Lunar surface deployed human lunar outpost class regenerative heat storage dual loop thermal management building system

Abstract

This invention relates to a cascaded dual-loop thermal management building system for manned lunar research stations deployed on the moon. It addresses the technical challenge of achieving low-energy consumption and highly reliable constant temperature control in the extreme lunar surface environment. In this dual-loop thermal management building system, the inner and outer loop heat exchangers and phase change thermal storage modules are located inside the lunar regolith. The heat exchange terminals inside the cabin form a circulation loop with the inner and outer loop heat exchangers via an inner loop circulation pipe. The lunar surface heat collection components are connected to the inlet of the phase change thermal storage module via a first outer pipe. The working fluid outlet of the phase change thermal storage module is connected to a buried heat exchange pipe via a second outer pipe. The buried heat exchange pipe is connected to the inner and outer loop heat exchangers via third and fourth outer pipes. The inner and outer loop heat exchangers are connected to the lunar surface heat collection components via fifth and sixth outer pipes. This invention utilizes the lava tube space and lunar regolith enclosure to significantly reduce lunar diurnal thermal fluctuations and employs a dual-loop working fluid division of labor, adapting to efficient heat transfer and extreme environmental conditions.

Description

Technical Field

[0001] This invention belongs to the field of extraterrestrial building thermal engineering and structural integration technology, specifically relating to an embedded active thermal management building system and its thermal management method for a manned lunar research station. Background Technology

[0002] With the advancement of lunar exploration and deep space development activities, the demand for facilities such as long-term resident research stations, scientific research bases, and manned habitats on the lunar surface is becoming increasingly clear. The Moon's rotation period is approximately 27.3 days, and its lunar day-night cycle is close to 29.5 Earth days. Under vacuum conditions, the lunar surface can heat up to approximately 120°C when exposed to sunlight, and drop to approximately -170°C during prolonged periods of shade, exhibiting extreme diurnal temperature variations with long cycles. Furthermore, the lack of an atmosphere and convection for heat transfer means that heat exchange relies primarily on radiation and solid-state conduction. This results in lunar structures fixed in specific locations experiencing extreme and slowly changing external thermal boundary conditions throughout a complete lunar day-night cycle.

[0003] Current lunar base thermal control technology heavily relies on spacecraft-derived solutions. The cabin employs a single-layer metal shell covered with multi-layer insulation (MLI), with thermal management primarily dependent on external radiative heat sinks on the roof and internal resistance heaters. However, this design has fundamental flaws in the lunar vacuum environment. First, the external heat sinks are constantly exposed to high vacuum, strong ultraviolet radiation, and micrometeorites. Apollo mission data shows that electrostatic adsorption of lunar dust causes its thermal radiation efficiency to decrease by 42% within 30 days, and the deployment mechanism has a failure rate exceeding 35% under brittle conditions at -170°C. Second, the passive insulation of the single-layer shell cannot buffer the 708-hour diurnal thermal cycle. When the external lunar temperature fluctuates between -170°C and 120°C, the internal temperature, relying solely on MLI (equivalent U-value 0.25 W / m²·K), will passively fluctuate between -10°C and 35°C, far exceeding the safe range of 18°C ​​to 25°C required for manned missions. This forces the resistance heating system to operate under high load continuously during the lunar night. Taking a 10kW heat load module as an example, it requires 3.36MWh of electricity during a 14-day lunar night, corresponding to a photovoltaic array area of ​​over 200m². 2 This significantly increases launch mass and energy costs. Finally, the traditional approach separates thermal control from the building structure, and the heat dissipation fins, as additional components, compromise the integrity of the cabin's airtight layer, creating a high-risk point for micrometeorite perforation, posing significant risks to its reliability and maintainability. On the other hand, resistance heating relies on electricity supplied by Earth and cannot utilize in-situ resources such as lunar soil and lava tubes, thus significantly increasing the total system mass and launch cost, and resulting in low system redundancy.

[0004] In research aimed at lunar bases, although recent studies have attempted to introduce phase change materials (such as decanoic acid / lunar soil composite PCM), these materials remain attached to the surface of the cabin walls and are not deeply integrated with the geological structure, thus failing to mitigate lunar day-night thermal fluctuations. Furthermore, traditional thermal control systems also have limitations in terms of working fluid selection and system architecture. Orbital spacecraft often use a few working fluids such as water and ammonia to handle the entire heat transfer chain from the cabin to the radiators. While ensuring personnel safety, material compatibility, and a stable system temperature range, it is difficult to simultaneously meet the requirements of antifreeze, anti-boiling, leak prevention, and low toxicity of the working fluid. For fixed bases like manned lunar research stations, the various heat exchange components, pipelines, and working fluids of the thermal control system need to operate reliably for extended periods within a temperature range of -20°C to 40°C. This requires adapting to thermal gradients in extreme external cold / hot environments while maintaining a relatively constant cabin air temperature close to 20°C.

[0005] Therefore, there is an urgent need for a thermal management architecture that transforms the building itself into a heat exchange interface and combines high reliability with in-situ resource utilization capabilities, fundamentally solving the three major pain points of exposed component vulnerability, energy dependence, and temperature runaway risk, in order to meet the safe operation requirements of manned missions and critical equipment. Summary of the Invention

[0006] This invention addresses the technical problem of achieving low-energy consumption and highly reliable constant temperature control in the extreme lunar surface heat environment of manned lunar research stations, and provides a cascaded heat storage and release dual-loop thermal management building system for manned lunar research stations deployed on the moon.

[0007] The present invention relates to a dual-loop thermal management building system for a manned lunar research station based on lunar soil and lava tubes. The system includes a research station working compartment, an internal heat exchange terminal, internal and external loop heat exchangers, a phase change heat storage module, buried heat exchange tubes, and lunar surface heat collection components. The research station working compartment and lunar surface heat collection components are located on the surface of the lunar soil cover layer, the internal and external loop heat exchangers and the phase change heat storage module are located inside the lunar soil cover layer, and the buried heat exchange tubes are installed inside the lava tube wall.

[0008] The heat exchange terminal inside the cabin is installed inside the working cabin of the research station. The heat exchange terminal inside the cabin forms a circulation loop with the inner and outer loop heat exchangers through the inner loop circulation pipe. The first working fluid circulates in the inner loop circulation pipe.

[0009] The external circulation pipeline includes a first external pipe, a second external pipe, a third external pipe, a fourth external pipe, a fifth external pipe, a sixth external pipe, and multiple three-way valves. The external circulation pipeline contains a second working fluid. The outlet of the lunar surface heat collection component flows into the first medium port of the phase change heat storage module through the bypass of the first three-way valve, the first external pipe, and the second three-way valve. The second medium port of the phase change heat storage module flows into the buried heat exchange tube through the bypass of the third three-way valve and the second external pipe. The medium outlet of the buried heat exchange tube is connected to the medium inlet of the inner and outer loop heat exchangers through the third external pipe, the fourth three-way valve, and the fourth external pipe. The medium outlet of the inner and outer loop heat exchangers is connected to the bypass inlet of the fifth three-way valve through the fifth external pipe. One end of the sixth external pipe is connected to the first outlet of the fifth three-way valve, and the other end of the sixth external pipe is connected to the medium inlet of the lunar surface heat collection component. A sixth three-way valve is installed on the sixth external pipe.

[0010] The other medium outlet of the No. 2 three-way valve is connected to the bypass of the No. 4 three-way valve through the eighth external pipe, and the No. 2 outlet of the No. 5 three-way valve is connected to the medium inlet of the No. 3 three-way valve through the seventh external pipe.

[0011] Unlike existing spacecraft thermal control methods that primarily rely on bulkhead insulation, external heat dissipation fins, and resistance heating, the main features of this invention's dual-loop thermal management building system for manned lunar research stations include: first, utilizing lava tube space and lunar soil enclosure, enabling large-volume rock masses to participate in long-term heat storage and smoothing lunar diurnal thermal fluctuations through heat exchanger arrays; second, integrating phase change thermal storage materials with the building envelope to provide near-constant temperature heat storage / release capabilities near the target temperature zone; and third, employing a dual-loop working fluid division of labor, with the inner loop adapting to the safety requirements of human habitation and precision equipment, and the outer loop adapting to efficient heat transfer and extreme environmental conditions, with energy coupling between the two at the heat exchanger. This constructs a thermal management method for manned lunar research stations that combines aerospace thermal control precision, building energy-saving logic, and the ability to utilize lunar in-situ resources.

[0012] The cascaded heat storage and release dual-loop thermal management building system for manned lunar research stations deployed under the moon of this invention has the following significant beneficial effects:

[0013] First, at the thermal environment level, by utilizing the lunar soil cover layer and lava tube rock mass to form a large-volume thermal inertia buffer, and integrating phase change heat storage modules in the enclosure structure, this invention can transform the severe external thermal boundary conditions of -170℃ to 120℃ into a relatively slowly changing working temperature range of approximately -20℃ to 40℃ inside the system. This greatly reduces the temperature difference and dynamic range that the thermal control system needs to cope with, and provides a stable medium-temperature heat source / cold source for constant temperature control of the internal loop.

[0014] Secondly, in terms of energy consumption and equipment scale, taking a typical 10kW cabin heat load as an example, the traditional pure resistance heating scheme requires about 3.36MWh of electricity for heating during the entire lunar night cycle. However, this invention, through coupling with the lava tube heat storage and phase change heat storage module via an external loop, and combined with high-efficiency heat exchange equipment such as heat pumps, can reduce power consumption by about 60% to 70% under the same heating demand. Correspondingly, the photovoltaic array installation area and energy storage capacity can be reduced by about 50% to 65%, significantly reducing the total system mass and launch cost.

[0015] Third, in terms of reliability and safety, this invention replaces large-area exposed heat dissipation fins with an embedded heat exchange structure of lunar soil and lava tubes, reducing the number of vulnerable components susceptible to lunar dust cover, micrometeorite impacts, and thermal fatigue. Simultaneously, the separate working fluids in the internal and external circuits prevent highly toxic or high-pressure working fluids from entering the cabin's habitable area, reducing the risk of leakage accidents. Even in the event of a power supply or active thermal control system failure, the lava tube rock mass and phase change thermal storage module can still act as a passive thermal buffer, significantly delaying temperature changes within the cabin and buying time for crew evacuation or system recovery.

[0016] Fourth, in terms of building integration and in-situ resource utilization, this invention directly integrates thermal management functions into the enclosure structure and geological structure of the manned lunar research station. It can partially use sintered lunar soil or lunar soil-based composite materials to make phase change module shells, heat exchange tube supports, and enclosure components, realizing multi-functional integration of structure, shielding, and thermal management. This provides a scalable building and thermal integration technology path for the large-scale construction of future long-term lunar bases. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the overall structure of the dual-loop thermal management building system for a manned lunar research station based on lunar soil and lava tubes according to the present invention. The red line in the diagram represents the circulation route of the first working medium, and the blue line represents the circulation route of the second working medium.

[0018] Figure 2 This is a schematic diagram illustrating the workflow of the dual-loop thermal management building system for a manned lunar research station based on lunar soil and lava tubes, as shown in the embodiment. Detailed Implementation

[0019] Specific Implementation Method 1: This implementation method is based on a dual-loop thermal management building system for a manned lunar research station using lunar soil and lava tubes. The system includes a research station working compartment 1, an internal heat exchange terminal 2, an inner and outer loop heat exchanger 5, a phase change heat storage module 8, a buried heat exchange tube 9, and a lunar surface heat collection assembly 10. The research station working compartment 1 and the lunar surface heat collection assembly 10 are located on the surface of the lunar soil cover layer 12, the inner and outer loop heat exchanger 5 and the phase change heat storage module 8 are located inside the lunar soil cover layer 12, and the buried heat exchange tube 9 is installed inside the lava tube wall.

[0020] The heat exchange terminal 2 is installed inside the working chamber 1 of the research station. The heat exchange terminal 2 forms a circulation loop with the inner and outer loop heat exchangers 5 through the inner loop circulation pipe. The inner loop circulation pipe contains the first working fluid.

[0021] The external circulation pipeline includes a first external pipe 13, a second external pipe 16, a third external pipe 18, a fourth external pipe 19, a fifth external pipe 7, a sixth external pipe 21, and multiple three-way valves. A second working fluid circulates within the external circulation pipeline. The outlet of the lunar surface heat collection assembly 10 flows sequentially into the first medium port of the phase change heat storage module 8 through the bypass of the first three-way valve 27, the first external pipe 13, and the second three-way valve 26. The second medium port of the phase change heat storage module 8 flows into the buried heat exchanger through the bypass of the third three-way valve 29 and the second external pipe 16. Heat pipe 9, the medium outlet of the buried heat exchange pipe 9 is connected to the medium inlet of the inner and outer loop heat exchanger 5 in sequence through the third outer pipe 18, the fourth three-way valve 30 and the fourth outer pipe 19. The medium outlet of the inner and outer loop heat exchanger 5 is connected to the bypass inlet of the fifth three-way valve 25 through the fifth outer pipe 7. One end of the sixth outer pipe 21 is connected to the first outlet of the fifth three-way valve 25. The other end of the sixth outer pipe 21 is connected to the medium inlet of the lunar surface heat collection assembly 10. A sixth three-way valve 28 is installed on the sixth outer pipe 21.

[0022] The other medium outlet of the No. 2 three-way valve 26 is connected to the bypass of the No. 4 three-way valve 30 through the eighth external pipe 17, and the No. 2 outlet of the No. 5 three-way valve 25 is connected to the medium inlet of the No. 3 three-way valve 29 through the seventh external pipe 24.

[0023] The enclosure structure of the working cabin described in this embodiment includes, from the inside out, an airtight layer, a structural layer, and a phase change heat storage layer. A lunar regolith covering layer can be installed on the outside of the phase change heat storage layer. The lunar regolith covering layer provides radiation protection, micrometeorite protection, and thermal hysteresis, thereby achieving integrated construction of the building envelope and thermal management functions. The shell, heat exchange tube support components, and part of the enclosure structure of the phase change heat storage module are made of locally sourced sintered lunar regolith or lunar regolith-based composite materials to reduce the weight of structural and insulation materials transported from Earth, and to achieve the synergistic application of the thermal management system and in-situ resource utilization technology.

[0024] In this embodiment, the heat exchange tube array in the lava tube wall is arranged along the top and side walls of the lava tube and connected to the external loop working fluid pipeline. It is used to exchange heat with the large volume of rock mass within the system operating temperature range of -20℃ to 40℃, so that the lava tube rock mass acts as a long-term thermal inertia buffer to smooth lunar diurnal and seasonal heat load fluctuations. The lunar surface heat collection and heat dissipation assembly includes a solar collector plate and / or a radiant heat dissipation plate thermally coupled to the external loop working fluid pipeline. The lunar surface heat collection and heat dissipation assembly is connected to the external loop working fluid pipeline inside the lava tube through a vertical shaft. Under sunlight conditions, it transfers the heat obtained from lunar surface solar radiation to the phase change heat storage module and the lava tube rock mass. Under lunar night or overheating conditions, it radiates excess heat into deep space.

[0025] This implementation method is based on an integrated dual-loop thermal management building system using lunar soil and lava tubes, which improves the thermal control system from traditional external auxiliary equipment to a comprehensive system that integrates geology, architecture, and electromechanical systems.

[0026] Specific Implementation Method Two: This implementation method differs from Specific Implementation Method One in that the inner loop circulation pipeline is formed by the first inner pipe 20 and the second inner pipe 4. One end of the first inner pipe 20 is connected to the first working fluid outlet of the inner and outer loop heat exchanger 5, and the other end of the first inner pipe 20 is connected to the working fluid inlet of the heat exchange terminal 2 in the cabin. One end of the second inner pipe 4 is connected to the first working fluid inlet of the inner and outer loop heat exchanger 5, and the other end of the second inner pipe 4 is connected to the working fluid outlet of the heat exchange terminal 2 in the cabin.

[0027] Specific Implementation Method 3: This implementation method differs from Specific Implementation Method 2 in that an internal loop circulation pump 3 is installed on the second inner pipe 4.

[0028] Specific Implementation Method Four: This implementation method differs from Specific Implementation Methods One to Three in that the first working medium is silicone oil, fluorine-containing inert heat transfer fluid, or ethylene glycol solution.

[0029] The fluorinated inert heat transfer fluid described in this embodiment is a fluorinated liquid with electrical insulation, low volatility, and chemical stability, which can remain stable within the working temperature range of the chamber and is compatible with the pipeline materials.

[0030] In this embodiment, the first working fluid, namely the inner loop working fluid, has good fluidity, electrical insulation and material compatibility in the range of 0°C to 60°C, and is used for heat exchange in areas close to the crew compartment and precision equipment.

[0031] Specific Implementation Method 5: This implementation method differs from Specific Implementation Method 4 in that the fluorinated inert heat transfer fluid is a perfluoropolyether (PFPE) heat transfer fluid, a hydrofluoroether (HFE) heat transfer fluid, or a fluoroketone heat transfer fluid.

[0032] Specific Implementation Method Six: This implementation method differs from Specific Implementation Methods One to Five in that the second working medium is liquid ammonia, heat transfer oil, or liquid (or supercritical) CO2.

[0033] In this embodiment, the second working medium, namely the external loop working medium, is indirectly coupled to the internal space of the working chamber through the internal and external loop heat exchangers. The external loop working medium does not come into direct contact with the air inside the chamber, thereby improving heat transfer efficiency and reducing safety risks to the chamber environment.

[0034] Specific Implementation Method Seven: This implementation method differs from Specific Implementation Methods One to Six in that the phase change material in the phase change heat storage module 8 is an organic phase change material, an inorganic salt hydrate, or a lunar soil composite phase change material.

[0035] The lunar soil composite phase change material described in this embodiment includes, but is not limited to, a shaped phase change material formed by impregnating, encapsulating, or microencapsulating the above-mentioned organic phase change material or inorganic salt hydrate with sintered lunar soil or lunar soil-based porous ceramic / foam as the skeleton carrier, such as a composite system of sintered lunar soil porous skeleton loaded with paraffin-based phase change material or lunar soil-based porous carrier loaded with salt hydrate phase change material.

[0036] In this embodiment, the phase change material is preferably an organic phase change material, an inorganic salt hydrate, or a lunar soil composite phase change material with a melting point between -10°C and 30°C. The phase change heat storage module forms a heat storage zone that covers or is arranged in sections along the circumference of the working chamber inside the lava tube, so as to improve the thermal stability of the working chamber enclosure structure near the target temperature range.

[0037] Specific Implementation Method Eight: This implementation method differs from Specific Implementation Method Seven in that the organic phase change material is n-tetradecane, n-hexadecane, n-octadecane, lauric acid, myristic acid, palmitic acid, or polyethylene glycol; and the inorganic salt hydrate is a calcium chloride hydrate system (CaCl2·6H2O) or a sodium sulfate hydrate system (Na2SO4·10H2O).

[0038] Specific Implementation Method Nine: This implementation method differs from Specific Implementation Methods One to Eight in that the lunar surface heat collection component 10 is a solar heat collection plate.

[0039] Specific Implementation Method 10: This implementation method differs from Specific Implementation Methods 1 to 9 in that an external loop circulation pump 6 is provided on the fifth external pipe 7.

[0040] Specific Implementation Method Eleven: This implementation method differs from Specific Implementation Methods One through Ten in that the bypass of the No. 1 three-way valve 27 is connected to the medium inlet of the buried heat exchange tube 9 through the ninth outer pipe 14.

[0041] This embodiment, by setting a ninth outer pipe 14, can directly transport the heat obtained by the lunar surface heat collection component 10 to the buried heat exchange pipe 9 and exchange heat with the lava pipe wall when the phase change heat storage module 8 is full, temporarily not participating in heat exchange, or when it is necessary to reduce the external circuit pressure drop, so as to realize the heat storage of the rock mass and enhance the circulation efficiency and operational reliability of the external circuit.

[0042] Specific Implementation Method Twelve: This implementation method differs from Specific Implementation Methods One to Eleven in that the bypass of the No. 6 three-way valve 28 is connected to the buried heat exchange pipe 9 through the tenth outer pipe 15.

[0043] This embodiment, by setting a tenth outer pipe 15, allows the second working fluid to flow directly into the buried heat exchanger 9 through the tenth outer pipe 15 during lunar night or emergency conditions when it is necessary to cut off the circulation of the lunar surface heat collection component 10. This prevents the second working fluid from entering the lunar surface heat collection component 10 at the No. 6 three-way valve 28, but instead allows it to exchange heat with the lunar soil and the lava tube wall before returning to the inner and outer loop heat exchangers 5. This reduces the ineffective heat dissipation of the lunar surface heat collection component 10 into deep space. At the same time, the tenth outer pipe 15, as a bypass, can also shorten the outer loop circulation path, reduce the loop pressure drop, and improve the operational reliability of the buried heat exchanger 9 when it is used for heating alone.

[0044] Specific Implementation Method Thirteen: The method for thermal management in this implementation method using a dual-loop thermal management building system for a manned lunar research station based on lunar soil and lava tubes is as follows:

[0045] The data collection includes the air temperature inside the research station's working chamber, the temperature of the phase change thermal storage module, the temperature of the lava tube rock mass, the temperature of the lunar surface heat collection and dissipation components, and the lunar surface solar radiation status.

[0046] Determine if it is currently a sunny period. If it is, enter daytime mode. Under the premise of ensuring that the temperature inside the cabin is within the preset comfort range, use the external loop working fluid to preferentially store the waste heat and solar heat collected in the phase change heat storage module and lava tube rock mass. If it is not a sunny period, enter nighttime mode. Adjust the flow rate of the external loop working fluid to extract heat from the phase change heat storage module and lava tube rock mass, and transport it to the heat exchange terminal inside the cabin to heat the working cabin through the internal and external loop heat exchangers.

[0047] In both daytime and nighttime modes, the flow rate of the working fluid in the inner loop and the heat exchange capacity of the heat exchange terminal in the cabin are adjusted in a closed loop based on the cabin temperature feedback in order to keep the cabin air temperature stable at a target value close to 20°C.

[0048] In this implementation method, when the temperature of the phase change thermal storage module and the lava pipe rock mass is detected to be lower than the preset minimum safe temperature threshold in night mode, the control system will switch the operating status to energy-saving or emergency mode. By reducing the internal temperature setpoint, limiting non-critical loads and / or activating backup heat sources, the use time of the thermal storage can be extended and the safe operation of the life support system and critical equipment can be ensured.

[0049] Example: This example describes a dual-loop thermal management building system for a manned lunar research station based on lunar soil and lava tubes. The system includes a research station working compartment 1, an internal heat exchange terminal 2, internal and external loop heat exchangers 5, a phase change thermal storage module (PCM) 8, buried heat exchange tubes 9, a lunar surface heat collection assembly 10, and a control module 11. The research station working compartment 1 and the lunar surface heat collection assembly 10 are located on the surface of the lunar soil cover layer 12, the internal and external loop heat exchangers 5 and the phase change thermal storage module 8 are located inside the lunar soil cover layer 12, and the buried heat exchange tubes 9 are installed inside the lava tube wall inside the lunar soil cover layer 12.

[0050] The heat exchange terminal 2 inside the cabin is installed inside the working cabin 1 of the research station. The heat exchange terminal 2 inside the cabin forms a circulation loop with the inner and outer loop heat exchangers 5 through the inner loop circulation pipe. The inner loop circulation pipe is filled with a first working fluid. One end of the first inner tube 20 is connected to the first working fluid outlet of the inner and outer loop heat exchangers 5, and the other end of the first inner tube 20 is connected to the working fluid inlet of the heat exchange terminal 2 inside the cabin. One end of the second inner tube 4 is connected to the first working fluid inlet of the inner and outer loop heat exchangers 5, and the other end of the second inner tube 4 is connected to the working fluid outlet of the heat exchange terminal 2 inside the cabin.

[0051] The external circulation pipeline includes a first external pipe 13, a second external pipe 16, a third external pipe 18, a fourth external pipe 19, a fifth external pipe 7, a sixth external pipe 21, a seventh external pipe 24, an eighth external pipe 17, a ninth external pipe 14, a tenth external pipe 15, and multiple three-way valves. A second working fluid circulates within the external circulation pipeline. The outlet of the lunar surface heat collection component 10 flows sequentially into the first medium port of the phase change heat storage module 8 through the bypass of the first three-way valve 27, the first external pipe 13, the second three-way valve 26, and the first branch pipe 22. The second medium port of the phase change heat storage module 8 flows into the buried heat exchanger through the bypass (port) of the second branch pipe 23, the third three-way valve 29, and the second external pipe 16. Heat pipe 9, the medium outlet of the buried heat exchange pipe 9 is connected to the medium inlet of the inner and outer loop heat exchanger 5 in sequence through the third outer pipe 18, the fourth three-way valve 30 and the fourth outer pipe 19. The third outer pipe 18 and the fourth outer pipe 19 are located on the main road of the fourth three-way valve 30. The medium outlet of the inner and outer loop heat exchanger 5 is connected to the bypass inlet of the fifth three-way valve 25 through the fifth outer pipe 7. An outer loop circulation pump 6 is installed on the fifth outer pipe 7. One end of the sixth outer pipe 21 is connected to the first outlet of the fifth three-way valve 25. The other end of the sixth outer pipe 21 is connected to the medium inlet of the lunar surface heat collection assembly 10. A sixth three-way valve 28 is installed on the sixth outer pipe 21.

[0052] The other medium outlet of the No. 2 three-way valve 26 is connected to the bypass of the No. 4 three-way valve 30 through the eighth external pipe 17. The eighth external pipe 17 and the first external pipe 13 are located on the main line of the No. 2 three-way valve 26. The No. 2 outlet of the No. 5 three-way valve 25 is connected to the medium inlet of the No. 3 three-way valve 29 through the seventh external pipe 24. The bypass of the No. 1 three-way valve 27 is connected to the medium inlet of the buried heat exchange tube 9 through the ninth external pipe 14. The bypass of the No. 6 three-way valve 28 is connected to the buried heat exchange tube 9 through the tenth external pipe 15.

[0053] The control module 11 is electrically connected to the actuators of the inner loop circulating pump 3, the inner and outer loop heat exchangers 5, the outer loop circulating pump 6, the phase change heat storage module 8, the buried heat exchange pipe 9, and each three-way valve (25, 26, 27, 28, 29, 30).

[0054] The five operating conditions of the dual-loop thermal management building system for the manned lunar research station based on lunar soil and lava tubes in this embodiment are as follows:

[0055] (1) Heating operation of the lunar surface heat collection assembly 10, phase change heat storage module 8 and buried heat exchange pipe 9:

[0056] The lunar surface heat collection module 10 heats the second working fluid. The heated working fluid flows through the first three-way valve 27, the first outer pipe 13, the second three-way valve 26, the first branch pipe 22, the phase change heat storage module 8, the second branch pipe 23, the third three-way valve 29, the second outer pipe 16, the buried heat exchange pipe 9, the third outer pipe 18, the fourth three-way valve 30, the fourth outer pipe 19, the inner and outer loop heat exchanger 5, the fifth outer pipe 7, the outer loop circulation pump 6, the fifth three-way valve 25, the sixth outer pipe 21, and the sixth three-way valve 28, and finally flows back to the lunar surface heat collection module 10.

[0057] (2) Heat exchanger tube 9 installed for independent heating:

[0058] The heated working fluid in the buried heat exchanger tube 9 flows sequentially through the third outer tube 18, the fourth three-way valve 30, the fourth outer tube 19, the inner and outer loop heat exchangers 5, the fifth outer tube 7, the outer loop circulation pump 6, the fifth three-way valve 25, the seventh outer tube 24, the third three-way valve 29, and the second outer tube 16, and finally flows back to the buried heat exchanger tube 9; alternatively, it can flow directly back to the buried heat exchanger tube 9 through the fifth three-way valve 25 via the sixth outer tube 21, the sixth three-way valve 28, and the tenth outer tube 15.

[0059] (3) Phase change thermal storage module 8 in stand-alone heating mode:

[0060] The working fluid heated in the phase change heat storage module 8 flows sequentially through the first branch pipe 22, the second three-way valve 26, the eighth outer pipe 17, the fourth three-way valve 30, the fourth outer pipe 19, the inner and outer loop heat exchanger 5, the fifth outer pipe 7, the outer loop circulation pump 6, the fifth three-way valve 25, the seventh outer pipe 24, the third three-way valve 29, and the second branch pipe 23, and finally flows back to the phase change heat storage module 8.

[0061] (4) When the phase change heat storage module 8 is full, the heating medium in the lunar surface heat collection assembly 10 flows directly into the buried heat exchange pipe 9 for heating operation:

[0062] The working fluid heated inside the lunar surface heat collection assembly 10 flows sequentially through the No. 1 three-way valve 27, the ninth outer pipe 14, the buried heat exchange pipe 9, the third outer pipe 18, the No. 4 three-way valve 30, the fourth outer pipe 19, the inner and outer loop heat exchangers 5, the fifth outer pipe 7, the outer loop circulation pump 6, the No. 5 three-way valve 25, the sixth outer pipe 21, and the No. 6 three-way valve 28, and finally flows back to the lunar surface heat collection assembly 10.

[0063] (5) During the lunar daytime, when both the phase change thermal storage module 8 and the buried heat exchange pipe 9 are full, the lunar surface heat collection assembly 10 operates under the condition of heating alone:

[0064] The working fluid heated inside the lunar surface heat collection assembly 10 flows sequentially through the No. 1 three-way valve 27, the first outer pipe 13, the No. 2 three-way valve 26, the eighth outer pipe 17, the No. 4 three-way valve 30, the fourth outer pipe 19, the inner and outer loop heat exchanger 5, the fifth outer pipe 7, the outer loop circulation pump 6, the No. 5 three-way valve 25, the sixth outer pipe 21, and the No. 6 three-way valve 28, and finally flows back to the lunar surface heat collection assembly 10.

[0065] The working process of the dual-loop thermal management building system for the manned lunar research station based on lunar soil and lava tubes in this embodiment is divided into three main stages, the three stages (such as...) Figure 2 (As shown) are as follows:

[0066] (1) Daytime heat collection and cascaded heat storage stage: When the control module 11 detects that the solar radiation intensity on the lunar surface exceeds the preset threshold, the system enters the daytime mode. First, the control module instructs the switching valve group to switch the external loop pipeline to the heat collection-heat storage topology and connect the lunar surface heat collection components. The external loop working fluid absorbs solar radiation heat under the drive of the external loop circulation pump. During this process, the system executes the cascaded heat storage strategy: the heat is preferentially stored as latent heat through the phase change heat storage module 8, and its isothermal phase change characteristics are used to quickly suppress thermal shock; when the phase change material of the phase change heat storage module 8 is detected to be completely melted (saturated), the excess heat is further transported through the pipeline to the buried heat exchange pipe 9, and the sensible heat is stored at a deep depth using the large volume of rock.

[0067] (2) Lunar night heating and tiered heat extraction stage: During the lunar night or the period of eclipse, the switching valve group immediately cuts off the heat dissipation branch where the lunar surface heat collection component 10 is located. Preferably, the No. 6 three-way valve 28 is switched to the bypass, so that the second working fluid is connected to the buried heat exchange tube 9 through the tenth outer pipe 15, forming an internal circulation path composed of the inner and outer loop heat exchangers 5, the phase change heat storage module 8 and the buried heat exchange tube 9, which physically isolates it from the radiation heat exchange with the low temperature deep space. The system prioritizes extracting the latent heat of phase change from the phase change heat storage module 8 to maintain a precise temperature control of 20°C in the cabin; if the phase change heat storage module 8 is insufficient (temperature drops), the residual heat is extracted from the buried heat exchange tube 9 through the outer loop working fluid as a supplement, and heat is transferred to the inner loop through the inner and outer loop heat exchangers 5.

[0068] (3) Emergency and Feedback Regulation Logic: If the system detects that the total heat of the phase change heat storage module 8 and the buried heat exchange tube 9 is lower than the safety threshold, the system enters emergency mode. At this time, the switching valve group further operates to completely isolate the energy-depleted or low-efficiency circulation branch and concentrate the remaining heat to supply the working chamber. At the same time, the internal loop circulation pump 3 adjusts the working fluid flow rate in real time according to the air temperature T1 fed back by the heat exchange terminal 2 in the chamber, so as to achieve closed-loop constant temperature control in the range of 18°C ​​to 25°C.

[0069] This embodiment is applicable to using lunar regolith and natural lava tube geological structures as thermal inertial buffers. Through the synergistic effect of internal and external dual-loop liquid working fluid circulation and phase change thermal storage materials (PCM), it achieves constant temperature control of the cabin environment under extreme lunar surface temperature fluctuations. This system deeply integrates thermal management functions into the building envelope, replacing traditional external heat dissipation fins and pure resistance heating solutions. Through integrated geological and architectural design, it transforms the severe thermal boundary conditions of -170°C to 120°C on the lunar surface into a controllable system operating temperature range of -20°C to 40°C, ensuring a stable operating environment of approximately 20°C for the crew cabin and critical equipment. It is suitable for manned structures such as research stations deployed on the lunar surface or in the shallow sublunar region.

Claims

1. A cascaded heat storage and release dual-loop thermal management building system for a manned lunar research station deployed under the moon, characterized in that... The dual-loop thermal management building system of the manned lunar research station based on lunar soil and lava tubes includes a research station working module (1), an internal heat exchange terminal (2), an inner and outer loop heat exchanger (5), a phase change heat storage module (8), a buried heat exchange tube (9), and a lunar surface heat collection assembly (10). The research station working module (1) and the lunar surface heat collection assembly (10) are located on the surface of the lunar soil cover layer (12), the inner and outer loop heat exchanger (5) and the phase change heat storage module (8) are located inside the lunar soil cover layer (12), and the buried heat exchange tube (9) is set inside the lava tube wall. The heat exchange terminal (2) inside the cabin is installed in the working cabin (1) of the research station. The heat exchange terminal (2) inside the cabin forms a circulation loop with the heat exchanger (5) inside and outside the loop through the inner loop circulation pipe. The first working fluid circulates inside the inner loop circulation pipe. The external circulation pipeline includes a first external pipe (13), a second external pipe (16), a third external pipe (18), a fourth external pipe (19), a fifth external pipe (7), a sixth external pipe (21), and multiple three-way valves. The external circulation pipeline contains a second working fluid. The outlet of the lunar surface heat collection component (10) flows into the first medium port of the phase change heat storage module (8) through the bypass of the first three-way valve (27), the first external pipe (13), and the second three-way valve (26). The second medium port of the phase change heat storage module (8) flows into the buried heat exchanger through the bypass of the third three-way valve (29) and the second external pipe (16). The medium outlet of the buried heat exchange tube (9) is connected to the medium inlet of the inner and outer loop heat exchanger (5) in sequence through the third outer tube (18), the fourth three-way valve (30) and the fourth outer tube (19). The medium outlet of the inner and outer loop heat exchanger (5) is connected to the bypass inlet of the fifth three-way valve (25) through the fifth outer tube (7). One end of the sixth outer tube (21) is connected to the first outlet of the fifth three-way valve (25). The other end of the sixth outer tube (21) is connected to the medium inlet of the lunar surface heat collection assembly (10). A sixth three-way valve (28) is installed on the sixth outer tube (21). The medium outlet of the No. 2 three-way valve (26) is connected to the bypass of the No. 4 three-way valve (30) through the eighth external pipe (17), and the No. 2 outlet of the No. 5 three-way valve (25) is connected to the medium inlet of the No. 3 three-way valve (29) through the seventh external pipe (24).

2. The cascaded heat storage and release dual-loop thermal management building system for a manned lunar research station deployed under the moon as described in claim 1, characterized in that... The inner loop circulation pipeline is formed by the first inner pipe (20) and the second inner pipe (4). One end of the first inner pipe (20) is connected to the first working fluid outlet of the inner and outer loop heat exchanger (5), and the other end of the first inner pipe (20) is connected to the working fluid inlet of the heat exchange terminal (2) in the cabin. One end of the second inner pipe (4) is connected to the first working fluid inlet of the inner and outer loop heat exchanger (5), and the other end of the second inner pipe (4) is connected to the working fluid outlet of the heat exchange terminal (2) in the cabin.

3. The cascaded heat storage and release dual-loop thermal management building system for a manned lunar research station deployed under the moon as described in claim 1, characterized in that... The first working fluid is silicone oil, fluorine-containing inert heat transfer fluid, or ethylene glycol solution.

4. The cascaded heat storage and release dual-loop thermal management building system for a manned lunar research station deployed under the moon as described in claim 3, characterized in that... The fluorinated inert heat transfer fluid is a perfluoropolyether heat transfer fluid, a hydrofluoroether heat transfer fluid, or a fluoroketone heat transfer fluid.

5. The cascaded heat storage and release dual-loop thermal management building system for a manned lunar research station deployed under the moon as described in claim 1, characterized in that... The second working fluid is liquid ammonia, heat transfer oil, or liquid CO2.

6. The cascaded heat storage and release dual-loop thermal management building system for a manned lunar research station deployed under the moon as described in claim 1, characterized in that... The phase change material in the phase change heat storage module (8) is an organic phase change material, an inorganic salt hydrate, or a lunar soil composite phase change material.

7. The cascaded heat storage and release dual-loop thermal management building system for a manned lunar research station deployed under the moon as described in claim 1, characterized in that... The lunar surface heat collection component (10) is a solar heat collection panel.

8. The cascaded heat storage and release dual-loop thermal management building system for a manned lunar research station deployed under the moon as described in claim 1, characterized in that... An external circulation pump (6) is installed on the fifth outer pipe (7).

9. The cascaded heat storage and release dual-loop thermal management building system for a manned lunar research station deployed under the moon as described in claim 1, characterized in that... The bypass of the No. 1 three-way valve (27) is connected to the medium inlet of the buried heat exchange tube (9) through the ninth outer pipe (14).

10. The cascaded heat storage and release dual-loop thermal management building system for a manned lunar research station deployed under the moon as described in claim 1, characterized in that... The bypass of the No. 6 three-way valve (28) is connected to the buried heat exchange tube (9) through the tenth outer pipe (15).

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