A multi-energy supply system for a lunar base during the lunar night based on carbon, hydrogen, and oxygen cycles

Abstract

This invention proposes a multi-energy supply system for a lunar base across the lunar night based on a carbon-hydrogen-oxygen cycle, belonging to the field of lunar base cold, heat, and electricity supply systems. It solves the problem that existing lunar bases cannot meet their energy system requirements for cold and heat energy, in addition to electricity. It includes a chemical thermal storage subsystem, a gas turbine subsystem, and an adsorption refrigeration cycle subsystem. The chemical thermal storage subsystem absorbs solar energy during the lunar day, converting thermal energy into chemical energy and storing it. The gas turbine subsystem outputs electricity through its turbine, and the adsorption refrigeration subsystem utilizes the waste heat from the gas turbine subsystem to output cold energy. This invention enables the supply of cold, heat, and electricity to the lunar base across the lunar night, while simultaneously improving energy quality and enhancing the output capacity of power generation equipment through chemical thermal storage technology.

Description

Technical Field

[0001] This invention belongs to the field of cold, heat, and power supply systems for lunar bases, and in particular relates to a multi-energy supply system for lunar bases across lunar nights based on the carbon, hydrogen, and oxygen cycle. Background Technology

[0002] Extraterrestrial space bases centered on the lunar base will become the focus of future manned spaceflight activities, and are an inevitable trend for China's space program and deep space exploration.

[0003] Currently, the primary challenge lies in how astronauts can achieve extended stays at lunar bases. The energy system is crucial for the construction of long-term manned lunar bases. Compared to traditional spacecraft power generation systems, the Moon presents several unique challenges: 1) Complex solar radiation: Due to the low solar altitude angle (-1.5° to +1.5°) and the 360° change in solar azimuth with a lunar cycle, photovoltaic array power generation is highly susceptible to sunlight conditions, hindering its application on the Moon; 2) Complex geographical conditions: If a site is chosen near the lunar south pole, the presence of craters makes the lunar surface uneven, making it difficult to construct lunar base buildings. Furthermore, photovoltaic panels are easily blocked by mountain edges, reducing power generation capacity; 3) A long lunar night of 14 Earth days: To achieve long lunar night operations, considering the constraints of volume and weight transfer between Earth and the Moon, traditional combinations of solar cells and batteries are insufficient.

[0004] Therefore, it is urgent to start from the mission requirements of the lunar base for its energy system, adapt to local conditions, combine existing mature energy systems on Earth, innovate the system architecture, and conduct necessary theoretical analysis. Furthermore, in addition to electricity, the demand for cooling and heating energy cannot be met, and research on the combined cooling, heating, and power supply for the lunar base is insufficient. Summary of the Invention

[0005] In view of this, and in order to solve the technical problems mentioned in the background section, this invention proposes a multi-energy supply system for a lunar base across the lunar night based on a carbon-hydrogen-oxygen cycle. This invention has two key features: first, it enables the supply of heating, cooling, and electrical energy to the lunar base across the lunar night; second, it utilizes chemical thermal storage technology to enhance the energy level and increase the output capacity of the power generation equipment.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: a lunar base multi-energy supply system based on carbon, hydrogen, and oxygen cycle, comprising a chemical thermal storage subsystem, a gas turbine subsystem, and an adsorption refrigeration cycle subsystem. The chemical thermal storage subsystem absorbs solar energy during the lunar day, converts thermal energy into chemical energy and stores it. The gas turbine subsystem outputs electrical energy through a turbine. The adsorption refrigeration subsystem utilizes the waste heat of the gas turbine subsystem to output cold energy.

[0007] The chemical thermal storage subsystem includes a dish-type solar collector and a reduction reaction chamber. The dish-type solar collector supplies heat from the solar thermal source to the reduction reaction chamber. Methane and water vapor produced by fermentation in the lunar base's life support cabin are transported to the reduction reaction chamber. Under the action of the solar thermal source, a methane reforming reaction and a hydrogen reduction oxygen carrier reaction occur, and the heat is stored in the reduction reaction chamber.

[0008] The gas turbine subsystem includes a gas reaction chamber, a turbine, a regenerator, and a compressor. The circulating working fluid is air, which is generated in the life support cabin of the lunar base. After being pressurized by the compressor, the air enters the gas reaction chamber to undergo an oxidation reaction. The gas reaction chamber is then connected to the turbine and the regenerator in sequence. The solid product oxygen carrier after the reaction is sent back to the reduction reaction chamber to absorb heat again.

[0009] The adsorption-type refrigeration cycle subsystem includes an absorber, a generator, an evaporator, and a radiator, which are connected end to end. The generator is sequentially connected to a heat exchanger and a life support module for the lunar base.

[0010] Furthermore, the dish-type solar collector is a solar energy reflection structure, including an arc-shaped structure and a base, wherein the arc-shaped structure is mounted on the base to reflect sunlight.

[0011] Furthermore, the reduction reaction chamber is equipped with several oxygen carriers, and the reaction temperature is 450°C.

[0012] Furthermore, the gas reaction chamber is provided with several reduced oxygen carriers, which undergo a strongly exothermic oxidation reaction at a temperature of 900°C.

[0013] Furthermore, the adsorbent is located in the absorber and generator, while the refrigerant flows throughout the entire adsorption refrigeration cycle subsystem.

[0014] Furthermore, in the absorber, the adsorbent adsorbs the refrigerant; when the system needs to start the refrigeration cycle, the generator is heated, the temperature of the adsorbent rises, causing the adsorption equilibrium to be broken, and the adsorbent begins to desorb the refrigerant; when the refrigerant vapor enters the radiator, it releases heat through radiation to deep space, the temperature drops, and after reaching saturation, it begins to condense into a liquid; the evaporator is where the refrigeration system generates cooling capacity, the liquid refrigerant absorbs heat and vaporizes in the evaporator, thereby achieving the cooling effect.

[0015] Furthermore, after absorbing heat through the adsorption-type refrigeration cycle subsystem, the heat energy is output under the action of the heat exchanger, and the final exhaust gas is input into the life support cabin of the lunar base.

[0016] Furthermore, the adsorption-type refrigeration subsystem uses a porous medium formed from lunar soil sintering as the adsorbent and water as the refrigerant.

[0017] Furthermore, the radiator is a heat pipe type radiator, which uses heat pipes to achieve rapid heat transfer from high-temperature fluid to the radiating surface.

[0018] Compared with existing technologies, the beneficial effects of the lunar base multi-energy supply system based on the carbon-hydrogen-oxygen cycle described in this invention are:

[0019] (1) The present invention uses chemical thermal storage technology, which effectively solves the problems of no light on the lunar night and fluctuating heat sources during the lunar day.

[0020] (2) The chemical reaction in the reaction chamber of this invention effectively increases the gas temperature and enhances the work capacity of the gas turbine.

[0021] (3) The present invention uses chemical thermal storage technology, gas turbine power generation technology and adsorption refrigeration technology to realize the supply of cold and heat power to the lunar base. Attached Figure Description

[0022] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0023] Figure 1 This is a schematic diagram of the structure of the lunar base multi-energy supply system based on the carbon-hydrogen-oxygen cycle as described in this invention;

[0024] In the diagram: 1. Disc collector; 2. Reduction reaction chamber; 3. Gas reaction chamber; 4. Regenerator; 5. Turbine; 6. Compressor; 7. Motor; 8. Absorber; 9. Generator; 10. Radiator; 11. Evaporator; 12. Heat exchanger; 13. Lunar base life support capsule; 14. Oxygen carrier; 15. Reduced oxygen carrier. Specific implementation methods

[0025] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of the present invention can be combined with each other, and the described embodiments are only some embodiments of the present invention, not all embodiments.

[0026] For a lunar base, the energy supply system is undoubtedly of paramount importance, as the production of any material is inextricably linked to electricity. Megawatt-level energy demands must be met through a thermal power generation system. Furthermore, adsorption refrigeration technology can rapidly transfer heat from the lunar base's compartments. These two systems can fulfill the base's cooling, heating, and electrical needs. Moreover, chemical thermal storage technology can effectively address the challenges of the lunar night's lack of sunlight and the fluctuating nature of solar energy. In the future construction of the lunar base's energy system, improving energy efficiency and reliability will provide solid support for human activities on the moon.

[0027] The following is combined Figure 1 This patent will be further illustrated with specific examples:

[0028] A multi-energy supply system for a lunar base during the lunar night, based on a carbon-hydrogen-oxygen cycle, comprises a chemical thermal storage subsystem, a gas turbine subsystem, and an adsorption-type refrigeration cycle subsystem. The chemical thermal storage subsystem absorbs solar energy during the lunar day, converting thermal energy into chemical energy and storing it. The gas turbine subsystem outputs electrical energy through a turbine. The adsorption-type refrigeration subsystem utilizes the waste heat from the gas turbine subsystem to output cooling energy. This invention, through the organic combination of these three subsystems, can effectively supply lunar cooling, thermal, and electrical energy, primarily solving the energy supply difficulties caused by the variable temperature zone of the moon and the lack of sunlight during the lunar night.

[0029] The chemical thermal storage subsystem consists of a dish-type solar collector 1 and a reduction reaction chamber 2. The dish-type solar collector 1 is a solar energy reflector structure. The chemical thermal storage subsystem utilizes methane and water vapor produced by fermentation in the lunar base's life support capsule 13. Under the action of a solar heat source, a methane reforming reaction and a hydrogen reduction reaction of the oxygen carrier occur, storing the heat in the oxygen carrier 14 in the reduction reaction chamber 2. The reaction temperature is approximately 450°C, thereby achieving the effect of chemical thermal storage.

[0030] The described chemical thermal energy storage subsystem converts thermal energy into chemical energy for storage, solving the problems of fluctuating solar energy and insufficient energy supply. Furthermore, upgrading the 450°C solar heat source to a 900°C chemical energy heat source significantly improves the energy level, substantially enhances the power generation capacity of the equipment, and addresses the high-power energy needs of the lunar base.

[0031] To address the problem of prolonged darkness during the lunar night, part of the solid fuel produced in reduction reaction chamber 2 is used for energy supply during the lunar day, while the other part is stored to meet the energy demand during the lunar night.

[0032] The gas turbine subsystem consists of a gas reaction chamber 3, a turbine 5, a regenerator 4, and a compressor 6, with air as the circulating working fluid. First, a large amount of air is generated in the lunar base's life support module 13. After being pressurized by the compressor 6, it enters the gas reaction chamber 3 and undergoes a strongly exothermic oxidation reaction with the reduced oxygen carrier 15 inside. The reaction temperature is 900℃, significantly increasing the air temperature to become a high-temperature, high-pressure gas. Under the action of the turbine 5, it expands, performs work, and outputs electrical energy. Furthermore, the regenerator 4 is used to increase the compressor outlet temperature, improving energy utilization. The solid product oxygen carrier after the reaction is mechanically pushed back to the reduction reaction chamber 2 to absorb heat again.

[0033] The gas turbine subsystem features a coaxial design of compressor 6, turbine 5, and motor 7, employing a three-in-one design concept to reduce space volume.

[0034] The adsorption-type refrigeration cycle subsystem consists of an absorber 8, a generator 9, a radiator 10, and an evaporator 11. The adsorbent is located in the absorber 8 and the generator 9, while the refrigerant flows throughout the entire refrigeration cycle.

[0035] In absorber 8, the adsorbent adsorbs the refrigerant. When the system needs to start the refrigeration cycle, generator 9 is heated, the temperature of the adsorbent rises, causing the adsorption equilibrium to be broken, and the adsorbent begins to desorb the refrigerant. When the refrigerant vapor enters radiator 10, it releases heat through radiation to deep space, its temperature drops, and it begins to condense into a liquid after reaching saturation. Evaporator 11 is where the refrigeration system generates cooling capacity. The liquid refrigerant absorbs heat and vaporizes in evaporator 11, thereby achieving the cooling effect. After absorbing heat through the adsorption refrigeration cycle subsystem, the heat energy is output under the action of heat exchanger 12. The final exhaust gas is input into the lunar base life support capsule 13, where carbon, hydrogen, and oxygen elements are cycled using internal plants.

[0036] The adsorption-based refrigeration subsystem uses a porous medium formed from sintered lunar regolith as the adsorbent and water as the refrigerant. The sintering process alters the physical structure of the lunar regolith, creating a rich porous structure with a large specific surface area and suitable pore structure. These pores provide attachment sites and transport channels for adsorbed substances, increasing the adsorbent's adsorption capacity for target substances.

[0037] The radiator 10 in the adsorption refrigeration subsystem is a heat pipe radiator, which uses heat pipes to achieve rapid heat transfer from high-temperature fluid to the radiating surface.

[0038] The methane in the lunar base life support capsule 13 is produced by microorganisms converting organic matter into methane, which is an in-situ resource of the lunar base and also realizes the recycling of carbon, hydrogen and oxygen elements.

[0039] The embodiments of the present invention disclosed above are merely illustrative of the invention. These embodiments do not exhaustively describe all details, nor do they limit the invention to the specific implementation methods described. Many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize the invention.

Claims

1. A multi-energy supply system for a lunar base during the lunar night based on a carbon-hydrogen-oxygen cycle, characterized in that: It includes a chemical thermal storage subsystem, a gas turbine subsystem, and an adsorption refrigeration cycle subsystem. The chemical thermal storage subsystem absorbs solar energy during the lunar day, converts thermal energy into chemical energy and stores it. The gas turbine subsystem outputs electrical energy through a turbine (5). The adsorption refrigeration cycle subsystem uses the waste heat of the gas turbine subsystem to output cold energy. The chemical thermal storage subsystem includes a dish collector (1) and a reduction reaction chamber (2). The dish collector (1) supplies heat from the solar thermal source to the reduction reaction chamber (2). The methane and water vapor produced by fermentation in the lunar base life support cabin (13) are transported to the reduction reaction chamber (2). Under the action of the solar thermal source, a methane reforming reaction and a hydrogen reduction oxygen carrier reaction occur, and the heat is stored in the reduction reaction chamber (2). The gas turbine subsystem includes a gas reaction chamber (3), a turbine (5), a regenerator (4), and a compressor (6). The circulating working fluid is air. The air generated in the lunar base life support cabin (13) is pressurized by the compressor (6) and enters the gas reaction chamber (3) to undergo an oxidation reaction. Then, the gas reaction chamber (3) is connected to the turbine (5) and the regenerator (4) in sequence. The solid product oxygen carrier after the reaction is sent back to the reduction reaction chamber (2) to absorb heat again. The adsorption-type refrigeration cycle subsystem includes an absorber (8), a generator (9), an evaporator (11), and a radiator (10). The absorber (8), generator (9), radiator (10), and evaporator (11) are connected end to end. The generator (9) is connected in sequence to a heat exchanger (12) and a lunar base life support module (13).

2. The lunar base multi-energy supply system based on carbon-hydrogen-oxygen cycle according to claim 1, characterized in that: The dish collector (1) is a solar energy reflection structure, including an arc-shaped structure and a base. The arc-shaped structure is installed on the base to reflect sunlight.

3. The lunar base multi-energy supply system based on carbon-hydrogen-oxygen cycle according to claim 1, characterized in that: The reduction reaction chamber (2) is equipped with several oxygen carriers (14), and the reaction temperature is 450℃.

4. The lunar base multi-energy supply system based on carbon-hydrogen-oxygen cycle according to claim 1, characterized in that: The gas reaction chamber (3) is provided with several reduced oxygen carriers (15), and the reduced oxygen carriers (15) undergo a strongly exothermic oxidation reaction at a temperature of 900°C.

5. The lunar base multi-energy supply system based on carbon-hydrogen-oxygen cycle according to claim 1, characterized in that: The adsorbent is located in the absorber (8) and the generator (9), while the refrigerant flows throughout the entire adsorption refrigeration cycle subsystem.

6. The lunar base multi-energy supply system based on carbon-hydrogen-oxygen cycle according to claim 5, characterized in that: In the absorber (8), the adsorbent adsorbs the refrigerant; When the system needs to start the refrigeration cycle, the generator (9) is heated, the temperature of the adsorbent rises, causing the adsorption equilibrium to be broken, and the adsorbent begins to desorb the refrigerant; when the refrigerant vapor enters the radiator (10), it releases heat through radiation to deep space, the temperature drops, and after reaching saturation, it begins to condense into liquid; the evaporator (11) is where the refrigeration system generates cold energy, and the liquid refrigerant absorbs heat and vaporizes in the evaporator, thereby achieving the refrigeration effect.

7. The lunar base multi-energy supply system based on carbon-hydrogen-oxygen cycle according to claim 6, characterized in that: After absorbing heat through the adsorption-type refrigeration cycle subsystem, the heat energy is output under the action of the heat exchanger (12), and the final exhaust gas is input into the lunar base life support cabin (13).

8. The lunar base multi-energy supply system based on carbon-hydrogen-oxygen cycle according to claim 1, 6, or 7, characterized in that: The adsorption-type refrigeration cycle subsystem uses a porous medium formed from lunar soil sintering as the adsorbent and water as the refrigerant.

9. The lunar base multi-energy supply system based on carbon-hydrogen-oxygen cycle according to claim 1, 6, or 7, characterized in that: The radiator (10) is a heat pipe type radiator, which uses heat pipes to achieve rapid heat transfer from high-temperature fluid to the radiating surface.

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