An electrolytic water-based microthruster suitable for microsatellites

Abstract

The present application relates to a kind of micro-propeller based on electrolytic water suitable for micro-satellite, the micro-propeller includes solar panel, power system, electromagnetic valve, combustion chamber and nozzle, the micro-propeller also includes electrolytic device, electrolytic water is generated hydrogen and oxygen by electrolysis technology using ion exchange membrane in orbit, and hydrogen and water separation and oxygen and water separation are achieved by adding gas-liquid separator;Between gas-liquid separator and oxygen storage tank and between gas-liquid separator and hydrogen storage tank, gas bubble breaker is also respectively equipped, and the oxygen or hydrogen bubble still existing is broken down, so that oxygen or hydrogen is released.The present application solves the problem that gas-liquid is not easy to separate in space due to the absence of gravity by designing and adding gas-liquid separation device and bubble breaker in micro-propeller based on electrolytic water, and realizes the combustion of hydrogen and oxygen generated by electrolytic water as the thrust of micro-propeller.

Description

Technical Field

[0001] This invention relates to the field of water electrolysis-based micro-thrusters, and more specifically to a water electrolysis-based micro-thruster suitable for microsatellites. Background Technology

[0002] 1. Necessity Analysis

[0003] Satellite technology is currently developing in two directions: on the one hand, researching large satellite technology, and on the other hand, developing microsatellite technology and researching satellite networking technology. Various micro and small (miniature, nano, and ultra-miniature) satellites, deep space probes, and spacecraft represent the new trend in the development of aerospace technology.

[0004] Regardless of satellite size, the propulsion system is a critical subsystem of spacecraft, primarily used for orbital maneuvers and special attitude control. With the development of microsatellite technology and the expansion of its application areas, the demand for micro-propulsion systems is becoming increasingly urgent. Microsatellite formation flying can accomplish many complex and expensive tasks that large satellites cannot, placing high demands on maintaining the relative orbital positions between satellites and achieving high-precision attitude control.

[0005] Currently, many microsatellites, due to cost or weight limitations, are not equipped with propulsion systems and rely solely on their initial velocity to operate in orbit. Towards the end of their lifespan, their speed decreases, and they re-enter the atmosphere. If microsatellites were equipped with propulsion systems and had orbit-changing capabilities, their energy efficiency would be greatly improved. For example, a large number of microsatellites could be pre-deployed in a specific orbit. Normally, these satellites would remain dormant, but in emergencies, they could be activated instantly through ground-based commands or on-orbit self-sensing, flexibly changing their orbits to enter designated orbits and perform their missions.

[0006] While traditional propulsion systems can provide high specific impulse thrust, their complex structure, large size, and weight make them unsuitable for microsatellite propulsion systems. Furthermore, most microsatellites are currently developed and used by commercial companies, and traditional propulsion systems are costly and highly specialized, lacking advantages in the commercial sector. Therefore, researching low-power, low-thrust, and low-impulse micro-propulsion systems suitable for microsatellites not only has significant application value in scientific, technological, and military fields but also holds broad commercial prospects.

[0007] This project proposes a microsatellite thruster technology based on water as a raw material. By electrolyzing water in orbit to produce hydrogen and oxygen, and then igniting it again to generate impulse, the microsatellite is provided with thrust.

[0008] 2. Current Situation Analysis

[0009] This paper mainly compares the current development status, advantages and disadvantages of various micro-thrusters, introduces the characteristics of micro-thrusters based on water electrolysis, and analyzes that this thruster is more suitable for microsatellite applications.

[0010] Micro-thrusters are an emerging research field both domestically and internationally. Research on micro-propulsion systems has attracted global attention, with dedicated topics on the subject at international conferences. International research in this area began in the 1990s. Supported by the US University Satellite Program and the Advanced Space Transportation Program, laboratories, companies, universities, and research institutions in the US, such as Stanford University and the University of Washington, are actively engaged in micro-thruster research. Universities and research institutions in Europe, the UK, and Japan are also working on micro-propulsion.

[0011] In recent years, various micro-propulsion systems based on different principles have been developed in industry and academia. Each method has its own advantages, including liquid and solid chemical propellants, electric propulsion systems, and electrothermal propulsion systems.

[0012] Miniature cold gas thrusters are miniaturized versions of large cold gas thrusters. The SNAP-1 nanosatellite launched by the University of Surrey in the UK used a gas thruster with butane as the propellant, achieving a thrust of 45 mN, a specific impulse greater than 60 s, and a system weight of less than 0.5 kg.

[0013] There are many types of micro electric propulsion, mainly classified into electrothermal, electrostatic, and electromagnetic types based on their working principles. Electrothermal electric propulsion has a simple structure and is easy to manufacture. It operates on two principles: one uses a resistance heater to heat the gas in the thrust chamber, which is then ejected through a nozzle to generate thrust; the other uses a heating resistor to heat the liquid or solid in the silicon cavity thrust chamber to its phase transition temperature. When the gas pressure from liquid evaporation or solid sublimation exceeds the pressure that a microvalve can withstand, the microvalve opens, and the gas is ejected through the nozzle to generate thrust. Electrostatic electric propulsion works by using an electrostatic field to accelerate charged ions or colloidal particles, using the reaction force to generate thrust. Currently, the main electrostatic electric propulsion technologies under research include field-effect ion engines and colloidal thrusters. Micro pulsed plasma thrusters belong to the electromagnetic electric propulsion category, and their propellants are generally solids, such as polytetrafluoroethylene (PTFE).

[0014] Chemical micro-thrusters typically generate thrust through the combustion and exothermic decomposition of propellant. The fundamental difference between them and electrothermal electric propulsion lies in the conversion of chemical energy into mechanical energy. NASA has developed a solid-fuel digital thruster that utilizes MEMS technology and SOC technology to integrate addressing drive circuitry, igniter, propellant tank, combustion chamber, micro-valve, and micro-nozzle onto a single chip. It primarily uses solid propellants, such as double-base solid nitrocellulose. This type of propulsion array often combines the tank and combustion chamber into a single unit, requiring a single propellant loading. Therefore, the energy carried is limited, the total thrust of the thruster is relatively small, and its operational lifespan is limited.

[0015] Goddard Space Flight Center has developed a prototype single-component fuel thruster. This thruster uses the catalytic decomposition of high-concentration hydrogen peroxide as its propulsion mechanism. The decomposition products generate thrust through miniature supersonic nozzles. The target thrust is 50 μN, with a specific impulse of 140–180 s.

[0016] The table below summarizes and compares the various types of micro-thrusters that have emerged in recent years.

[0017]

[0018] Before evaluating the characteristics of various thrusters, we must be aware that the characteristics of each satellite dictate different constraints. A thruster suitable for one type of satellite may not be suitable for others. For example, pulsed plasma thrusters and ion thrusters can produce extremely low thrust levels, but currently they are relatively large and heavy, and microsatellites cannot meet their high power consumption requirements. Solid-state and digital thrusters have significant inherent limitations in their principles; each small nozzle can only be used once. Therefore, these thrusters can only be made in array form, with the number of nozzles pre-set. A potential problem is that the thrust vector generated by these arrayed thrusters will be inconsistent each time during microsatellite applications. At the microsatellite scale, the different thrust positions each time will introduce new perturbations to the satellite's attitude.

[0019] Single- and dual-component fuel propulsion systems are chemical propulsion systems. Their advantage lies in offering a wider range of total impulse, thrust, and pulse bit range compared to solid propellants. However, both hydrogen peroxide and hydrazine, used as fuels, possess a degree of toxicity, requiring stringent development and testing environments, which hinders commercial application. Summary of the Invention

[0020] The purpose of this invention is to overcome the problems of existing chemical propulsion systems used in microsatellites being toxic, environmentally harmful, and difficult to manufacture, and to propose a water-electrolysis-based micro-propulsion system suitable for microsatellites.

[0021] This invention proposes a water-electrolysis-based micro-thruster suitable for microsatellites. The micro-thruster includes a solar panel, a power system, an electromagnetic valve, a combustion chamber, and a nozzle. The micro-thruster also includes an electrolysis device that uses ion exchange membrane electrolysis technology to electrolyze water in orbit to produce hydrogen and oxygen. Furthermore, a gas-liquid separator is added to separate hydrogen from water and oxygen from water.

[0022] As one of the improvements to the above technical solution, the electrolysis device includes: a water tank, an electrolytic cell, a gas-liquid separator, a hydrogen storage tank, and an oxygen storage tank;

[0023] The water tank is used to store the electrolytic aqueous solution and to transfer the aqueous solution to the electrolytic cell;

[0024] The electrolytic cell uses ion exchange membrane water electrolysis technology to electrolyze an aqueous solution to produce hydrogen and oxygen, and then transfers the produced hydrogen and oxygen to the gas-liquid separator respectively.

[0025] The gas-liquid separator is used to separate hydrogen and oxygen from the aqueous solution, and to transfer the hydrogen to a hydrogen storage tank, transfer the oxygen to an oxygen storage tank, and pressurize the aqueous solution back into the water tank.

[0026] As an improvement to the above technical solution, a pusher plate is installed in the water tank, and the pusher plate is connected to the top of the water tank by a spring; the pusher plate increases the pressure of the aqueous solution under the push of the spring and pushes the aqueous solution into the electrolysis cell.

[0027] As an improvement to the above technical solution, the electrolyzer has a proton exchange membrane in the middle; the proton exchange membrane divides the electrolyzer into a hydrogen chamber and an oxygen chamber; the hydrogen chamber and the oxygen chamber are respectively connected to a water tank through a first valve; the hydrogen chamber is connected to a gas-liquid separator through a second valve; the oxygen chamber is connected to the gas-liquid separator through a third valve.

[0028] When the first valve and the second valve are opened, under the water pressure in the water tank, the water in the electrolytic cell is forced into the oxygen chamber, and the aqueous solution mixed with hydrogen is pushed into the gas-liquid separator, which separates the hydrogen from the water.

[0029] When the first and third valves are opened, the water in the electrolytic cell is forced into the hydrogen chamber under the water pressure in the water tank, and the aqueous solution mixed with oxygen is pushed into the gas-liquid separator, which separates the oxygen from the water.

[0030] As one of the improvements to the above technical solution, the gas-liquid separator is connected to a water tank via an eighth valve, to a hydrogen storage tank via a fourth valve, and to an oxygen storage tank via a fifth valve.

[0031] When the fourth and eighth valves are open, hydrogen enters the hydrogen storage tank through the fourth valve, and the aqueous solution is pushed back to the water tank by the gas-liquid separator through the eighth valve.

[0032] When the fifth and eighth valves are open, oxygen enters the oxygen storage tank through the fifth valve, and the aqueous solution is forced back into the water tank by the gas-liquid separator through the eighth valve.

[0033] As an improvement to the above technical solution, the electrolysis device is further equipped with bubble breakers between the gas-liquid separator and the oxygen storage tank and between the gas-liquid separator and the hydrogen storage tank, respectively. These bubble breakers are used to further break up the remaining oxygen or hydrogen bubbles when the gas-liquid separator completes gas-liquid separation, so as to release the oxygen or hydrogen.

[0034] The bubble breaker has alternating high-voltage lines and high-voltage return lines inside; when energized, a high-voltage electric field is formed between the high-voltage lines and high-voltage return lines; when hydrogen or oxygen bubbles enter the bubble breaker, the high-voltage electric field ionizes the liquid film on the bubble surface, causing local discharge on the film surface, local temperature rise, and resulting in the bubble film rupturing and the release of hydrogen or oxygen.

[0035] As an improvement to the above technical solution, when the high-voltage line and the high-voltage return line are energized, the applied voltage is required to be greater than 500V.

[0036] As an improvement to the above technical solution, heating elements are attached to the outside of the hydrogen storage tank and the oxygen storage tank, respectively. The heating elements are used to heat the hydrogen storage tank and the oxygen storage tank, causing the internal gas to expand and generate a certain pressure, which forces the gas into the combustion chamber. The water vapor after combustion is sprayed out through the nozzle, thereby generating the thrust of the micro-propeller.

[0037] As an improvement to the above technical solution, the hydrogen storage tank is connected to the combustion chamber via a sixth valve, and the oxygen storage tank is connected to the combustion chamber via a seventh valve; when the sixth and seventh valves are open, hydrogen and oxygen are mixed into the combustion chamber in proportion by controlling different opening times.

[0038] As an improvement to the above technical solution, the power system includes a power control system and an electrode power controller; the solar panel obtains electrical energy through the solar sail and converts it into various voltages required by the micro-thruster using the power control system; the electrode power controller is used to supply and distribute power to the proton exchange membrane electrolyzer; the electrolysis device also includes a controller for controlling the voltage and current of the electrolysis electrodes in the proton exchange membrane electrolyzer, thereby controlling the electrolysis speed and the operation of the gas-liquid separator.

[0039] The advantages of this invention compared to the prior art are:

[0040] This invention designs a micro-thruster based on ion-exchange membrane water electrolysis technology, enabling the production of hydrogen and oxygen in space using this technology. By incorporating a gas-liquid separation device into the water-electrolysis-based micro-thruster, this invention solves the problem of gas not rising to the surface in space due to the absence of gravity, causing bubbles to remain suspended and hindering gas-liquid separation. Simultaneously, by adding a high-voltage ionization bubble breaker, the invention effectively breaks up oxygen or hydrogen bubbles in the aqueous solution, releasing the oxygen or hydrogen, significantly improving the utilization efficiency of the hydrogen and oxygen produced by water electrolysis and conserving resources. Attached Figure Description

[0041] Figure 1 This is a schematic diagram of a micro-propeller based on water electrolysis.

[0042] Figure 2 Schematic diagram of a water electrolysis-based micro-propeller for adding a gas-liquid separation device;

[0043] Figure 3 This is a schematic diagram of the high-voltage ionization bubble breaker designed for this invention. Detailed Implementation

[0044] The technical solutions provided by the present invention will be further illustrated below with reference to the embodiments.

[0045] 3. Analysis of the characteristics of micro-thrusters based on water electrolysis

[0046] Addressing the shortcomings of current micro-thrusters, this project proposes using water as a raw material to produce hydrogen and oxygen in orbit via solar electrolysis. Each time a small amount of gas is produced, it is ignited in the combustion chamber and allowed to burn completely, generating jet propulsion through nozzles to provide thrust for the satellite. This achieves a water-based conversion process from electrical energy to chemical energy to mechanical energy. Figure 1 shows the schematic diagram of a water-electrolysis-based micro-thruster.

[0047] High safety, low cost, and ease of large-scale commercial application: As an inert substance, water allows for high safety during storage and launch processes in microsatellites when used as propellant. Containers for storing water only need to maintain a pressure of 1-1.5 atmospheres, far less than containers using gaseous propellants (typically with an internal pressure of 20-30 atmospheres). Therefore, the manufacturing cost of these containers is significantly lower than that of gaseous fuel containers. Furthermore, using water as a raw material is non-toxic and pollution-free, avoiding the dangers associated with using chemical fuels.

[0048] High specific impulse, high efficiency, and relatively simple structure: According to existing reports, the specific impulse of micro-thrusters based on water electrolysis is greater than 800 m / s. Although it is lower than that of traditional chemical component thrusters, it is higher than that of most electric and cold gas thrusters. More importantly, this thruster has a simpler structure, is safer and more reliable than other thrusters, and has high overall economic benefits.

[0049] Using water as a propellant offers advantages such as ease of on-orbit preparation and broad application prospects: Currently, terrestrial liquid oxygen and liquid hydrogen engines require cryogenic environments, have bulky refueling equipment, and complex refueling processes, making on-orbit refueling and preparation difficult. Using water as a propellant not only facilitates on-orbit refueling but also allows for the on-orbit preparation of hydrogen and oxygen. Developing micro-thrusters based on water electrolysis can be applied not only to microsatellites but also provides a technological pathway for exploring planets with water, such as Mars, where evidence of water already exists. If water could be prepared on Mars and used as a propellant, it could provide energy for spacecraft returning from Mars to Earth.

[0050] 4 options

[0051] Water electrolysis technology is widely and maturely applied in industry. Electrolysis technology is divided into alkaline electrolysis, ion-exchange membrane electrolysis, and solid oxide electrolysis. Alkaline electrolysis is a mature technology with relatively low cost; ion-exchange membrane electrolysis uses more expensive materials, resulting in higher costs, but it offers a higher electrolysis rate and requires less power (around 10V), making it ideal for the power systems of microsatellites. This project plans to use ion-exchange membrane electrolysis technology to achieve on-orbit electrolysis of water to produce hydrogen and oxygen.

[0052] In space, hydrogen and oxygen are produced using water electrolysis technology. Unlike on Earth, where gravity is absent, the gases do not rise from the liquid to the surface; instead, the bubbles remain suspended in the water. Therefore, a gas-liquid separation device is designed and installed, such as... Figure 2 As shown.

[0053] Work steps:

[0054] 1. Obtain electrical energy through solar panels and convert it into various voltages required by the system using a power supply system.

[0055] 2. The electrode power controller is used to control the voltage and current of the electrolytic electrodes in the proton exchange membrane electrolyzer, thereby controlling the electrolysis rate.

[0056] 3. The water tank stores an aqueous solution for electrolysis, which contains sodium sulfate to increase conductivity.

[0057] 4. The top of the water tank can move up and down, driven by a spring, to increase the pressure on the aqueous solution, making it easier to push the water into the electrolytic cell in a weightless environment.

[0058] 5. Before starting work, all valves must be closed;

[0059] 6. When starting work, the controller opens the first valve to press 100ml of aqueous solution into the proton exchange membrane electrolyzer, and then closes the first valve.

[0060] 7. The electrode power controller controls the electrode to be energized, and hydrogen and oxygen are generated in the proton exchange membrane electrolyzer.

[0061] 8. Since hydrogen and oxygen do not rise to the surface of water like they do on land in a weightless environment, but remain suspended in the water, a centrifugal gas-liquid separator is needed to separate the gases from the water.

[0062] 9. Open the first and second valves. Under the water pressure of the water tank, 100ml of water is forced into the left electrolytic cell, and the aqueous solution mixed with hydrogen is pushed into the centrifugal gas-liquid separator. Close the first and second valves.

[0063] 10. The centrifugal gas-liquid separator starts working, and the gas and liquid are separated.

[0064] 11. In a weightless environment, when a gas separates from a liquid, in addition to pure gas, there are many bubbles that need to be broken up to release the gas.

[0065] 12. This design proposes a high-voltage ionization bubble breaker. A mixture containing bubbles is introduced into the bubble breaker through the inlet. The device contains alternating high-voltage lines and high-voltage return lines (e.g., high-voltage lines and high-voltage return lines). Figure 3 As shown in the diagram, a high-voltage electric field is formed between the bubble and the liquid film on its surface. When the bubble enters, the high-voltage electric field ionizes the liquid film on the bubble's surface, causing localized discharge and a rise in local temperature. This leads to the rupture of the bubble film and the release of gas. A high voltage greater than 500V can be applied.

[0066] In this embodiment, the bubble breaker is installed outside the gas-liquid separator, specifically on the pipeline between the separator and the fourth or fifth valve.

[0067] 13. Open the fourth and eighth valves. Hydrogen enters the hydrogen storage tank through the fourth valve, and the aqueous solution is pushed back into the water tank by the centrifugal gas-liquid separator through the eighth valve.

[0068] 14. Close the fourth and eighth valves.

[0069] 15. Next, begin separating oxygen and water. Open the first and third valves. Under the water pressure in the tank, 100ml of water is forced into the left electrolytic cell, and the aqueous solution mixed with oxygen is pushed into the centrifugal gas-liquid separator. Close the first and third valves.

[0070] 16. The centrifugal gas-liquid separator starts working, opens the fifth valve and the eighth valve, and oxygen enters the oxygen storage tank through the fifth valve. The aqueous solution is pushed back into the water tank by the centrifugal gas-liquid separator through the eighth valve.

[0071] 17. Close valves 5 and 8.

[0072] 18. Hydrogen and oxygen storage tanks are equipped with heating elements on the outside, which cause the internal gas to expand and generate a certain pressure through heating.

[0073] 19. Open the sixth and seventh valves and control their opening times to mix hydrogen and oxygen into the combustion chamber in a 2:1 ratio.

[0074] 20. Control the igniter to ignite hydrogen and oxygen. The water vapor produced after combustion is sprayed out through the nozzle, thereby generating thrust.

[0075] 21. Repeat steps 5 to 15 above.

[0076] As can be seen from the above detailed description of the present invention, the present invention designs a micro-thruster based on ion exchange membrane electrolysis water technology, and solves the problem of poor gas-liquid separation in space due to the absence of gravity by designing and installing a gas-liquid separation device and a bubble breaker in the water-based micro-thruster, thereby realizing the use of hydrogen and oxygen generated by water electrolysis as the thrust of the micro-thruster.

[0077] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to the embodiments, those skilled in the art should understand that modifications or equivalent substitutions to the technical solutions of the present invention do not depart from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A water-electrolysis-based microthruster suitable for microsatellites, the microthruster comprising a solar panel, a power system, a solenoid valve, a combustion chamber, and a nozzle, characterized in that, The micro-thruster also includes an electrolysis device, which uses ion exchange membrane electrolysis technology to electrolyze water in orbit to produce hydrogen and oxygen, and uses a centrifugal gas-liquid separator to separate hydrogen from water and oxygen from water. The micro-propulsion device also includes a bubble breaker, which is used to further break up the remaining oxygen or hydrogen bubbles after the gas-liquid separator has completed gas-liquid separation, so as to release the oxygen or hydrogen. The bubble breaker has alternating high-voltage lines and high-voltage return lines inside; when energized, a high-voltage electric field is formed between the high-voltage lines and high-voltage return lines; when hydrogen or oxygen bubbles enter the bubble breaker, the high-voltage electric field ionizes the liquid film on the bubble surface, causing local discharge on the film surface, local temperature rise, and resulting in the bubble film rupturing and the release of hydrogen or oxygen.

2. The water-electrolysis-based micro-thruster suitable for microsatellites according to claim 1, characterized in that, The electrolysis device includes: a water tank, an electrolytic cell, a gas-liquid separator, a hydrogen storage tank, and an oxygen storage tank; The water tank is used to store the electrolytic aqueous solution and to transfer the aqueous solution to the electrolytic cell; The electrolytic cell uses ion exchange membrane water electrolysis technology to electrolyze an aqueous solution to produce hydrogen and oxygen, and then transfers the produced hydrogen and oxygen to the gas-liquid separator respectively. The gas-liquid separator is used to separate hydrogen and oxygen from the aqueous solution, and to transfer the hydrogen to a hydrogen storage tank, transfer the oxygen to an oxygen storage tank, and pressurize the aqueous solution back into the water tank.

3. The water-electrolysis-based micro-thruster suitable for microsatellites according to claim 2, characterized in that, A push plate is installed in the water tank, and the push plate is connected to the top of the water tank by a spring; the push plate increases the pressure of the aqueous solution under the push of the spring and pushes the aqueous solution into the electrolytic cell.

4. The water-electrolysis-based micro-thruster suitable for microsatellites according to claim 2, characterized in that, The electrolytic cell has a proton exchange membrane in the middle; the proton exchange membrane divides the electrolytic cell into a hydrogen chamber and an oxygen chamber; the hydrogen chamber and the oxygen chamber are respectively connected to a water tank through a first valve; the hydrogen chamber is connected to a gas-liquid separator through a second valve; the oxygen chamber is connected to the gas-liquid separator through a third valve; When the first valve and the second valve are opened, under the water pressure in the water tank, the water in the electrolytic cell is forced into the oxygen chamber, and the aqueous solution mixed with hydrogen is pushed into the gas-liquid separator, which separates the hydrogen from the water. When the first and third valves are opened, the water in the electrolytic cell is forced into the hydrogen chamber under the water pressure in the water tank, and the aqueous solution mixed with oxygen is pushed into the gas-liquid separator, which separates the oxygen from the water.

5. The water-electrolysis-based micro-thruster suitable for microsatellites according to claim 2, characterized in that, The gas-liquid separator is connected to a water tank via an eighth valve, to a hydrogen storage tank via a fourth valve, and to an oxygen storage tank via a fifth valve. When the fourth and eighth valves are open, hydrogen enters the hydrogen storage tank through the fourth valve, and the aqueous solution is pushed back to the water tank by the gas-liquid separator through the eighth valve. When the fifth and eighth valves are open, oxygen enters the oxygen storage tank through the fifth valve, and the aqueous solution is forced back into the water tank by the gas-liquid separator through the eighth valve.

6. The water-electrolysis-based micro-thruster suitable for microsatellites according to claim 2, characterized in that, The electrolysis device is equipped with bubble breakers between the gas-liquid separator and the oxygen storage tank, and between the gas-liquid separator and the hydrogen storage tank.

7. The water-electrolysis-based micro-thruster suitable for microsatellites according to claim 1, characterized in that, When the high-voltage line and high-voltage return line are energized, the applied voltage must be greater than 500V.

8. The water-electrolysis-based micro-thruster suitable for microsatellites according to claim 2, characterized in that, Heating elements are attached to the outside of the hydrogen and oxygen storage tanks, respectively. The heating elements are used to heat the hydrogen and oxygen storage tanks, causing the internal gas to expand and generate a certain pressure, which forces the gas into the combustion chamber. The water vapor after combustion is sprayed out through the nozzle, thereby generating the thrust of the micro-propeller.

9. The water-electrolysis-based micro-thruster suitable for microsatellites according to claim 2, characterized in that, The hydrogen storage tank is connected to the combustion chamber via a sixth valve, and the oxygen storage tank is connected to the combustion chamber via a seventh valve. When the sixth and seventh valves are open, hydrogen and oxygen are mixed into the combustion chamber in a specific ratio by controlling different opening times.

10. The water-based micro-thruster suitable for microsatellites according to any one of claims 1-9, characterized in that, The power system includes a power control system and an electrode power controller; the solar panel obtains electrical energy through the solar sail and converts it into various voltages required by the micro-thruster using the power control system; the electrode power controller is used to supply and distribute power to the proton exchange membrane electrolyzer; the electrolysis device also includes a controller for controlling the voltage and current of the electrolysis electrodes in the proton exchange membrane electrolyzer, thereby controlling the electrolysis speed and the operation of the gas-liquid separator.

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