Parallel coaxial dielectric barrier discharge Mars atmosphere conversion device and method

Abstract

The invention discloses a parallel coaxial dielectric barrier discharge Mars atmosphere conversion device which comprises a high-frequency alternating-current power supply and a Mars atmosphere conversion module. The Mars atmosphere conversion module comprises a circulating water ground electrode and a plurality of coaxial dielectric barrier discharge reactors, and the two ends of each coaxial dielectric barrier discharge reactor penetrate out of the circulating water ground electrode; the high-voltage electrode comprises a metal plate and a metal rod, and the metal rod is arranged in the coaxial dielectric barrier discharge reactor in a penetrating manner; according to the parallel coaxial dielectric barrier discharge Mars atmosphere conversion device, a plurality of conventional single-tube packed bed coaxial dielectric barrier discharge reactors are connected in parallel to work, and are used for efficient in-situ resource utilization of Mars atmosphere through system integration and technological process optimization; the stable and efficient carbon dioxide conversion process can be directly achieved under the Mars surface environment condition, and the use requirements for oxygen, methane and other key energy life conservation material resources in future deep space exploration are met.

Description

Technical Field

[0001] This invention relates to the field of carbon dioxide conversion technology, specifically to a parallel coaxial dielectric barrier discharge Martian atmosphere conversion device and method. Background Technology

[0002] Over the past few decades, space agencies around the world have conducted extensive research on Mars exploration missions and developed their own plans and strategies for Mars exploration missions, Mars sample return missions, and future manned Mars missions. Based on the orbital mechanics principles of the Hohmann transfer orbit, a Mars launch window occurs only once every two years, and a one-way journey takes approximately six months. This means that astronauts on a manned Mars exploration mission would need to stay on Mars for about a year. Employing in-situ resource utilization technology to produce energy and life support supplies needed for surface scientific activities and return journeys on Mars can effectively reduce launch costs and mission risks; therefore, this field has received widespread attention in recent years.

[0003] The Martian atmosphere is primarily composed of carbon dioxide, making up approximately 95.3% (with the remaining major components including 2.7% argon and 1.6% nitrogen). Carbon dioxide can serve as a raw material for producing various critical resources needed for Mars exploration: for example, the decomposition of carbon dioxide produces carbon monoxide and oxygen, and the reaction of carbon dioxide with hydrogen, under the action of a catalyst, can generate various hydrocarbons (including methane, ethylene, and other important fuels and chemical raw materials). In the long term, if carbon dioxide can be completely decomposed into elemental carbon, it can provide the basic materials for constructing various carbon structures and organic molecules.

[0004] The key challenge in carbon dioxide conversion lies in the high stability of its molecules. Carbon dioxide decomposition requires at least 5.5 eV of energy, making it a strongly endothermic process. Currently, traditional carbon dioxide conversion processes on Earth mainly employ thermocatalysis and electrochemical techniques, which suffer from low energy efficiency, reliance on rare metal materials, and the need for high-temperature, high-pressure operating environments. These characteristics will further reduce their efficiency in the low-temperature, low-pressure environment of Mars. Therefore, researching and developing a new Martian atmospheric conversion technology that can effectively adapt to the Martian surface environment is increasingly important. Summary of the Invention

[0005] To address the shortcomings of existing technologies, the present invention aims to provide a parallel coaxial dielectric barrier discharge Mars atmospheric conversion device, which solves the problems of low energy efficiency, reliance on rare metal materials, and the need for high-temperature and high-pressure working environments in existing devices and methods.

[0006] To solve the above-mentioned technical problems, the present invention adopts the following technical solution: a parallel coaxial dielectric barrier discharge Mars atmosphere conversion device, comprising a high-frequency AC power supply and a Mars atmosphere conversion module connected together.

[0007] The Mars atmosphere conversion module includes a circulating water ground electrode and multiple coaxial dielectric barrier discharge reactors inserted within the circulating water ground electrode. Both ends of the multiple coaxial dielectric barrier discharge reactors extend out of the circulating water ground electrode.

[0008] The Mars atmosphere conversion module also includes a high-voltage electrode, which comprises a metal plate and a metal rod vertically mounted on the metal plate, the metal rod being inserted into a coaxial dielectric barrier discharge reactor.

[0009] The high-frequency AC power supply is used to power the Martian atmospheric conversion module.

[0010] The present invention also has the following technical features: The coaxial dielectric barrier discharge reactor includes a quartz tube and a reaction gas inlet and a reaction gas outlet formed on the quartz tube.

[0011] The reaction gas inlet is located at one end of the quartz tube that exits the circulating water ground electrode, and the reaction gas outlet is located at the other end of the quartz tube that exits the circulating water ground electrode.

[0012] The metal rod is inserted into one end of the quartz tube.

[0013] The circulating water ground electrode includes a circulating water ground electrode cavity and a circulating water inlet and a circulating water outlet opened on the circulating water ground electrode cavity.

[0014] The circulating water ground electrode cavity is in the shape of a hollow cylinder, and the circulating water inlet and circulating water outlet are located on the peripheral side of the circulating water ground electrode cavity.

[0015] The circulating water ground electrode cavity is provided with reactor tube holes on both ends, and the quartz tube is inserted into the reactor tube holes.

[0016] A water-passing plate is also installed inside the circulating water ground electrode cavity.

[0017] A support leg is also installed on one end face of the circulating water ground electrode cavity, and the support leg is located on the other side of the high-frequency AC power supply.

[0018] The high-frequency AC power supply includes a high-frequency AC power supply housing and a circuit module installed inside the high-frequency AC power supply housing.

[0019] The high-frequency AC power supply housing is in the shape of a hollow cylinder, and a power inlet is installed at the end of the high-frequency AC power supply housing facing away from the circulating water ground electrode.

[0020] The metal plate is installed on the inner end face of the high-frequency AC power supply housing, and the metal rod extends out of the inner end face of the high-frequency AC power supply housing and into the quartz tube.

[0021] One end of the quartz tube is fixed to the outer end face of the high-frequency AC power supply housing.

[0022] The parallel coaxial dielectric barrier discharge Mars atmospheric conversion device also includes a control mechanism.

[0023] The control mechanism includes a mounting plate and a motor connected to the mounting plate via a support frame.

[0024] A lifting mechanism is also installed on the output shaft of the motor via a coupling. A screw is also installed on the lifting mechanism. The screw passes through the mounting plate and connects to the circulating water ground electrode cavity. The lifting mechanism and the screw work together to drive the circulating water ground electrode cavity to move on the quartz tube.

[0025] One end of the quartz tube is connected to the mounting plate, and the support leg passes through the mounting plate and is slidably connected to the mounting plate.

[0026] A parallel coaxial dielectric barrier discharge method for Martian atmospheric conversion, implemented using the aforementioned device, includes the following steps: Step 1: Turn on the motor remote control lifting mechanism in the control mechanism and power it. Adjust the lifting mechanism according to the actual working needs, and adjust the circulating water ground electrode to the predetermined position through the screw and coupling.

[0027] Step 2: Turn on the circulating water system. Circulating water flows into the circulating water ground electrode cavity from the lower circulating water inlet, and after passing through the entire structure, it flows out from the circulating water outlet and enters the thermal management module of the in-situ resource utilization system for recycling.

[0028] Step 3: Turn on the external gas supply device to provide the Martian atmosphere required for the operation of multiple parallel coaxial dielectric barrier discharge reactors. The gas flows into the quartz tube from the reaction gas inlet and then flows out from the reaction gas outlet.

[0029] Step 4: Turn on the high-frequency AC power supply to power the high-voltage electrode and the circulating water ground electrode in the Mars atmosphere conversion module. After the working gas passes through the plasma discharge zone in the coaxial dielectric barrier discharge reactor, it is converted into specific target products such as carbon monoxide, oxygen, and methane through processes such as carbon dioxide decomposition reaction and carbon dioxide hydrogenation reaction, thus completing the Mars atmosphere conversion process based on coaxial dielectric barrier discharge.

[0030] Compared with the prior art, the present invention has the following technical effects: (I) The present invention provides a parallel coaxial dielectric barrier discharge Mars atmospheric conversion device, which uses a parallel coaxial dielectric barrier discharge Mars atmospheric conversion device to connect multiple conventional single-tube packed bed coaxial dielectric barrier discharge reactors in parallel. After system integration and process optimization, it is used for efficient in-situ resource utilization of the Martian atmosphere. It can directly achieve a stable and efficient carbon dioxide conversion process under the Martian surface environment, and solve the demand for key energy life support materials such as oxygen and methane in future deep space exploration.

[0031] (II) The present invention provides a parallel coaxial dielectric barrier discharge Mars atmospheric conversion device, which integrates the traditional single-tube packed bed dielectric barrier discharge reactor in parallel, significantly improving the total propellant production and improving system efficiency through effective power matching.

[0032] (III) The present invention provides a parallel coaxial dielectric barrier discharge Mars atmospheric conversion device, which uses a circulating water ground electrode as the ground electrode of the coaxial plasma reactor. This design can simultaneously meet the requirements of the plasma discharge ground electrode and system thermal management, and adjust the temperature conditions inside the reactor according to different system operating requirements. The temperature gradient between reaction tubes can be adjusted according to different system water circulation schemes. Based on the difference in suitable operating temperature, different carbon dioxide conversion reactions can be realized between different reaction tubes of the same device, such as carbon dioxide decomposition to produce oxygen and carbon dioxide methanation. Attached Figure Description

[0033] Figure 1 This is a schematic diagram of the overall structure of the parallel coaxial dielectric barrier discharge Mars atmospheric conversion device of the present invention.

[0034] Figure 2 This is a cross-sectional structural schematic diagram of the parallel coaxial dielectric barrier discharge Mars atmospheric conversion device of the present invention.

[0035] Figure 3 This is a top view schematic diagram of the parallel coaxial dielectric barrier discharge Mars atmospheric conversion device of the present invention.

[0036] Figure 4 This is a schematic diagram of the overall structure of the circulating water ground electrode of the present invention.

[0037] Figure 5 This is a schematic diagram of one structure of the water-passing plate of the present invention.

[0038] Figure 6 This is a schematic diagram of another structure of the water-passing plate of the present invention.

[0039] Figure 7 This is a schematic diagram of the first specific structure of the circuit module of the present invention.

[0040] Figure 8 This is a specific circuit topology for the first specific structure of the circuit module of the present invention.

[0041] Figure 9 This is a specific circuit implementation of the first specific structure of the circuit module of the present invention.

[0042] Figure 10 This is a schematic diagram of a second specific structure of the circuit module of the present invention.

[0043] Figure 11 This is a schematic diagram of the third specific structure of the circuit module of the present invention.

[0044] Figure 12 This is a schematic diagram of the fourth specific structure of the circuit module of the present invention.

[0045] The meanings of the labels in the attached diagram are as follows: 1-High-frequency AC power supply, 2-Mars atmosphere conversion module, 3-Control mechanism.

[0046] 1-1-High-frequency AC power supply housing, 1-2-Circuit module, 1-3-Power input.

[0047] 2-1-Circulating water ground electrode, 2-2-Coaxial dielectric barrier discharge reactor, 2-3-High voltage electrode.

[0048] 3-1-Mounting plate, 3-2-Support frame, 3-3-Motor, 3-4-Coupling, 3-5-Lifting mechanism, 3-6-Screw.

[0049] 2-1-1-Circulating water ground electrode cavity, 2-1-2-Circulating water inlet, 2-1-3-Circulating water outlet, 2-1-4-Reactor tube hole, 2-1-5-Water flow plate, 2-1-6-Support leg.

[0050] 2-2-1-Quartz tube, 2-2-2-Reaction gas inlet, 2-2-3-Reaction gas outlet.

[0051] 2-3-1-Metal plate, 2-3-2-Metal rod.

[0052] The specific content of the present invention will be further explained in detail below with reference to the embodiments. Detailed Implementation

[0053] Unless otherwise specified, all components in this invention are components known in the prior art.

[0054] The following are specific embodiments of the present invention. It should be noted that the present invention is not limited to the following specific embodiments. All equivalent modifications made based on the technical solutions of this application fall within the protection scope of the present invention.

[0055] Example 1: This embodiment provides a parallel coaxial dielectric barrier discharge Martian atmospheric conversion device, such as... Figures 1-3 As shown, it includes a high-frequency AC power supply 1 and a Mars atmosphere conversion module 2 connected together.

[0056] The Mars atmosphere conversion module 2 includes a circulating water ground electrode 2-1 and multiple coaxial dielectric barrier discharge reactors 2-2 inserted inside the circulating water ground electrode 2-1. Both ends of the multiple coaxial dielectric barrier discharge reactors 2-2 extend out of the circulating water ground electrode 2-1.

[0057] The Mars atmosphere conversion module 2 also includes a high-voltage electrode 2-3, which includes a metal plate 2-3-1 and a metal rod 2-3-2 vertically mounted on the metal plate 2-3-1. The metal rod 2-3-2 is inserted into the coaxial dielectric barrier discharge reactor 2-2.

[0058] The high-frequency AC power supply 1 is used to supply power to the Martian atmosphere conversion module 2 and the control mechanism 3.

[0059] As a preferred embodiment: The coaxial dielectric barrier discharge reactor 2-2 includes a quartz tube 2-2-1 and a reaction gas inlet 2-2-2 and a reaction gas outlet 2-2-3 opened on the quartz tube 2-2-1.

[0060] The reaction gas inlet 2-2-2 is located at one end of the quartz tube 2-2-1 that exits the circulating water ground electrode 2-1, and the reaction gas outlet 2-2-3 is located at the other end of the quartz tube 2-2-1 that exits the circulating water ground electrode 2-1.

[0061] The metal rod 2-3-2 is inserted into one end of the quartz tube 2-2-1.

[0062] The Mars Atmosphere Conversion Module 2 consists of a circulating water ground electrode 2-1, a coaxial dielectric barrier discharge reactor 2-2, and a high-voltage electrode 2-3.

[0063] The coaxial dielectric barrier discharge reactor 2-2 comprises twenty identical quartz tubes 2-2-1, with a length ranging from 100 to 200 mm and a diameter ranging from 10 to 18 mm.

[0064] The high-voltage electrode 2-3 consists of twenty metal rods 2-3-2 with a diameter of 3-8 mm connected in parallel. A metal plate 2-3-1 with a diameter of 200 mm and a thickness of 1 mm is connected to the top to ensure power supply uniformity and electrode coaxiality. When the system is working, a dielectric barrier discharge is generated between the high-voltage electrode 2-3 and the circulating water ground electrode 2-1, with the quartz tube 2-2-1 serving as the dielectric layer of the discharge zone.

[0065] A catalyst can be filled between the quartz tube 2-2-1 and the metal rod 2-3-2 to achieve a reactor structure with packed bed dielectric barrier discharge. The appropriate catalyst can be filled according to different reaction requirements. For example, the carbon dioxide decomposition reaction can be filled with spherical BaTiO3 catalyst with a diameter of 0.5~2mm, and the carbon dioxide hydrogenation reaction can be filled with spherical Ni / Al2O3 catalyst with a diameter of 0.5~2mm.

[0066] The Martian atmosphere used in the Mars Atmosphere Conversion Module 2 is supplied by an external gas supply device. It flows into the quartz tube 2-2-1 from the reaction gas inlet 2-2-2. After passing through the plasma discharge zone, the Martian atmosphere is converted into specific target products such as carbon monoxide, oxygen, and methane, and then flows out from the reaction gas outlet 2-2-3.

[0067] As a preferred embodiment: The circulating water ground electrode 2-1 includes a circulating water ground electrode cavity 2-1-1 and a circulating water inlet 2-1-2 and a circulating water outlet 2-1-3 opened on the circulating water ground electrode cavity 2-1-1.

[0068] The circulating water ground electrode cavity 2-1-1 is in the shape of a hollow cylinder, and the circulating water inlet 2-1-2 and the circulating water outlet 2-1-3 are opened on the peripheral side of the circulating water ground electrode cavity 2-1-1.

[0069] The circulating water ground electrode cavity 2-1-1 is provided with reactor tube holes 2-1-4 on both ends, and the quartz tube 2-2-1 is inserted into the reactor tube holes 2-1-4.

[0070] A water-passing plate 2-1-5 is also installed inside the circulating water ground electrode cavity 2-1-1.

[0071] The circulating water ground electrode cavity 2-1-1 is also equipped with a support leg 2-1-6 on one end face, and the support leg 2-1-6 is located on the other side of the high-frequency AC power supply 1.

[0072] This system features a targeted design for the circulating water ground electrode 2-1 to improve system efficiency and environmental adaptability. Circulating water is introduced into the circulating water ground electrode cavity 2-1-1 to simultaneously meet the requirements of plasma discharge ground electrode and system thermal management.

[0073] like Figure 4 As shown, the circulating water ground electrode cavity 2-1-1 is supported on the control mechanism 3 by the support leg 2-1-6. Twenty quartz tubes 2-2-1 are tightly inserted into the reactor tube hole 2-1-4 to ensure uniform and stable discharge. Circulating water flows in from the lower circulating water inlet 2-1-2, and after passing through the entire structure, it flows out from the circulating water outlet 2-1-3 and enters the in-situ resource utilization system thermal management module for recycling.

[0074] Figure 5 One configuration of the water-passing plate 2-1-5 is shown. This plate-type water-passing plate 2-1-5 allows circulating water to flow in from below, then sequentially through twenty baffle zones via specially designed alternating upper and lower baffle holes, each corresponding to one of the twenty dielectric barrier discharge reactors. Finally, the circulating water flows out from above into the ground electrode cavity 2-1-1. This structure allows for adjustment of the temperature conditions in each zone by regulating the temperature and flow rate of the circulating water. Heat conduction through the circulating water enables the twenty dielectric barrier discharge reactors to operate in different temperature zones. Because the thermodynamic properties of various Martian atmospheric transformation reactions differ, different reactions can be set within each reactor to obtain the optimal reaction rate based on the actual temperature. For example, the carbon dioxide decomposition reaction is endothermic and should be placed in the high-temperature zone; the carbon dioxide methanation reaction is exothermic and should be placed in the low-temperature zone.

[0075] Figure 6 Another form of the water-passing plate 2-1-5 is shown, employing a spiral water-passing plate 2-1-5. Circulating water flows in from below, gradually rises through the spiral structure, and flows out from the top of the circulating water ground electrode cavity 2-1-1. This design effectively extends the residence time of circulating water inside the circulating water ground electrode cavity 2-1-1, fully realizing heat exchange between the circulating water and the quartz tube 2-2-1.

[0076] As a preferred embodiment: The high-frequency AC power supply 1 includes a high-frequency AC power supply housing 1-1 and a circuit module 1-2 installed inside the high-frequency AC power supply housing 1-1.

[0077] The high-frequency AC power supply housing 1-1 is in the shape of a hollow cylinder, and a power inlet 1-3 is installed at the end of the high-frequency AC power supply housing 1-1 facing away from the circulating water ground electrode 2-1.

[0078] The metal plate 2-3-1 is installed on the inner end face of the high-frequency AC power supply housing 1-1, and the metal rod 2-3-2 extends out of the inner end face of the high-frequency AC power supply housing 1-1 and into the quartz tube 2-2-1.

[0079] One end of the quartz tube 2-2-1 is fixed to the outer end face of the high-frequency AC power supply housing 1-1.

[0080] As a preferred embodiment: The parallel coaxial dielectric barrier discharge Mars atmospheric conversion device also includes a control mechanism 3.

[0081] The control mechanism 3 includes a mounting plate 3-1 and a motor 3-3 connected to the mounting plate 3-1 via a support frame 3-2.

[0082] A lifting mechanism 3-5 is also installed on the output shaft of the motor 3-3 via a coupling 3-4. A screw 3-6 is also installed on the lifting mechanism 3-5. The screw 3-6 passes through the mounting plate 3-1 and connects to the circulating water ground electrode cavity 2-1-1. The lifting mechanism 3-5 and the screw 3-6 work together to drive the circulating water ground electrode cavity 2-1-1 to move on the quartz tube 2-2-1.

[0083] One end of the quartz tube 2-2-1 is connected to the mounting plate 3-1, and the support leg 2-1-6 passes through the mounting plate 3-1 and is slidably connected to the mounting plate 3-1.

[0084] In the control mechanism 3, the lifting mechanism 3-5 is powered and remotely controlled via motor 3-3. The lifting mechanism 3-5 is connected to the circulating water ground electrode 2-1 via screw 3-6 and coupling 3-4. The height of the circulating water ground electrode 2-1 module can be adjusted according to actual working needs, thereby adjusting the length of the plasma discharge area and the reactor temperature control area. The support frame 3-2 ensures a stable connection between the motor 3-3 and the lifting mechanism 3-5 and the Mars atmospheric conversion module 2.

[0085] As a preferred embodiment: During operation, this system receives a stable bus voltage from an external power source to the high-frequency AC power supply 1 of this device. Depending on the application scenario, this bus voltage can be a DC voltage ranging from 10V to 400V or an AC voltage ranging from 24V to 400V. Common operating conditions are 28V DC, 100V DC, or 220V AC. The high-frequency AC power supply 1 powers the Mars atmospheric conversion module 2 and the control mechanism 3. The specific power output is shown below: The first specific structure of circuit module 1-2 is as follows: Figure 7As shown, this embodiment features low-voltage, low-frequency input and high-voltage, high-frequency sinusoidal output. The power input is a square wave or sinusoidal AC voltage with an effective value between 24V and 400V and a frequency between 20Hz and 400Hz; the output is a sinusoidal AC voltage with an effective value between 4kV and 10kV and a frequency between 5kHz and 10kHz. Rectifier 11 converts the input power supply into a DC voltage with an amplitude between 34V and 800V. The digital circuits, analog circuits, and drive circuits are powered by a self-starting circuit. DC transformer 12 processes the DC voltage output from rectifier 11 with a turns ratio between 0.04 and 23, while also providing electrical isolation between the input and output. When the turns ratio is 1 and there is no electrical isolation, DC transformer 12 can be omitted. Inverter 13 converts the output of DC transformer 12 into a high-frequency sinusoidal AC voltage with an effective value adjustable between 24V and 1.5kV and a frequency adjustable between 5kHz and 10kHz. Transformer 14 boosts the output of inverter 13 with a turns ratio between 6 and 420. DC transformer 15 converts the output of rectifier 11 into a DC voltage with an amplitude between 3V and 48V, providing power to the digital circuits, analog circuits, and drive circuits in DC transformer 12 and inverter 13. Cooling airflow provides a cold source and insulating medium for power electronic converters 11, 12, 13, 15, and transformer 14.

[0086] The specific circuit topology for the first specific structure of circuit module 1-2 is shown in [reference needed]. Figure 8 The input IN is a sinusoidal AC voltage with an effective value of 220V and a frequency of 50Hz; the output OUT is a sinusoidal AC voltage with an effective value adjustable from 6kV to 10kV and a frequency adjustable from 5kHz to 10kHz; the rectifier 11, composed of full-bridge uncontrolled rectifiers D1~D4, inductor L1, MOSFET S1, and capacitor C1, converts the input IN into a stable DC voltage with an amplitude of 450V, while simultaneously achieving power factor correction at the AC port to reduce the impact on other equipment in the network; the DC transformer 12 is omitted; the inverter 13 consists of full-bridge MOSFETs Composed of S3~S6, inductor L2 and capacitor C3, it converts the output of rectifier 11 into a sinusoidal AC voltage with an effective value of 150V~250V and a frequency of 5kHz~10kHz that is adjustable. Transformer 14 has a turns ratio of 1:40 and boosts the output of inverter 13 to a sinusoidal AC voltage with an effective value of 6kV~10kV and a constant frequency. MOSFET S2, transformer T2, diode D5 and capacitor C2 form DC transformer 15, which converts the output of rectifier 11 into a DC voltage AUX with an amplitude of 15V, which is used to provide auxiliary power to the digital circuits, analog circuits and drive circuits in inverter 13.

[0087] The specific circuit implementation of the first specific structure of circuit module 1-2 is shown in [link to implementation details]. Figure 9The input IN enters from the power inlet 10; the positive terminal of the output OUT flows out from the power outlet 101, supplying power to the Mars atmosphere conversion module 2; the rectifier 11, inverter 13 and DC transformer 15 are arranged as shown in the figure. The transformer 14 is split into sub-transformers 141~143 to reduce the overall height and make full use of the substrate area. The parts are electrically connected by copper wires on the substrate; the cooling airflow enters the cavity from the airflow inlet 18 to cool the substrate and components, and then flows out of the plasma power module through the airflow outlet 19, and enters the in-situ resource utilization system thermal management module for recycling.

[0088] The second specific structure of circuit module 1-2 is as follows: Figure 10 As shown, the second specific structure is a low-voltage DC input and a high-voltage, high-frequency sinusoidal output. The power input is a DC voltage with an amplitude between 10V and 400V; the output is a sinusoidal AC voltage with an effective value between 4kV and 10kV and a frequency between 5kHz and 10kHz. DC transformer 12 regulates and boosts the input DC voltage, with an output DC voltage amplitude between 34V and 800V. It also provides electrical isolation between the input and output. The power supply for the digital circuits, analog circuits, and drive circuits comes from the self-starting circuit. Inverter 13 converts the output of DC transformer 12 into a high-frequency sinusoidal AC voltage with an effective value adjustable between 24V and 1.5kV and a frequency adjustable between 5kHz and 10kHz. Transformer 14 boosts the output of inverter 13 with a turns ratio between 6 and 420. DC transformer 15 converts the output of DC transformer 12 into a DC voltage with an amplitude between 3V and 48V, providing power for the digital circuits, analog circuits, and drive circuits in inverter 13. Cooling airflow provides a cold source and insulating medium for power electronic converters 12, 13, 15, and transformer 14.

[0089] The third specific structure of circuit module 1-2 is as follows Figure 11As shown, the third specific structure features a low-voltage, low-frequency input and a high-voltage, high-frequency square wave or pulse output. The power input is a square wave or sinusoidal AC voltage with an effective value between 24V and 400V and a frequency between 20Hz and 400Hz. The output is a square wave AC or pulse voltage with an amplitude between 4kV and 15kV and a frequency between 5kHz and 20kHz. The rectifier 11 converts the input power supply to a DC voltage with an amplitude between 34V and 800V. The power supply for the digital circuits, analog circuits, and drive circuits comes from the self-starting circuit. The DC transformer 12 processes the DC voltage output from the rectifier 11, with a turns ratio between 0.04 and 23, while simultaneously providing electrical isolation between the input and output. When the turns ratio is 1 and there is no electrical isolation, the DC transformer 12 can be omitted. The inverter 13 converts the output of the DC transformer 12 into a high-frequency square wave AC or pulse voltage with an adjustable amplitude between 24V and 2.2kV and an adjustable frequency between 5kHz and 20kHz. Transformer 14 boosts the output of inverter 13, with a turns ratio between 6 and 420. Magnetic pulse compression circuit 16 narrows the edge of the square wave voltage output from transformer 14. In scenarios where the steepness of the square wave edge is not critical, this pulse compression circuit 16 can be omitted. DC transformer 15 converts the output of rectifier 11 into a DC voltage with an amplitude between 3V and 48V, providing power to the digital, analog, and drive circuits in DC transformer 12 and inverter 13. Cooling airflow provides a cold source and insulating medium for power electronic converters 11, 12, 13, 15, transformer 14, and magnetic pulse compression circuit 16.

[0090] The fourth specific structure of circuit module 1-2 is as follows Figure 12As shown, the fourth specific structure is a low-voltage DC input and a high-voltage high-frequency square wave output. The power input is a square wave or sinusoidal AC voltage with an effective value between 24V and 400V and a frequency between 20Hz and 400Hz; the output is a square wave AC voltage with an amplitude between 4kV and 15kV and a frequency between 5kHz and 10kHz. Rectifier 11 converts the input power supply into a DC voltage with an amplitude between 34V and 800V, wherein the power supply for the digital circuit, analog circuit, and drive circuit comes from the self-starting circuit; inverter 13 converts the output of rectifier 11 into a high-frequency AC voltage with an adjustable amplitude between 24V and 2.2kV; transformer 14 boosts the output of inverter 13 with a turns ratio between 6 and 420; rectifier 111 rectifies the output of transformer 14 into a high-voltage DC voltage; inverter 131 directly inverts the output of rectifier 111 into a high-frequency square wave AC voltage. The edge steepness is guaranteed, and the frequency is adjustable between 5kHz and 10kHz; the DC transformer 15 converts the output of the rectifier 11 into a DC voltage with an amplitude between 3V and 48V, providing power to the digital circuits, analog circuits and drive circuits in the DC transformer 13, and providing power to the digital circuits, analog circuits and drive circuits in the rectifier 111 and inverter 131 through the isolation DC transformer 17; the cooling airflow provides a cold source and insulating medium for the power electronic converters 11, 13, 15, 17, 111, 131 and transformer 14.

[0091] This invention provides a parallel coaxial dielectric barrier discharge Mars atmospheric conversion device. It is designed with a dedicated high-frequency AC power supply according to the working requirements of the plasma system. The power supply and reactor are highly integrated and share the grounding and cooling airflow, which realizes the miniaturization and weight reduction of the system. It can realize different power output capabilities such as sine wave, pulse, and square wave according to the actual mission requirements.

[0092] Example 2: This embodiment provides a parallel coaxial dielectric barrier discharge method for Martian atmospheric conversion, implemented using the apparatus described in Embodiment 1, and includes the following steps: Step 1: Turn on the motor 3-3 in the control mechanism 3 to remotely control the lifting mechanism 3-5 and supply it with power. Adjust the lifting mechanism 3-5 according to the actual working needs. Adjust the circulating water ground electrode 2-1 to the predetermined position through the screw 3-6 and coupling 3-4.

[0093] Step 2: Start the circulating water system. Circulating water flows into the circulating water ground electrode cavity 2-1-1 from the lower circulating water inlet 2-1-2, and after passing through the entire structure, it flows out from the circulating water outlet 2-1-3 and enters the in-situ resource utilization system thermal management module for recycling.

[0094] Step 3: Turn on the external gas supply device to provide the Martian atmosphere required for the operation of multiple parallel coaxial dielectric barrier discharge reactors 2-2. The gas flows into the quartz tube 2-2-1 from the reaction gas inlet 2-2-2 and then flows out from the reaction gas outlet 2-2-3.

[0095] Step 4: Turn on the high-frequency AC power supply 1 to supply power to the high-voltage electrode 2-3 and the circulating water ground electrode 2-1 in the Mars atmosphere conversion module 2. After the working gas passes through the plasma discharge zone in the coaxial dielectric barrier discharge reactor 2-2, it is converted into specific target products such as carbon monoxide, oxygen, and methane through processes such as carbon dioxide decomposition reaction and carbon dioxide hydrogenation reaction, thus completing the Mars atmosphere conversion process based on coaxial dielectric barrier discharge.

[0096] The specific working process of this invention: Under the Martian surface environment, the use of cryogenic plasma technology for carbon dioxide conversion offers numerous advantages, including strong environmental adaptability and high system efficiency. Compared to traditional thermochemical or electrochemical conversion technologies, the in-situ resource utilization system of the Martian atmosphere based on cryogenic plasma technology can operate directly under Martian surface conditions without the need for additional heating and pressurization equipment, effectively reducing system weight. In traditional technical routes, the system requires high purity of the feed gas, necessitating prior purification of the Martian atmosphere to remove trace gas components. However, the plasma conversion system eliminates the need for feed gas purification and separation. Conversely, trace amounts of argon and nitrogen in the Martian atmosphere can actually enhance the efficiency of the plasma system. Argon optimizes the electron energy distribution in plasma discharge, while nitrogen promotes energy transfer to the asymmetric stretching vibration mode of carbon dioxide, thereby enhancing the vibrational excitation of carbon dioxide. Furthermore, the Martian surface pressure of approximately 700 Pa (only 0.7% of Earth's) falls precisely within the optimal operating range of the plasma device, avoiding the drawbacks of excessively frequent electron collisions and difficulty in acceleration under high pressure environments, while overcoming the problem of low electron-heavy particle energy transfer efficiency in ultra-low pressure environments. This means that the application of this technology on Mars could achieve higher energy efficiency than on Earth. Finally, plasma technology has a dual advantage in the low-temperature environment of the Martian surface (averaging approximately -60°C): on the one hand, this low temperature promotes vibrational quantum exchange processes through long-range intermolecular gravitational interactions; on the other hand, it suppresses the dissipation of vibrational energy into gas thermal motion caused by collisional deactivation. Domestic and international research indicates that its efficiency on Mars will be significantly higher than on Earth. In conclusion, using plasma for Martian atmospheric conversion on the Martian surface can significantly reduce the resupply requirements of Mars exploration missions, enabling the sustainable development of future deep space exploration missions.

[0097] The above technical solutions are merely preferred embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions conceived by those skilled in the art within the scope of the technology disclosed in the present invention without creative effort are covered within the scope of protection of the present invention.

Claims

1. A parallel coaxial dielectric barrier discharge Martian atmosphere conversion device, characterized in that, It includes a high-frequency AC power supply (1) for connection and a Mars atmosphere conversion module (2); The Mars atmosphere conversion module (2) includes a circulating water ground electrode (2-1) and multiple coaxial dielectric barrier discharge reactors (2-2) inserted inside the circulating water ground electrode (2-1). Both ends of the multiple coaxial dielectric barrier discharge reactors (2-2) extend out of the circulating water ground electrode (2-1). The Mars atmosphere conversion module (2) further includes a high-voltage electrode (2-3), which includes a metal plate (2-3-1) and a metal rod (2-3-2) vertically mounted on the metal plate (2-3-1). The metal rod (2-3-2) is inserted into the coaxial dielectric barrier discharge reactor (2-2). The high-frequency AC power supply (1) is used to supply power to the Martian atmospheric conversion module (2).

2. The parallel coaxial dielectric barrier discharge Martian atmosphere conversion device as described in claim 1, characterized in that, The coaxial dielectric barrier discharge reactor (2-2) includes a quartz tube (2-2-1) and a reaction gas inlet (2-2-2) and a reaction gas outlet (2-2-3) opened on the quartz tube (2-2-1). The reaction gas inlet (2-2-2) is located at one end of the quartz tube (2-2-1) that exits the circulating water ground electrode (2-1), and the reaction gas outlet (2-2-3) is located at the other end of the quartz tube (2-2-1) that exits the circulating water ground electrode (2-1). The metal rod (2-3-2) is inserted into one end of the quartz tube (2-2-1).

3. The parallel coaxial dielectric barrier discharge Mars atmospheric conversion device as described in claim 2, characterized in that, The circulating water ground electrode (2-1) includes a circulating water ground electrode cavity (2-1-1) and a circulating water inlet (2-1-2) and a circulating water outlet (2-1-3) opened on the circulating water ground electrode cavity (2-1-1). The circulating water ground electrode cavity (2-1-1) is in the shape of a hollow cylinder, and the circulating water inlet (2-1-2) and circulating water outlet (2-1-3) are opened on the peripheral side of the circulating water ground electrode cavity (2-1-1). The circulating water ground electrode cavity (2-1-1) is also provided with reactor tube holes (2-1-4) on both ends, and the quartz tube (2-2-1) is inserted into the reactor tube holes (2-1-4); The circulating water ground electrode cavity (2-1-1) is also equipped with a water-passing plate (2-1-5); The circulating water ground electrode cavity (2-1-1) is also equipped with a support leg (2-1-6) on one end face, and the support leg (2-1-6) is located on the other side of the high-frequency AC power supply (1).

4. The parallel coaxial dielectric barrier discharge Martian atmosphere conversion device as described in claim 3, characterized in that, The high-frequency AC power supply (1) includes a high-frequency AC power supply housing (1-1) and a circuit module (1-2) installed inside the high-frequency AC power supply housing (1-1). The high-frequency AC power supply housing (1-1) is a hollow cylinder, and a power inlet (1-3) is installed at the end of the high-frequency AC power supply housing (1-1) facing away from the circulating water ground electrode (2-1). The metal plate (2-3-1) is installed on the inner end face of the high-frequency AC power supply housing (1-1), and the metal rod (2-3-2) extends out of the inner end face of the high-frequency AC power supply housing (1-1) and into the quartz tube (2-2-1); One end of the quartz tube (2-2-1) is fixed to the outer end face of the high-frequency AC power supply housing (1-1).

5. A parallel coaxial dielectric barrier discharge Mars atmospheric conversion device as described in claim 4, characterized in that, The parallel coaxial dielectric barrier discharge Mars atmosphere conversion device also includes a control mechanism (3). The control mechanism (3) includes a mounting plate (3-1) and a motor (3-3) connected to the mounting plate (3-1) via a support frame (3-2). A lifting mechanism (3-5) is also installed on the output shaft of the motor (3-3) via a coupling (3-4). A screw (3-6) is also installed on the lifting mechanism (3-5). The screw (3-6) passes through the mounting plate (3-1) and connects to the circulating water ground electrode cavity (2-1-1). The lifting mechanism (3-5) and the screw (3-6) work together to drive the circulating water ground electrode cavity (2-1-1) to move on the quartz tube (2-2-1). One end of the quartz tube (2-2-1) is connected to the mounting plate (3-1), and the support leg (2-1-6) passes through the mounting plate (3-1) and is slidably connected to the mounting plate (3-1).

6. A parallel coaxial dielectric barrier discharge method for Martian atmospheric conversion, characterized in that, Implemented using the apparatus of any one of claims 1-5, comprising the following steps: Step 1: Turn on the motor (3-3) in the control mechanism (3) to remotely control the lifting mechanism (3-5) and supply it with power. Adjust the lifting mechanism (3-5) according to the actual working needs. Adjust the circulating water ground electrode (2-1) to the predetermined position through the screw (3-6) and coupling (3-4). Step 2: Start the circulating water system. Circulating water flows into the circulating water ground electrode cavity (2-1-1) from the lower circulating water inlet (2-1-2), and after passing through the entire structure, it flows out from the circulating water outlet (2-1-3) and enters the thermal management module of the in-situ resource utilization system for recycling. Step 3: Turn on the external gas supply device to provide the Martian atmosphere required for the operation of multiple parallel coaxial dielectric barrier discharge reactors (2-2). The gas flows into the quartz tube (2-2-1) from the reaction gas inlet (2-2-2) and then flows out from the reaction gas outlet (2-2-3). Step 4: Turn on the high-frequency AC power supply (1) to supply power to the high-voltage electrode (2-3) and the circulating water ground electrode (2-1) in the Mars atmosphere conversion module (2). After the working gas passes through the plasma discharge zone in the coaxial dielectric barrier discharge reactor (2-2), it is converted into specific target products such as carbon monoxide, oxygen, and methane through processes such as carbon dioxide decomposition reaction and carbon dioxide hydrogenation reaction, thus completing the Mars atmosphere conversion process based on coaxial dielectric barrier discharge.

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