Gas compression and cooling system for extraterrestrial environment

Abstract

The invention relates to the technical field of aerospace engineering, and discloses a gas compression and cooling system for an extraterrestrial environment, the gas compression and cooling system comprises a multi-stage compression mechanism and a cooling mechanism, the multi-stage compression mechanism comprises at least two gas compressors, the gas outlet end of one gas compressor is communicated with the gas inlet end of the other gas compressor through a gas channel, and the gas outlet end of the other gas compressor is communicated with the cooling mechanism through a gas channel. The multi-stage compression and radiation cooling integrated design is adopted, one-stage radiator is adopted in each stage of cooling, the efficient heat dissipation performance is guaranteed while the equipment size is reduced, the first-stage radiator is coupled with the evaporation section of the loop heat pipe, the heat dissipation efficiency is improved, and the heat dissipation efficiency is improved. According to the mode, the loop heat pipe and the two-stage radiator are introduced, heat can be treated in a grading or layering mode, the cooling capacity is remarkably improved, and due to the two-stage heat dissipation structure, radiators with different orientations or different sizes can be selected according to factors such as the structure space, the posture and sunlight, so that the overall heat dissipation efficiency is improved.

Description

Technical Field

[0001] This invention relates to the field of aerospace engineering technology, specifically to a gas compression and cooling system for extraterrestrial environments. Background Technology

[0002] With the development of deep space exploration technology, gas supply systems in extraterrestrial environments have become one of the key technologies. Taking oxygen as an example, traditional oxygen production methods (such as cryogenic air separation, adsorption separation, and water electrolysis) require a cooling-compression-cooling process to store the gas in terrestrial environments. However, extraterrestrial environments (such as the lunar surface) lack atmospheric convection for heat dissipation, and the high-temperature (approximately 1000℃) and low-pressure (approximately 1kPa) gases produced by in-situ oxygen production (such as lunar soil reduction) need to be compressed and cooled to meet usage standards (such as 1000kPa and 25℃).

[0003] The existing technology has the following shortcomings: Low cooling efficiency: Traditional cryogenic cycle processes are energy-intensive and complex, making them unsuitable for space cooling.

[0004] Poor environmental adaptability: The high radiation heat dissipation efficiency of space is not fully utilized, resulting in a large system size and high power consumption.

[0005] Compressor performance limitations: In a vacuum environment, the temperature fluctuations at the compressor's inlet and outlet are prone to exceed the operating limits, affecting reliability.

[0006] At the same time, radiative heat dissipation technology in extraterrestrial environments faces the following challenges. Dramatic changes in radiation conditions: For extraterrestrial environments such as spacecraft and planetary surfaces, radiation conditions often change drastically in a short period of time, causing rapid changes in the surface temperature and heat dissipation of radiators. For example, when the sun is directly overhead, radiation conditions are harsh, and the surface temperature of the radiator rises sharply. Due to the presence of surface radiative heat flow, the radiator is unable to dissipate heat effectively. However, when the radiator does not receive solar radiation, it directly exchanges heat with the cosmic background (approximately -273.15°C), causing the surface temperature of the radiator to drop sharply, and the radiative heat dissipation effect is better in this case.

[0007] System layout constraints: Due to factors such as the location, system layout, and orientation of spacecraft or heat dissipation systems, radiators are often subject to layout constraints, which limits the radiation area and the amount of heat dissipation when directly using radiators for heat dissipation.

[0008] Therefore, a gas compression and cooling system for extraterrestrial environments is proposed. Summary of the Invention

[0009] The purpose of this invention is to provide a gas compression and cooling system for extraterrestrial environments, thereby solving or at least alleviating one or more of the aforementioned and other problems existing in the prior art.

[0010] To achieve the above objectives, the present invention provides the following technical solution: a gas compression and cooling system for extraterrestrial environments, comprising: A multi-stage compression mechanism, comprising at least two gas compressors, wherein the outlet of one gas compressor is connected to the inlet of the other gas compressor via a gas passage; A cooling mechanism is provided for cooling the high-temperature gas in the gas channel.

[0011] In a gas compression and cooling system for an extraterrestrial environment according to the present invention, the cooling mechanism optionally includes a primary radiator, the gas channel is opened inside the primary radiator, two adjacent gas channels are relatively independent, and the primary radiator is respectively provided with an inlet and an outlet connected to the gas channel.

[0012] In a gas compression and cooling system for an extraterrestrial environment according to the present invention, optionally, a honeycomb layer with high thermal conductivity is fixedly connected inside the primary radiator, the gas channel is wrapped inside the honeycomb layer, and an upper radiating surface for dissipating heat to the outside is provided on the top of the honeycomb layer.

[0013] In a gas compression and cooling system for an extraterrestrial environment according to the present invention, the cooling mechanism optionally further includes a secondary radiator and a loop heat pipe, wherein the evaporation section of the loop heat pipe is coupled to the primary radiator and the condensation section of the loop heat pipe is coupled to the secondary radiator.

[0014] In a gas compression and cooling system for an extraterrestrial environment according to the present invention, optionally, the evaporation section is fixedly attached to the surface of the primary radiator.

[0015] In a gas compression and cooling system for an extraterrestrial environment according to the present invention, optionally, the honeycomb layer and the skin of the upper radiating surface are both made of aluminum, the gas channel is made of stainless steel, and the loop heat pipe is made of copper.

[0016] In a gas compression and cooling system for an extraterrestrial environment according to the present invention, optionally, the working fluid in the loop heat pipe includes, but is not limited to, distilled water or deionized water, and the capillary structure in the loop heat pipe is made of, but is not limited to, sintered copper powder or fine copper mesh.

[0017] In a gas compression and cooling system for an extraterrestrial environment according to the present invention, optionally, the pressure ratio of each stage of the multi-stage compression mechanism is distributed as 4.0-6.0.

[0018] In a gas compression and cooling system for an extraterrestrial environment according to the present invention, optionally, the flow path arrangement of the gas channel in the primary radiator and the loop heat pipe includes, but is not limited to, one of counter-flow, vertical flow and mixed flow.

[0019] In a gas compression and cooling system for an extraterrestrial environment according to the present invention, optionally, the surfaces of the primary radiator and the secondary radiator are coated with a selective radiation coating, with an emissivity ≥0.90 in the 8-14μm band and an emissivity ≤0.20 in other bands.

[0020] Compared with the prior art, the beneficial effects of the present invention are: It adopts a multi-stage compression and radiation cooling integrated design, and each stage of cooling uses a single radiator, which reduces the size of the equipment while ensuring high-efficiency heat dissipation performance; The primary radiator is coupled to the evaporation section of the loop heat pipe. This method, by introducing the loop heat pipe and the secondary radiator, can process heat in stages or layers, significantly improving the cooling capacity. Due to the two-stage heat dissipation structure, radiators of different orientations or sizes can be selected according to factors such as structural space, orientation, and sunlight to improve the overall heat dissipation efficiency.

[0021] By directly concentrating the heat of high-temperature gas onto a relatively compact primary radiator, and then transferring the heat to a secondary radiator via a loop heat pipe for final heat release, this arrangement is more conducive to airborne radiation. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the structure of a gas compression and cooling system for extraterrestrial environments according to the present invention; Figure 2 This is a partial cross-sectional schematic diagram of the primary radiator of a gas compression and cooling system for extraterrestrial environments according to the present invention. Figure 3 This is a front view partial cross-sectional structural diagram of a primary radiator of a gas compression and cooling system for an extraterrestrial environment according to the present invention. Figure 4 This is a partial side view cross-sectional structural diagram of a primary radiator of a gas compression and cooling system for an extraterrestrial environment according to the present invention. Figure 5 This is a schematic diagram of a gas compression and cooling system for extraterrestrial environments according to the present invention, in which the working fluid flow direction and the gas flow direction are in the same direction. Figure 6This is a schematic diagram of a gas compression and cooling system for extraterrestrial environments according to the present invention, in which the working fluid flow direction and the gas flow direction are countercurrent. Figure 7 This is a schematic diagram of a gas compression and cooling system for extraterrestrial environments according to the present invention, in which the working fluid flow direction is perpendicular to the gas flow direction. Figure 8 This is a schematic diagram of the mixed flow structure of the working fluid and gas in a gas compression and cooling system for extraterrestrial environments according to the present invention.

[0023] In the diagram: 1. Gas compressor; 2. Gas passage; 201. Inlet; 202. Outlet; 3. Primary radiator; 301. Honeycomb layer; 302. Upper radiating surface; 4. Secondary radiator; 5. Loop heat pipe; 501. Evaporation section; 502. Condensation section. Detailed Implementation

[0024] The technical solution of the present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0025] The accompanying drawings are for illustrative purposes only and are schematic diagrams, not actual images. They should not be construed as limiting the scope of this patent. To better illustrate the embodiments of the present invention, some parts in the drawings may be omitted, enlarged, or reduced, and do not represent the actual dimensions of the product. It is understandable to those skilled in the art that some well-known structures and their descriptions may be omitted in the drawings.

[0026] In the accompanying drawings of the embodiments of the present invention, the same or similar reference numerals correspond to the same or similar components. In the description of the present invention, it should be understood that if terms such as "upper," "lower," "left," "right," "inner," and "outer" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, they are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, the terms used to describe positional relationships in the drawings are only for illustrative purposes and should not be construed as limiting the present patent. For those skilled in the art, the specific meaning of the above terms can be understood according to the specific circumstances.

[0027] In the description of this invention, unless otherwise explicitly specified and limited, the term "connection" or similar designation indicating a connection between components should be interpreted broadly. For example, it can refer to a fixed connection, a detachable connection, or an integral part; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can refer to the internal communication between two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0028] Example 1 Please see Figures 1 to 8 This embodiment provides a gas compression and cooling system for extraterrestrial environments, including: a multi-stage compression mechanism and a cooling mechanism, wherein: The multi-stage compression mechanism includes at least two gas compressors 1, the outlet of one gas compressor 1 being connected to the inlet of the other gas compressor 1 via a gas passage 2; The cooling mechanism is used to cool the high-temperature gas in gas channel 2.

[0029] The multi-stage compression mechanism consists of at least two gas compressors 1 connected sequentially to form a multi-stage compression chain. Gas is compressed in the first gas compressor 1, increasing its pressure and temperature. The high-temperature compressed gas then enters the next stage gas compressor 1 through gas channel 2 for further compression. Compared to single-stage compression, this multi-stage compression method can more efficiently compress gas to the required pressure within the operating pressure range of each compressor stage, while reducing power consumption and mechanical stress on the equipment during the compression process. The cooling mechanism is responsible for cooling the high-temperature gas in gas channel 2 to prevent excessively high gas temperatures from damaging subsequent equipment and also helps improve compression efficiency.

[0030] In this embodiment, the cooling mechanism includes a primary radiator 3, and a gas channel 2 is opened inside the primary radiator 3. Two adjacent gas channels 2 are relatively independent. The primary radiator 3 is provided with an air inlet 201 and an air outlet 202 that are connected to the gas channel 2.

[0031] The first-stage radiator 3, as a key component of the cooling mechanism, has an internal gas channel 2 used to guide the flow of high-temperature gas. Adjacent gas channels 2 are relatively independent, avoiding mutual interference between gases from different compression stages. High-temperature gas enters the gas channel 2 through the inlet 201. During its flow within the channel, heat is transferred to the first-stage radiator 3 through the wall of the gas channel 2. The first-stage radiator 3 dissipates the heat of the gas by radiating it to the outside, thereby cooling the high-temperature gas. The cooled gas flows out through the outlet 202 and enters the next stage of compression or subsequent processing.

[0032] In this embodiment, a honeycomb layer 301 with high thermal conductivity is fixedly connected inside the primary radiator 3, the gas channel 2 is wrapped inside the honeycomb layer 301, and the top of the honeycomb layer 301 is provided with an upper radiating surface 302 for heat dissipation to the outside.

[0033] The high thermal conductivity honeycomb layer 301 can quickly and evenly transfer the heat from the gas channel 2 throughout the entire honeycomb layer 301. The special structure of the honeycomb layer 301 increases the heat dissipation area and improves heat dissipation efficiency. The gas channel 2 is enclosed inside the honeycomb layer 301, ensuring good heat conduction. Heat is transferred from the honeycomb layer 301 to the top upper radiating surface 302, which dissipates the heat into the surrounding environment in the form of radiation, further enhancing the heat dissipation capacity of the first-stage radiator 3 and more effectively cooling the high-temperature gas inside the gas channel 2.

[0034] Furthermore, the cooling mechanism also includes a secondary radiator 4 and a loop heat pipe 5. The evaporation section 501 of the loop heat pipe 5 is coupled to the primary radiator 3, and the condensation section 502 of the loop heat pipe 5 is coupled to the secondary radiator 4.

[0035] The evaporation section 501 of the loop heat pipe 5 is coupled to the primary radiator 3. When the primary radiator 3 absorbs heat from the high-temperature gas in the gas channel 2 and its temperature rises, the working fluid in the loop heat pipe 5 absorbs heat in the evaporation section 501 and evaporates into steam. Under the action of the pressure difference, the steam flows along the pipe of the loop heat pipe 5 to the condensation section 502. In the condensation section 502, the steam transfers heat to the secondary radiator 4 and condenses into liquid. The secondary radiator 4 radiates the heat absorbed from the loop heat pipe 5 into the external environment.

[0036] The condensed liquid, under the action of capillary force, flows back to the evaporation section 501 through the capillary structure inside the loop heat pipe 5, completing the cycle. In this way, heat is transferred from the primary radiator 3 to the secondary radiator 4 through the loop heat pipe 5, realizing two-stage radiative heat dissipation and enhancing the cooling effect.

[0037] The loop heat pipe 5 can realize long-distance heat transport. For the poor radiation conditions of the primary radiator 3 and the situation that it is not suitable to place it far away from the heat dissipation system, the addition of the loop heat pipe 5 and the secondary radiator 4 can effectively overcome the above difficulties, realize efficient heat dissipation and cooling of the gas, and also help the flexible arrangement of the gas heat dissipation system and the stability of the heat dissipation effect. For example, the secondary radiator (4) is installed in a part that does not receive solar radiation, and directly exchanges heat with the cosmic background to improve the heat dissipation effect.

[0038] Furthermore, the evaporation section 501 is fixedly attached to the surface of the primary radiator 3.

[0039] In some embodiments, multiple loop heat pipes 5 may be provided to improve heat dissipation efficiency.

[0040] By fixing the evaporation section 501 to the surface of the primary radiator 3, good thermal contact between the two can be ensured. In this way, the heat absorbed by the primary radiator 3 can be quickly and efficiently transferred to the working fluid in the evaporation section 501, causing the working fluid to evaporate rapidly, improving heat transfer efficiency, ensuring that the loop heat pipe 5 can effectively remove the heat from the primary radiator 3 in a timely manner, and enhancing the heat dissipation capacity of the primary radiator 3 and the cooling performance of the entire cooling system.

[0041] Furthermore, the skin of the honeycomb layer 301 and the upper radiating surface 302 are both made of aluminum, the gas channel 2 is made of stainless steel, and the loop heat pipe 5 is made of copper.

[0042] Aluminum, with its low density and good thermal conductivity, is used for the skin of the honeycomb layer 301 and the upper radiating surface 302, reducing system weight while ensuring good heat dissipation. Stainless steel, with its excellent corrosion resistance and mechanical strength, is suitable for gas channel 2, ensuring that it will not be damaged by corrosion or pressure during the transport of high-temperature gases. Copper, with its extremely high thermal conductivity, is used in the loop heat pipe 5 to efficiently transfer heat, improving its operating efficiency and thus enhancing the performance of the entire cooling system.

[0043] The materials mentioned above are all conventional terrestrial materials, easy to obtain and transport, and commonly found in lunar and other planetary soil resources. With the future maturation of deep space exploration and in-situ resource utilization technologies, this system will be even easier to promote and use.

[0044] Furthermore, the working fluid in the loop heat pipe 5 is distilled water. Distilled water has the characteristics of high purity and no impurity ions, which can effectively avoid problems such as pipe blockage caused by impurity deposition during the operation of the loop heat pipe, and ensure the smooth circulation of the working fluid in the heat pipe and the stability of heat exchange efficiency.

[0045] In some embodiments, the working fluid in the loop heat pipe 5 is deionized water. Deionized water has extremely low electrical conductivity, which can prevent electrochemical corrosion caused by ionic conductivity and extend the service life of the loop heat pipe. At the same time, its good thermal stability also helps to maintain the performance of the heat pipe system.

[0046] In some embodiments, the working fluid in the loop heat pipe 5 may also be methanol. Methanol has a low boiling point and a high latent heat of vaporization, and can achieve phase change heat transfer at a low temperature. It can be applied to loop heat pipe systems with low requirements for start-up temperature.

[0047] In some embodiments, the working fluid in the loop heat pipe 5 may also be ethanol. Ethanol has good chemical stability and compatibility with a variety of materials, which can adapt to loop heat pipe structures of different materials, and its moderate thermophysical properties can also meet the heat transfer requirements under various operating conditions.

[0048] In some embodiments, the working fluid in the loop heat pipe 5 may also be acetone. Acetone has high volatility and low viscosity, which makes the flow resistance of the working fluid in the loop heat pipe small, enabling rapid heat transfer and exchange, and improving the response speed of the heat pipe.

[0049] Furthermore, the capillary structure inside the loop heat pipe 5 is made of sintered copper powder. The capillary structure made of sintered copper powder has a rich pore structure and a large capillary suction force, which can effectively transport the liquid working fluid from the condensation section to the evaporation section, ensuring the circulation of the working fluid inside the loop heat pipe. Its high mechanical strength also enhances the stability of the structure.

[0050] In some embodiments, the capillary structure inside the loop heat pipe 5 is made of fine copper mesh. Fine copper mesh has good flexibility and uniform pore distribution, which can better fit the inner wall of the loop heat pipe and provide stable capillary force. At the same time, its manufacturing process is relatively simple and the cost is low.

[0051] In some embodiments, the capillary structure within the loop heat pipe 5 is a carbon nanotube array. The carbon nanotube array has an extremely high specific surface area and excellent capillary performance, which can significantly improve the transport speed and heat transfer efficiency of the working fluid. Furthermore, its good chemical stability makes it suitable for various working fluid environments.

[0052] In some embodiments, the capillary structure within the loop heat pipe 5 is made of metal foam. The metal foam has a three-dimensional interconnected pore structure and high porosity, which can provide greater capillary driving force and good liquid storage capacity, thus helping to improve the performance and reliability of the loop heat pipe.

[0053] In some embodiments, the capillary structure inside the loop heat pipe 5 is made of ceramic fiber. Ceramic fiber has the characteristics of high temperature resistance and corrosion resistance, and is suitable for loop heat pipes in high temperature environments. Furthermore, the pores between its fibers can form effective capillary channels to realize the transport of the working fluid.

[0054] Different circulating working fluids and capillary structures in a loop heat pipe each have their own advantages. The appropriate selection and design should be based on the actual operating temperature requirements and equipment characteristics to achieve better heat dissipation and cooling effects. Heat pipe structure selection and design are standard knowledge in the field and will not be elaborated upon here.

[0055] Gas compression and cooling parameters need to be determined based on the gas usage scenario. Taking the oxygen requirements for breathing in the Shenzhou spacecraft cabin as an example, the principles for setting compression and cooling parameters are introduced. Specifically, the Shenzhou spacecraft cabin uses a dual-component gas of oxygen and nitrogen, with the total pressure controlled at 91±10 kPa and the oxygen partial pressure at 20~26 kPa.

[0056] To ensure the compressor operates normally in a vacuum environment, the compressor's suction and discharge temperatures should not be too low or too high. Since the pre-cooled oxygen pressure at the system inlet is generally low, the design parameters are set at an inlet pressure of 1 kPa, an inlet temperature of 25°C, a storage pressure of 1000 kPa, and a storage temperature of 25°C. Calculations are performed using 25°C and 150°C as the safe inlet and outlet temperatures for each stage of the compressor. The calculated pressure ratio for each stage in this example is approximately 5.7.

[0057] Due to the varying temperatures and pressures of different gases after precooling at the system's input side and the different storage temperature and pressure requirements at the system's output side, the compression and cooling parameters differ between different systems and embodiments. The compression and cooling parameters for each system should be determined based on the compressor's inlet and outlet safe temperatures and actual design parameters. It is recommended that the compressor outlet temperature not exceed 150°C, and the pressure ratio of each compressor should be maintained within the range of 4.0-6.0 as much as possible, dynamically adjusted based on the compression process.

[0058] The compression and cooling parameter allocation determined based on this principle enables each stage of the gas compressor 1 and the first-stage radiator 3 to operate within a relatively reasonable pressure and temperature range. This ensures that each compression stage can effectively increase the gas pressure while avoiding excessively high temperatures, power consumption, and equipment stress caused by excessively large single-stage pressure ratios. A reasonable pressure ratio allocation helps improve the compression efficiency and stability of the entire multi-stage compression mechanism, and also facilitates the cooling mechanism's cooling of the high-temperature gas after compression.

[0059] In this embodiment, the gas channel 2 and the loop heat pipe 5 in the primary radiator 3 are arranged in a counter-current manner.

[0060] The gas channel 2 of the primary radiator 3 is arranged in a specific direction, while the flow path of the loop heat pipe 5 runs parallel to it in the opposite direction. This counter-current arrangement enables highly efficient heat exchange. When the hot gas flows in the gas channel 2, the low-temperature working fluid in the loop heat pipe 5 flows in the opposite direction to the hot gas, and a large temperature difference exists between them. According to the principle of heat exchange, heat is transferred from the hot gas to the low-temperature working fluid. This arrangement makes the entire heat exchange process more complete and improves heat exchange efficiency.

[0061] In some embodiments, the gas channel 2 and the loop heat pipe 5 within the primary radiator 3 are arranged in a vertical flow configuration.

[0062] Gas channel 2 is arranged in a plane, while the flow path of loop heat pipe 5 passes perpendicularly through this plane. When hot gas flows in the horizontal gas channel 2, the vertically passing loop heat pipe 5 exchanges heat with the hot gas. Due to the vertically intersecting structure, the contact area between the hot gas and the loop heat pipe is relatively large, which can improve the efficiency of heat exchange to a certain extent. Moreover, this arrangement allows heat exchange to occur in different spatial dimensions, reducing space occupation.

[0063] In some embodiments, the gas channel 2 and the loop heat pipe 5 within the primary radiator 3 are arranged in a mixed flow configuration.

[0064] The mixed flow arrangement combines the characteristics of counter-current and vertical flow. Part of the gas channel 2 and the loop heat pipe 5 are arranged in a counter-current manner, while the other part is arranged in a vertical flow manner.

[0065] In the counter-current section, a larger temperature difference is used to achieve rapid heat transfer; in the vertical flow section, the heat exchange efficiency is further improved by increasing the contact area. This hybrid arrangement fully leverages the advantages of both counter-current and vertical flow, enabling optimized heat exchange performance under various operating conditions.

[0066] In some embodiments, the gas channel 2 within the primary radiator 3 and the flow path of the loop heat pipe 5 are arranged in a co-current manner.

[0067] The gas channel 2 flows in the same direction as the loop heat pipe 5. This arrangement allows the gas and working fluid to maintain a relatively stable contact state throughout the flow process.

[0068] During the flow of hot gas, it exchanges heat with the working fluid in the loop heat pipe 5, which flows in the same direction. Although the initial temperature difference is smaller in the co-current arrangement than in the counter-current arrangement, the working fluid can gradually absorb the heat transferred by the gas because the two flow in the same direction, thus achieving a relatively stable heat exchange process.

[0069] In some embodiments, the gas channel 2 within the primary radiator 3 and the flow path of the loop heat pipe 5 are arranged in a cross-flow configuration. The flow paths of gas channel 2 and loop heat pipe 5 are interwoven, forming a grid-like interwoven structure. This arrangement increases the contact opportunities and contact area between the gas and the working fluid.

[0070] As the hot gas flows through the interlaced channels, it continuously encounters the loop heat pipe 5 and exchanges heat. Due to the interlaced structure, the flow paths of the gas and working fluid are more complex, resulting in more complete heat exchange and improved heat exchange efficiency.

[0071] Advantages: Suitable for scenarios with high requirements for heat exchange efficiency and relatively ample space, such as heat exchangers in large air conditioning systems. Cross-flow arrangement can improve heat exchange performance and reduce energy consumption without significantly increasing equipment size.

[0072] Different flow path arrangements each have their advantages. The heat exchange process can be adjusted according to actual working requirements and equipment characteristics to achieve better heat dissipation and cooling effects.

[0073] In this embodiment, the surfaces of the primary radiator 3 and the secondary radiator 4 are both coated with a selective radiation coating, with an emissivity ≥0.90 in the 8-14μm band and an emissivity ≤0.20 in other bands.

[0074] In the 8-14 μm band, the background radiation from the external environment is relatively weak. The selective radiation coatings sprayed on the surfaces of primary radiators 3 and secondary radiators 4 have a high emissivity of ≥0.90 in this band, effectively emitting the heat absorbed by the radiators as thermal radiation. In other bands, the coating emissivity is ≤0.20, reducing the absorption and emission of radiation in other bands, minimizing interference from external environmental radiation on the radiator's heat dissipation, and improving the radiator's heat dissipation efficiency in specific bands, thus more effectively cooling the gas. Selective radiation coatings include, but are not limited to, aluminum-based coatings.

[0075] In this embodiment, a two-stage heat dissipation mode can be selected based on different heat loads. When the heat load is low, the gas heat dissipation requirement can be met by the primary radiator 3 alone; when the heat load is high, efficient heat dissipation is achieved by combining the primary radiator 3 and the secondary radiator 4.

[0076] Furthermore, the structure of the first-stage radiator varies depending on the differences between the oxygen flow path and the heat pipe flow path. The shapes of the oxygen and loop heat pipe flow channels include, but are not limited to, circular and square shapes. Based on different flow directions of the oxygen and heat pipe working fluid, the structural arrangement of the first-stage radiator can be categorized into counter-current, vertical flow, co-current, and mixed flow forms. Different implementations of the loop heat pipe evaporation section and oxygen flow path are as follows: Figure 7-8 As shown. The flow path arrangement of the heat exchanger is basic general knowledge and will not be elaborated here. Different flow paths of oxygen and loop heat pipes can be arranged and combined according to requirements, resulting in various primary radiator 3 and secondary radiator 4 structures, which will not be shown one by one here.

[0077] It is worth noting that this system is particularly suitable for oxygen supply cooling and has the following advantages in oxygen supply cooling: 1. High-efficiency multi-stage compression and heat dissipation design ensures oxygen compression efficiency and safety. 1.1 Multi-stage compression link optimization: By connecting at least two compressors in series, the pressure ratio of each stage is controlled within a reasonable range of 4.0-6.0 (such as the pressure ratio of about 5.7 in the Shenzhou spacecraft case), avoiding high temperature, high power consumption and equipment stress caused by excessive pressure ratio of a single stage, ensuring that each compressor operates within a safe temperature range (inlet and outlet temperature 25-150℃), and improving compression efficiency.

[0078] 1.2 Enhanced Two-Stage Radiative Heat Dissipation: The first-stage radiator incorporates a high-thermal-conductivity honeycomb layer (aluminum skin) to increase the heat dissipation area. Combined with the coupling design of the loop heat pipe (made of copper) and the second-stage radiator, efficient heat transfer from the high-temperature gas to the external environment is achieved. Under low heat loads, only the first-stage radiator is used; under high loads, both stages work together to adapt to different operating conditions, ensuring effective cooling of the compressed high-temperature oxygen (e.g., outlet ≤150℃) and preventing damage to downstream equipment.

[0079] 2. Selection of materials and working fluids adapted to the external environment to ensure system reliability. 2.1 Lightweight and corrosion-resistant materials: The honeycomb layer and radiator skin are made of aluminum (low density and good thermal conductivity), the gas channel is made of stainless steel (high pressure resistance and corrosion resistance), and the loop heat pipe is made of copper (high thermal conductivity). All of these are conventional materials used on Earth and are easy to obtain from the soil resources of planets such as the Moon, making them suitable for in-situ resource utilization in deep space exploration.

[0080] 2.2 Working fluid and capillary structure compatibility: The working fluid of the loop heat pipe can be selected from distilled water (high purity to prevent clogging), deionized water (to prevent electrochemical corrosion), methanol / ethanol (low boiling point, good compatibility), etc., to adapt to different temperature conditions; the capillary structure adopts sintered copper powder, fine copper mesh, carbon nanotube array, etc., to provide stable capillary driving force, ensure smooth circulation of working fluid, and extend system life.

[0081] 3. Flexible flow path layout and thermal management improve heat exchange efficiency. 3.1 Diverse flow path design: Gas channels and loop heat pipes can be arranged in various ways, such as counter-flow (maximum temperature difference for efficient heat exchange), vertical flow (increase contact area), and mixed flow (combining the advantages of both), and can be dynamically adjusted according to space constraints and heat dissipation requirements to optimize heat exchange efficiency.

[0082] 3.2 Selective radiation coating: The surface of the radiator is sprayed with a high emissivity (≥0.90) coating in the 8-14μm band to specifically enhance thermal radiation to the outside world (such as the cosmic background) while reducing interference from other bands, and efficiently dissipating heat in vacuum and extreme temperature difference extraterrestrial environments.

[0083] 4. Modular design and parameter adaptability to meet the needs of manned environments. 4.1 Dynamic parameter adjustment: Based on the compressor's safe temperature and actual needs (such as the total oxygen pressure of the Shenzhou spacecraft cabin at 91±10kPa and the oxygen partial pressure at 20-26kPa), the compression ratio and cooling parameters of each stage are dynamically allocated to ensure that the output oxygen pressure (such as 1000kPa) and temperature (25℃) meet the standards and adapt to harsh scenarios such as manned spaceflight.

[0084] 4.2 Lightweight and Spatial Flexibility: The loop heat pipe enables long-distance heat transport, allowing the secondary radiator to be installed in shadow areas without solar radiation (such as the permanently shadowed polar regions of the moon), solving the problem of uneven radiation conditions in extraterrestrial environments and facilitating a compact system layout.

[0085] In summary, through the coordinated design of multi-stage compression and two-stage heat dissipation, the use of materials and working fluids adapted to extraterrestrial environments, flexible flow paths, and intelligent thermal management, this system achieves efficient compression, reliable cooling, low power consumption, and strong environmental adaptability in oxygen supply. It is particularly suitable for scenarios with extremely high requirements for gas supply safety, lightweight design, and long-term stability, such as deep space exploration and manned spaceflight.

[0086] Working principle: In a gas compression and cooling system for extraterrestrial environments, gas pre-cooled to meet the compressor's intake temperature requirements enters a multi-stage compression mechanism consisting of at least two gas compressors 1. The gas is sequentially compressed within the multi-stage gas compressors 1, with the pressure and temperature gradually increasing. The compressed, high-temperature gas then enters the first-stage radiator 3 through gas channel 2. Gas channel 2 inside the first-stage radiator 3 guides the high-temperature gas inwards, transferring heat to the upper radiating surface 302 via a highly thermally conductive honeycomb layer 301 for initial heat dissipation through radiation. Simultaneously, the evaporation section 501 of the loop heat pipe 5 coupled to the first-stage radiator 3 absorbs heat from the first-stage radiator 3, causing the internal working fluid to evaporate. The vapor flows to the condensation section 502, transferring heat to the second-stage radiator 4, achieving second-stage radiative heat dissipation. After two stages of cooling, the gas efficiently achieves compression and cooling in extraterrestrial environments, meeting various application needs such as oxygen supply for breathing and liquid oxygen fuel production.

[0087] All parts not described in this invention are the same as or can be implemented using existing technology. Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A gas compression and cooling system for extraterrestrial environments, characterized in that, include: A multi-stage compression mechanism, the multi-stage compression mechanism including at least two gas compressors (1), wherein the outlet end of one of the gas compressors (1) is connected to the inlet end of the other gas compressor (1) through a gas passage (2); A cooling mechanism is used to cool the high-temperature gas in the gas channel (2).

2. A gas compression and cooling system for extraterrestrial environments according to claim 1, characterized in that: The cooling mechanism includes a primary radiator (3), and the gas channel (2) is opened inside the primary radiator (3). Two adjacent gas channels (2) are relatively independent. The primary radiator (3) is provided with an air inlet (201) and an air outlet (202) that are connected to the gas channel (2).

3. A gas compression and cooling system for extraterrestrial environments according to claim 2, characterized in that: The first-stage radiator (3) is internally fixedly connected to a honeycomb layer (301) with high thermal conductivity. The gas channel (2) is wrapped inside the honeycomb layer (301). The top of the honeycomb layer (301) is provided with an upper radiating surface (302) for dissipating heat to the outside.

4. A gas compression and cooling system for extraterrestrial environments according to claim 3, characterized in that: The cooling mechanism also includes a secondary radiator (4) and a loop heat pipe (5), wherein the evaporation section (501) of the loop heat pipe (5) is coupled to the primary radiator (3), and the condensation section (502) of the loop heat pipe (5) is coupled to the secondary radiator (4).

5. A gas compression and cooling system for extraterrestrial environments according to claim 5, characterized in that: The evaporation section (501) is fixedly attached to the surface of the primary radiator (3).

6. A gas compression and cooling system for extraterrestrial environments according to claim 5, characterized in that: The skin of the honeycomb layer (301) and the upper radiating surface (302) are both made of aluminum, the gas channel (2) is made of stainless steel, and the loop heat pipe (5) is made of copper.

7. A gas compression and cooling system for extraterrestrial environments according to claim 6, characterized in that: The working fluid in the loop heat pipe (5) includes, but is not limited to, distilled water or deionized water, and the capillary structure in the loop heat pipe (5) is made of, but is not limited to, sintered copper powder or fine copper mesh.

8. A gas compression and cooling system for extraterrestrial environments according to claim 7, characterized in that: The pressure ratio of each stage of the multi-stage compression mechanism is 4.0-6.

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9. A gas compression and cooling system for extraterrestrial environments according to claim 8, characterized in that: The flow path arrangement of the gas channel (2) in the primary radiator (3) and the loop heat pipe (5) includes, but is not limited to, one of counter-flow, vertical flow and mixed flow.

10. A gas compression and cooling system for extraterrestrial environments according to claim 6, characterized in that: The surfaces of the primary radiator (3) and the secondary radiator (4) are coated with a selective radiation coating, with an emissivity ≥0.90 in the 8-14μm band and an emissivity ≤0.20 in the other bands.

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