second low-temperature stop valve 9-13, and a third low-temperature stop valve 9-11.
Wherein a first passage and a second passage which form heat exchange contact are respectively arranged in the water vapor condenser 9-2, the precooler 9-4 and the carbon dioxide condenser 9-5;
the inlet end of the reaction gas separation pipeline 9-1 is used for introducing the reaction gas of the Sabatier device, and the outlet end is connected to a liquid methane storage tank 11. A first passage of a water vapor condenser 9-2, a first gas-liquid separator 9-3, a first passage of a precooler 9-4, a first passage of a carbon dioxide condenser 9-5, a second gas-liquid separator 9-6, a heat exchange pipeline in a methane liquefaction cold box 9-7, a third gas-liquid separator 9-9 and a first low-temperature stop valve 9-10 are sequentially connected between an inlet end and an outlet end of a reaction gas separation pipeline 9-1; the second passages of the water vapor condenser 9-2 and the precooler 9-4 are used for introducing mars atmosphere so as to cool the first passages; the methane liquefaction cold box 9-7 is provided with a low-temperature cold machine 9-8, a cold head of the low-temperature cold machine 9-8 is in heat exchange contact with a heat exchange pipeline in the methane liquefaction cold box 9-7, and the temperature of the cold head can liquefy methane in the Sabatier device reaction gas flowing through the heat exchange pipeline.
The inlet end of the liquid methane return pipeline 9-12 is connected with a 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 of the liquid methane return pipeline is connected with a 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 is sequentially connected with a second low-temperature stop valve 9-13, a second passage of the carbon dioxide condenser 9-5 and a third low-temperature stop valve 9-11 from the inlet end to the outlet end.
The selection and specific form of the above components can be adjusted according to actual needs, in this embodiment, the low-temperature cooler 9-8 is a stirling-type low-temperature cooler, and the first gas-liquid separator 9-3, the second gas-liquid separator 9-6, and the third gas-liquid separator 9-9 can all be centrifugal gas-liquid separators. The water vapor condenser 9-2 and the precooler 9-4 adopt fin tube type heat exchangers. The carbon dioxide condenser 9-5 adopts a liquid-liquid plate heat exchanger. The heat exchange pipeline in the methane liquefaction cold box 9-7 is connected with the cold head of the low-temperature cooler 9-8 in a coil form, and a heat-conducting medium is filled between the heat exchange pipeline and the cold head.
Based on the Sabatier reaction gas separation system 9, the process of specifically performing component separation and liquefaction on the reaction gas of the Sabatier device is as follows:
the Mars atmospheric temperature is monitored in real time, the Sabatier device reaction gas is separated and liquefied in a first operation mode when the Mars atmospheric temperature can condense carbon dioxide in the reaction gas, and the Sabatier device reaction gas is separated and liquefied in a second operation mode when the Mars atmospheric temperature cannot condense carbon dioxide in the reaction gas.
Wherein the first mode of operation is as follows:
s11, starting a first gas-liquid separator 9-3, a second gas-liquid separator 9-6, a low-temperature cooler 9-8 and a third gas-liquid separator 9-9, opening a first low-temperature stop valve 9-10, and closing a second low-temperature stop valve 9-13 and a third low-temperature stop valve 9-11; the Mars atmosphere is respectively input into a second passage of the water vapor condenser 9-2 and a second passage of the precooler 9-4 through the fan, and then cold energy is provided for the respective first passages;
s12, inputting the original reaction gas from the Sabatier device into a reaction gas separation pipeline 9-1, and adjusting the Martian atmospheric flow input into a second passage of a water vapor condenser 9-2 to ensure that the water vapor in the original reaction gas absorbs the cold energy of Martian atmosphere in the process of flowing through a first passage of the water vapor condenser 9-2 to complete liquefaction so as to become a first gas-liquid two-phase mixture of which the temperature is not lower than 273.15K; the first gas-liquid two-phase mixture continuously enters a first gas-liquid separator 9-3 to separate and recover liquid water, and a first residual reaction gas only containing carbon dioxide, methane and hydrogen is obtained;
s13, continuously introducing the first residual reaction gas into a first passage of a precooler 9-4, and liquefying carbon dioxide in the first residual reaction gas after absorbing cold of Mars atmosphere by adjusting Mars atmospheric flow input into a second passage of the precooler 9-4 so as to obtain a second gas-liquid two-phase mixture; the second gas-liquid two-phase mixture continuously enters a second gas-liquid separator 9-6 through a first passage of a carbon dioxide condenser 9-5 to separate and recover liquid carbon dioxide, and a second residual reaction gas only containing methane and hydrogen is obtained;
s14, continuously introducing the second residual reaction gas into a methane liquefaction cold box 9-7, and liquefying methane in the second residual reaction gas after heat exchange with a cold head by controlling the temperature of the cold head of a low-temperature cooler 9-8 so as to obtain a third gas-liquid two-phase mixture; the third gas-liquid two-phase mixture continuously enters a third gas-liquid separator 9-9 to separate liquid methane and hydrogen, the hydrogen is directly discharged and recycled, and the liquid methane is stored in a liquid methane storage tank 11;
wherein the second mode of operation is as follows:
s21, starting a first gas-liquid separator 9-3, a second gas-liquid separator 9-6, a low-temperature cooler 9-8 and a third gas-liquid separator 9-9, and opening a first low-temperature stop valve 9-10, a second low-temperature stop valve 9-13 and a third low-temperature stop valve 9-11; the Mars atmosphere is respectively input into a second passage of the water vapor condenser 9-2 and a second passage of the precooler 9-4 through the fan, and then cold energy is provided for the respective first passages;
s22, inputting the original reaction gas from the Sabatier device into a reaction gas separation pipeline 9-1, and adjusting the Martian atmospheric flow input into a second passage of a water vapor condenser 9-2 to ensure that the water vapor in the original reaction gas absorbs the cold energy of Martian atmosphere in the process of flowing through a first passage of the water vapor condenser 9-2 to complete liquefaction so as to become a first gas-liquid two-phase mixture of which the temperature is not lower than 273.15K; continuously feeding the first gas-liquid two-phase mixture into a first gas-liquid separator 9-3 to separate and recover liquid water, so as to obtain a first residual reaction gas only containing carbon dioxide, methane and hydrogen;
s23, continuously introducing the first residual reaction gas into a first passage of a precooler 9-4, cooling the first residual reaction gas to a temperature close to that of Mars atmosphere by adjusting the Mars atmosphere flow input into a second passage of the precooler 9-4, then introducing the first residual reaction gas into the first passage of a carbon dioxide condenser 9-5, continuously absorbing the liquid methane cold in the second passage of the carbon dioxide condenser 9-5, and completing the liquefaction of carbon dioxide so as to obtain a second gas-liquid two-phase mixture; the second gas-liquid two-phase mixture continuously enters a second gas-liquid separator 9-6 to separate and recover liquid carbon dioxide, and a second residual reaction gas only containing methane and hydrogen is obtained;
s24, mixing the second residual reaction gas with methane subjected to heat absorption vaporization in the liquid methane return pipeline 9-12, continuously introducing the mixture into a methane liquefaction cold box 9-7, and liquefying the methane in the second residual reaction gas after heat exchange with a cold head by controlling the temperature of the cold head of the low-temperature cooler 9-8 so as to obtain a third gas-liquid two-phase mixture; and the third gas-liquid two-phase mixture continuously enters a third gas-liquid separator 9-9 to separate liquid methane and hydrogen, the hydrogen is directly discharged and recovered, part of the liquid methane reflows to a second passage of a carbon dioxide condenser 9-5 through a liquid methane reflow pipeline 9-12 to be used for liquefying carbon dioxide, and the rest part of the liquid methane is directly stored in a liquid methane storage tank 11.
Finally, the invention also provides an in-situ preparation method of the Mars surface carrier rocket propellant by utilizing the integrated system shown in figure 1, which comprises the following steps:
s1, enriching Mars atmosphere through a carbon dioxide capture system 7, obtaining high-purity carbon dioxide gas, and then conveying carbon dioxide to a Sabatier reduction system 8 through a liquid methane preparation pipeline 1;
s2, conveying the water-containing minerals on the surface of the mars to a water vapor extraction system 13 through a water-containing mineral conveying system 12, extracting water vapor from the water-containing minerals through the water vapor extraction system 13, and conveying the water vapor to an electrolytic water system 14;
s3, the water electrolysis system 14 electrolyzes water to prepare hydrogen and oxygen, the hydrogen is conveyed to the Sabatier reduction system 8 through the hydrogen pipeline 5, the oxygen is divided into two outputs, one of the two outputs is conveyed to the oxygen liquefaction system 15 through the liquid oxygen preparation pipeline 2, the oxygen is liquefied by the oxygen liquefaction system 15 and then stored in the liquid oxygen storage tank 16, and the other output is conveyed to the life support system 10 through the oxygen pipeline 6;
s4, the Sabatier reduction system 8 utilizes carbon dioxide gas conveyed by the carbon dioxide capture system 7 and hydrogen transmitted by the water electrolysis system 14 as raw materials, methane and water are generated through Sabatier reaction under the action of a catalyst, reaction gas containing four components of methane, water vapor, carbon dioxide and hydrogen is generated, the reaction gas is conveyed to the Sabatier reaction gas separation system 9 to separate the four components, the separated carbon dioxide and hydrogen return to the Sabatier reduction system 8 and are mixed with the carbon dioxide gas conveyed by the carbon dioxide capture system 7 and the hydrogen transmitted by the water electrolysis system 14 to be used as raw material gas, the separated methane is stored in a liquid methane storage tank 11 in a liquid methane form, and the separated water enters the water electrolysis system 14 through a water vapor pipeline 4 to be electrolyzed together with water extracted by the water vapor extraction system 13.
The above-described embodiments are merely preferred embodiments of the present invention, which should not be construed as limiting the invention. Various changes and modifications may be made by one of ordinary skill in the pertinent art without departing from the spirit and scope of the present invention. Therefore, the technical scheme obtained by adopting the mode of equivalent replacement or equivalent transformation is within the protection scope of the invention.
Claims (10)
1. An integrated system for in-situ preparation of a propellant of a Mars surface carrier rocket is characterized by comprising a liquid methane preparation pipeline (1), a liquid oxygen preparation pipeline (2), a mixed gas pipeline (3), a water vapor pipeline (4), a hydrogen pipeline (5) and an oxygen pipeline (6);
the liquid methane preparation pipeline (1) is sequentially connected with a carbon dioxide capture system (7), a Sabatier reduction system (8), a Sabatier reaction gas separation system (9) and a liquid methane storage tank (11);
the liquid oxygen preparation pipeline (2) is sequentially connected with a water-containing mineral substance conveying system (12), a water vapor extraction system (13), an electrolytic water system (14), an oxygen liquefaction system (15) and a liquid oxygen storage tank (16);
the mixed gas pipeline (3) is connected with a Sabatier reaction gas separation system (9) and a Sabatier reduction system (8);
the water vapor pipeline (4) is connected with the Sabatier reaction gas separation system (9) and the electrolytic water system (14);
the hydrogen pipeline (5) is connected with an electrolytic water system (14) and a Sabatier reduction system (8);
the oxygen pipeline (6) is connected with the electrolytic water system (14) and external aerobic equipment;
the carbon dioxide capture system (7) is used for capturing carbon dioxide from Mars atmosphere and inputting the carbon dioxide into the Sabatier reduction system (8) as a raw material;
the Sabatier reduction system (8) is used for generating methane and water through a Sabatier reduction reaction by taking carbon dioxide and hydrogen as raw materials;
the Sabatier reaction gas separation system (9) is used for carrying out component separation on reaction gas output by the Sabatier reduction system (8), a mixture of unreacted carbon dioxide and hydrogen obtained by separation returns to the Sabatier reduction system (8) through the mixed gas pipeline (3) to be used as a raw material again, methane obtained by separation is stored in the liquid methane storage tank (11) in a liquid methane form, and water obtained by separation enters the electrolytic water system (14) through the water vapor pipeline (4);
the hydrous mineral conveying system (12) is used for conveying hydrous minerals collected on mars into the water vapor extraction system (13), extracting water in the hydrous minerals by the water vapor extraction system (13) and conveying the extracted hydrous minerals into the electrolytic water system (14);
the electrolytic water system (14) is used for electrolyzing water to prepare hydrogen and oxygen, the prepared hydrogen is input into the Sabatier reduction system (8) through a hydrogen pipeline (5) to serve as a raw material, one path of the prepared oxygen is input into an oxygen liquefaction system (15) to be liquefied and then stored into a liquid oxygen storage tank (16), and the other path of the prepared oxygen is input into external aerobic equipment through an oxygen pipeline (6).
2. The integrated mars surface launch vehicle propellant in-situ preparation system of claim 1, wherein said carbon dioxide capture system (7) comprises a carbon dioxide liquefaction line (7-1), a first inter-stage cooler (7-4), and a second inter-stage cooler (7-8);
a first passage and a second passage which form heat exchange contact are arranged in the first-stage intercooler (7-4) and the second-stage intercooler (7-8);
the inlet end of the carbon dioxide liquefaction pipeline (7-1) is used for introducing Mars atmosphere, and the outlet end of the carbon dioxide liquefaction pipeline is connected with a low-temperature gas-liquid separator (7-11); a carbon dioxide liquefaction pipeline (7-1) is sequentially connected with a filter (7-2), an electric heater (7-3), a first passage of a first inter-stage cooler (7-4), a low-temperature fan (7-5), a first-stage compressor (7-6), a second passage of the first inter-stage cooler (7-4), a second-stage compressor (7-7), a first passage of a second inter-stage cooler (7-8), a water vapor adsorber (7-9), a carbon dioxide condenser (7-10) and a low-temperature gas-liquid separator (7-11) from an inlet end to an outlet end;
and a gas phase outlet of the low-temperature gas-liquid separator (7-11) is emptied, a liquid phase outlet is connected with a second passage of the second inter-cooler (7-8) through an output pipeline (7-12), and a second passage outlet of the second inter-cooler (7-8) is connected with the liquid methane preparation pipeline (1).
3. The integrated mars surface launch vehicle propellant in-situ preparation system of claim 1, wherein said Sabatier reduction system (8) comprises an insulated reactor housing having an air inlet and an air outlet in a reaction chamber inside the reactor housing;
the reaction cavity is divided into a high-temperature reaction zone (8-4) and a gradient temperature field reaction zone (8-5) by an annular heat insulation partition plate (8-10);
a heater (8-9) for heating the feed gas of the Sabatier reaction to the initial reaction temperature is arranged in the high-temperature reaction zone (8-4), and a Sabatier reaction catalyst is coated on the surface of the heater (8-9);
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) are sequentially arranged in the gradient temperature field reaction zone (8-5) along the air inlet direction, the porosity of the first metal porous medium layer (8-11), the porosity of the second metal porous medium layer (8-12) and the porosity of the third metal porous medium layer (8-13) are decreased gradually, and the surface of the medium is coated with a Sabatier reaction catalyst; the three metal porous medium layers are subjected to heat exchange with external spark atmosphere through flat plate heat pipes penetrating through the reactor shell, so that Sabatier reaction heat in the three metal porous medium layers can be transferred to the spark atmosphere;
and after being introduced from the gas inlet, the raw gas flows through the surfaces of the heaters (8-9) in the high-temperature reaction zone (8-4) and 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) in the gradient temperature field reaction zone (8-5) in sequence and is discharged from the gas outlet.
4. The integrated system for the in-situ preparation of Mars surface launch vehicle propellant as claimed in claim 1, wherein the Sabatier reaction gas separation system (9) comprises a reaction gas separation line (9-1), a moisture condenser (9-2), a precooler (9-4), a carbon dioxide condenser (9-5) and a liquid methane return line (9-12);
wherein a first passage and a second passage which form heat exchange contact are respectively arranged in the water vapor condenser (9-2), the precooler (9-4) and the carbon dioxide condenser (9-5);
the inlet end of the reaction gas separation pipeline (9-1) is used for introducing a reaction gas of the Sabatier device, and the outlet end of the reaction gas separation pipeline is connected to a liquid methane storage tank (11); a reaction gas separation pipeline (9-1) is sequentially connected with a first passage of a water vapor condenser (9-2), a first gas-liquid separator (9-3), a first passage of a precooler (9-4), a first passage of a carbon dioxide condenser (9-5), a second gas-liquid separator (9-6), a heat exchange pipeline in a methane liquefaction cold box (9-7), a third gas-liquid separator (9-9) and a first low-temperature stop valve (9-10) from an inlet end to an outlet end; the second passages of the water vapor condenser (9-2) and the precooler (9-4) are used for introducing Mars atmosphere so as to cool the first passages; a low-temperature cooler (9-8) is arranged on the methane liquefaction cold box (9-7), a cold head of the low-temperature cooler (9-8) is in heat exchange contact with a heat exchange pipeline in the methane liquefaction cold box (9-7), and the temperature of the cold head can liquefy methane in the Sabatier device reaction gas flowing through the heat exchange pipeline;
the inlet end of the liquid methane return pipeline (9-12) is connected with a 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 of the liquid methane return pipeline is connected with a reaction gas separation pipeline (9-1) between the second gas-liquid separator (9-6) and the methane liquefaction cold box (9-7); and a liquid methane return pipeline (9-12) is sequentially connected with a second low-temperature stop valve (9-13), a second passage of the carbon dioxide condenser (9-5) and a third low-temperature stop valve (9-11) from the inlet end to the outlet end.
5. The integrated system for in-situ preparation of Mars surface carrier rocket propellant as claimed in claim 1, wherein the oxygen liquefaction system (15) pre-cools oxygen by using cold energy of Mars atmosphere in advance, and then cools and liquefies the oxygen by a low-temperature cooler.
6. The integrated mars surface launch vehicle propellant in-situ preparation system of claim 5, wherein said cryogenic chiller is a stirling cryogenic chiller.
7. The integrated mars surface launch vehicle propellant in-situ preparation system of claim 1, wherein the water vapor extraction system (13) is a microwave heating device for obtaining pure water vapor by microwave heating of water-containing minerals.
8. The integrated mars surface launch vehicle propellant in-situ preparation system of claim 1, wherein said electrolysis water system (14) is a photocatalytic assisted electrolysis water system.
9. The integrated mars surface launch vehicle propellant in-situ preparation system of claim 1, wherein said external aerobic device is a life support system (10).
10. A method for the in situ preparation of a propellant for a Mars surface launch vehicle using a system according to any one of claims 1 to 9, comprising:
s1, enriching Mars atmosphere through a carbon dioxide capture system (7) and obtaining high-purity carbon dioxide gas, and then conveying the carbon dioxide to a Sabatier reduction system (8) through a liquid methane preparation pipeline (1);
s2, conveying the water-containing minerals on the surface of the mars to a water vapor extraction system (13) through a water-containing mineral conveying system (12), extracting water vapor from the water-containing minerals through the water vapor extraction system (13), and conveying the water vapor to an electrolytic water system (14);
s3, electrolyzing water by an electrolytic water system (14) to prepare hydrogen and oxygen, wherein the hydrogen is conveyed to a Sabatier reduction system (8) through a hydrogen pipeline (5), the oxygen is divided into two outputs, one of the two outputs is conveyed to an oxygen liquefaction system (15) through a liquid oxygen preparation pipeline (2), the oxygen is liquefied by the oxygen liquefaction system (15) and then stored in a liquid oxygen storage tank (16), and the other output is conveyed to a life support system (10) through an oxygen pipeline (6);
s4, the Sabatier reduction system (8) uses carbon dioxide gas delivered by the carbon dioxide capture system (7) and hydrogen delivered by the water electrolysis system (14) as raw materials, methane and water are generated through Sabatier reaction under the action of a catalyst, reaction gas containing four components of methane, water vapor, carbon dioxide and hydrogen is generated, the reaction gas is delivered 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), the carbon dioxide gas and the hydrogen delivered by the water electrolysis system (14) are mixed to be used as raw material gas, the separated methane is stored in a liquid methane storage tank (11) in a form of liquid methane, and the separated water enters the water electrolysis system (14) through the water vapor pipeline (4) to be electrolyzed together with the water extracted by the water vapor extraction system (13).
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| PCT/CN2023/101629 WO2024041146A1 (en) | 2022-08-25 | 2023-06-21 | Integrated system and method for mars surface carrier rocket propellant in-situ preparation |
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| WO2024041146A1 (en) * | 2022-08-25 | 2024-02-29 | 北京航天试验技术研究所 | Integrated system and method for mars surface carrier rocket propellant in-situ preparation |
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