Ground comprehensive experiment platform and method for space superconducting electromagnetic propulsion device

Abstract

The invention discloses a ground comprehensive experiment platform and method for a space superconducting electromagnetic propulsion device, and belongs to the technical field of space electric propulsion. The ground comprehensive experiment platform comprises a vacuum system, an electric propulsion performance test system, a power supply system, an air supply system and a comprehensive control system; the vacuum system comprises a vacuum cavity; the electric pushing performance test system is arranged in the vacuum cavity; the upper computers of the power supply system, the air supply system and the comprehensive control system and the flow meter connected with the air supply system are arranged outside the vacuum cavity and are respectively connected with corresponding equipment in the cavity; the power supply system is used for supplying power to a superconducting magnet of the superconducting propeller and generating plasma plume for the superconducting propeller; the air supply system is connected to the superconducting electric propeller; signals acquired by the signal acquisition subsystem of the comprehensive control system are provided for the upper computer. According to the invention, an integrated and comprehensive experimental platform of the space superconducting electromagnetic propulsion device ground is constructed, and key performance parameters of the space superconducting electromagnetic propulsion device can be fully tested.

Description

Technical Field

[0001] This invention belongs to the field of space electric propulsion technology, specifically relating to a ground-based integrated experimental platform and method for a space superconducting electromagnetic propulsion device. Background Technology

[0002] Space electric propulsion technology uses high-temperature plasma generated by the ionization of propellants such as xenon to accelerate and eject the propellant, providing reverse thrust to the spacecraft. Compared to chemical propulsion, electric propulsion can increase the specific impulse by more than 10 times (specific impulse is an important physical parameter for measuring the efficiency of rocket or aircraft engines, defined as the impulse generated per unit of propellant, which can be measured in seconds or meters per second), allowing for longer-duration space transfer missions. Among them, the magneto-plasma thruster (MPDT), as a novel electric propulsion technology, works by using a strong magnetic field to accelerate the ejection of plasma ionized from the propellant to generate thrust. It can achieve a specific impulse of up to 10,000 s and a thrust of tens of Newtons. With its performance parameters gradually improving, MPDT has become a research hotspot.

[0003] Before MPDTs can be used in space, their performance must be thoroughly tested and verified, including plasma density, plume morphology, thruster thrust, and thruster lifespan under high-temperature conditions. Therefore, it is necessary to design a comprehensive experimental platform to test and evaluate the key performance characteristics of space electric thrusters.

[0004] Existing electric propulsion performance testing systems are mostly derived from conventional thruster platforms and can only measure single parameters. They cannot conduct comprehensive testing and are unable to meet the comprehensive measurement requirements of MPDT high-density plasma parameters and morphology, as well as high thrust (propulsion systems composed of multiple high-thrust main engines connected in parallel). Therefore, it is necessary to build a dedicated experimental platform for MPDT comprehensive performance testing that evolves from "single-item index testing" to "system integration optimization". Summary of the Invention

[0005] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0006] A ground-based integrated experimental platform for a space superconducting electromagnetic propulsion device includes: a vacuum system, an electric propulsion performance testing system, a power supply system, a gas supply system, and an integrated control system. The vacuum system includes a vacuum chamber and a vacuum pumping device located outside the vacuum chamber. The electric propulsion performance testing system is located inside the vacuum chamber of the vacuum system. The host computer and flow meter connected to the gas supply system in the power supply system, gas supply system, and integrated control system are all located outside the vacuum chamber and are connected to the corresponding equipment inside the chamber through pipelines passing through the vacuum chamber. The power supply system is used to power the superconducting magnet of the superconducting thruster and to generate a plasma plume for the superconducting thruster. The gas tank of the gas supply system is connected to the superconducting thruster through a gas pipe passing through the vacuum chamber to provide the required working fluid for the superconducting thruster. The integrated control system includes a signal acquisition subsystem and a host computer, and the signals acquired by the signal acquisition subsystem are provided to the host computer.

[0007] A ground-based integrated experimental method for a space superconducting electromagnetic propulsion device, used in the aforementioned ground-based integrated experimental device, comprising:

[0008] Step 1: Before the experiment begins, adjust the relative positions of the superconducting thruster, diagnostic device, and thrust measurement device using a three-dimensional moving installation platform.

[0009] Step 2: Establish a vacuum environment of not less than 0.01 Pa in the vacuum chamber: First, turn on the coarse vacuum pump to pump the vacuum level in the vacuum chamber to more than 1 Pa. Then, turn on the fine vacuum pump to pump the vacuum level in the vacuum chamber to more than 0.01 Pa. While pumping the vacuum, start the refrigerator in time to cool the superconducting magnet of the superconducting thruster so that it reaches the superconducting state.

[0010] Step 3: Once the vacuum level in the vacuum chamber and the temperature of the superconducting magnet in the superconducting thruster meet the experimental requirements, open the shut-off valve of the gas supply system and supply inert gas working fluid to the superconducting thruster through the gas tank.

[0011] Step 4: Next, plasma is generated by breaking down the inert gas working fluid through a high-voltage ignition power supply, and the superconducting magnet of the superconducting thruster is excited by a DC power supply to confine and adjust the plasma; at the same time, the performance parameters of the plasma plume and the thrust value are measured using a diagnostic device and a thrust measurement device.

[0012] The present invention has the following beneficial effects:

[0013] This invention proposes a ground-based integrated experimental platform for a space superconducting electromagnetic propulsion device. By setting up a vacuum system, an electric propulsion performance testing system, a power supply system, a gas supply system, and an integrated control system, an integrated and comprehensive ground-based experimental platform for a space superconducting electromagnetic propulsion device is constructed. This platform can fully test the key performance parameters of the space superconducting electromagnetic propulsion device and strongly promote the further development of superconducting propulsion technology.

[0014] (1) The ground-based integrated experimental platform for space superconducting electromagnetic propulsion device provided by the present invention, by setting up diagnostic devices, thrust measurement devices, etc., helps to systematically test and observe the key performance of superconducting propulsion devices, including plasma density measurement, plasma morphology observation, thrust measurement and propulsion expected life calculation, etc.

[0015] (2) The ground-based integrated experimental platform for the space superconducting electromagnetic propulsion device provided by the present invention can flexibly adjust the relative position between the diagnostic and measurement device and the superconducting propulsion device by setting up a three-dimensional moving platform in the vacuum cavity, and detect the propulsion performance of the superconducting propulsion device at different positions.

[0016] (3) The ground-based integrated experimental platform for the space superconducting electromagnetic propulsion device provided by the present invention has sufficient space for expansion installation by setting up a vacuum cavity, which can be used to install more measuring devices, such as high-speed camera systems, spectrometers, etc., and realize further observation and analysis of the plasma plume state.

[0017] (4) The ground integrated experimental platform for the space superconducting electromagnetic propulsion device provided by the present invention, through the setting of two-stage vacuum pumps for coarse pumping and fine pumping, can not only quickly reduce the vacuum degree in the vacuum chamber to below 0.01 Pa, but also maintain the vacuum degree in the vacuum chamber not higher than 0.1 Pa during the gas supply and ignition of the superconducting propulsion device.

[0018] (5) The ground integrated experimental platform for the space superconducting electromagnetic propulsion device provided by the present invention integrates the experimental platform control process by setting up an integrated control system, which not only helps to improve experimental efficiency, but also realizes safety interlocking. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the ground-based integrated experimental platform for the space superconducting electromagnetic propulsion device of the present invention, wherein: 1-vacuum chamber, 2-vacuum pumping device, 3-superconducting thruster, 4-refrigeration unit, 5-diagnostic device, 6-thrust measuring device, 7-DC power supply, 8-high-voltage ignition power supply, 9-gas tank, 10-stop valve, 11-host computer, 12-vacuum gauge, 13-low temperature thermometer, 14-flow meter, 15-displacement sensor, 16-Langmuir probe, 17-three-dimensional moving installation platform, 18-coarse vacuum pump, 19-fine vacuum pump, 20-vacuum breaker valve, 21-glass window, 22-rapid-drive telescopic device. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0021] In the description of this application, it should be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application 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, they should not be construed as limitations on this application.

[0022] The main improvements of this invention lie in the integration and adjustability of the electric propulsion diagnostic measurement system. Regarding integration, this invention builds an integrated, comprehensive experimental platform, enabling systematic testing and observation of all key parameters of the thruster. Regarding adjustability, this invention builds a three-dimensional moving platform, flexibly adjusting the relative position of the diagnostic system and the thruster to measure the thruster performance parameters at different positions. Furthermore, if a thruster of different power and size is replaced, there is no need to rebuild the diagnostic system; it can be used immediately after replacement.

[0023] like Figure 1 As shown, this invention discloses a ground-based integrated experimental platform for a space superconducting electromagnetic propulsion device, comprising a vacuum system, an electric propulsion performance testing system, a power supply system, a gas supply system, and an integrated control system. The electric propulsion performance testing system is located inside the vacuum chamber 1 of the vacuum system. The host computer 11 and the flow meter 14 connected to the gas supply system, which are part of the power supply system, gas supply system, and integrated control system, are all located outside the vacuum chamber 1. Cables or gas pipes pass through the vacuum chamber 1 in all three systems.

[0024] The vacuum system includes a vacuum chamber 1 and a vacuum pumping device 2. The vacuum chamber 1 is used to provide a vacuum environment for electric thruster performance experiments, and the vacuum pumping device 2 is located outside the vacuum chamber 1 and is used to establish and maintain the vacuum level inside the vacuum chamber 1.

[0025] The electric propulsion performance testing system includes a superconducting thruster 3, a cryostat 4, a diagnostic device 5, and a thrust measurement device 6, all installed inside the vacuum chamber 1. The cryostat 4 is mounted on the superconducting magnet (which is part of the superconducting thruster 3) of the superconducting thruster 3 and provides a cooling source for the superconducting coils. The diagnostic device 5 and the thrust measurement device 6 are mounted at the front end of the superconducting thruster 3 and are used to measure the plasma plume performance parameters and thrust value of the superconducting thruster 3 during operation, respectively.

[0026] The power supply system, used to power the superconducting magnet of the superconducting thruster 3 and generate a plasma plume, includes a DC power supply 7 and a high-voltage ignition power supply 8, which are independent of each other. The power supply line of the DC power supply 7 passes through the vacuum chamber 1 and connects to the superconducting magnet, providing DC power to the superconducting magnet of the superconducting thruster 3. The power supply line of the high-voltage ignition power supply 8 passes through the vacuum chamber 1 and connects to the electrodes of the superconducting thruster 3, breaking down the inert gas working fluid to generate a plasma plume.

[0027] The gas supply system includes a gas tank 9 and a shut-off valve 10. The gas tank 9 passes through the vacuum chamber 1 via a gas pipe and is connected to the superconducting thruster 3 to provide the required working fluid to the superconducting thruster 3. The shut-off valve 10 is located on the gas pipe between the gas tank 9 and the vacuum chamber 1 and is used to control the on / off state of the gas supply.

[0028] The integrated control system includes a signal acquisition subsystem and a host computer 11 located outside the vacuum chamber 1. The signal acquisition subsystem includes, but is not limited to: a vacuum gauge 12 located on the wall of the vacuum chamber 1 and connected to the vacuum system; a flow meter 14 located outside the vacuum chamber 1 and connected to the gas supply system; and several low-temperature thermometers 13, displacement sensors 15, and Langmuir probes 16 located inside the vacuum chamber 1 and connected to the electric propulsion performance testing system. These signal acquisition devices are used to acquire corresponding local signals and provide them to the host computer 11.

[0029] All devices of the electric propulsion performance testing system are installed inside the vacuum chamber 1; the host computer 11 included in the power supply system, gas supply system and integrated control system is located outside the vacuum chamber 1, and is connected to the corresponding equipment inside the chamber through pipelines passing through the vacuum chamber 1.

[0030] A three-dimensional mobile mounting platform 17 is installed at the bottom inside the vacuum chamber 1 to adjust the relative positions of the various devices in the electric propulsion performance testing system. The three-dimensional mobile mounting platform 17 is a three-axis mobile platform with X, Y, and Z axes. The X-axis is a guide rail laid along the length of the vacuum chamber 1. The Z-axis is a guide rail fixed to the X-axis for controlling vertical movement. The Y-axis is a guide rail perpendicular to the X and Z axes for controlling horizontal movement, and is mounted on the Z-axis. A mounting surface is provided on the Y-axis for mounting and fixing the superconducting thruster 3, diagnostic device 5, and thrust measuring device 6, etc. Only one set of X-axis is provided, while multiple independent sets of Y and Z axes can be provided, thus enabling free adjustment of the relative positions of the various devices in the electric propulsion performance testing system.

[0031] The vacuum pumping device 2 includes a coarse vacuum pump 18 and a fine vacuum pump 19. The coarse vacuum pump 18 is located at the rear end of the vacuum pumping device 2 and is used to pump the vacuum level inside the vacuum chamber 1 to about 1 Pa. The fine vacuum pump 19 is located at the front end of the vacuum pumping device 2 and is used to pump the vacuum level inside the vacuum chamber 1 to 0.01 Pa or higher.

[0032] Vacuum chamber 1 is equipped with a vacuum breaking valve 20, which is used to break the vacuum at the end of the experiment or in an emergency.

[0033] Glass windows 21 are provided at both ends and symmetrically on both sides of the vacuum chamber 1 to observe the experimental status of the electric thruster.

[0034] The diagnostic device 5 is equipped with a fast-drive telescopic device 22 to prevent the Langmuir probe 16 from staying in the high-temperature plasma region for too long, which could damage the probe.

[0035] The distance between the thrust measuring device 6 and the superconducting thruster 3 can be adjusted by the three-dimensional moving installation platform 17. The thrust measuring device 6 is used to measure the thrust changes at different plume positions.

[0036] The signal acquisition subsystem includes, but is not limited to, the following signal acquisition devices:

[0037] Vacuum gauge 12 is installed on the wall of vacuum chamber 1 and is used to detect the vacuum level inside vacuum chamber 1.

[0038] Flow meter 14 is installed on the gas supply pipeline of the gas supply system to detect and control the flow rate of inert gas working medium.

[0039] Several low-temperature thermometers 13 are respectively installed on the cold head of the refrigerator 4 and the superconducting coil of the superconducting thruster 3 to detect the temperature of the refrigerator 4 and the superconducting magnet.

[0040] The displacement sensor 15 is installed on the thrust measuring device 6 to collect the minute deformation of the target plate of the thrust measuring device 6 during the operation of the superconducting thruster 3, and convert the minute deformation signal into a thrust signal; the plasma ejected by the superconducting thruster 3 hits the thrust measuring device 6, causing the thrust measuring device 6 to produce minute deformation, and the displacement sensor collects the minute deformation.

[0041] The Langmuir probe 16, installed at the end of the diagnostic device 5, is used to collect parameters of the plasma plume ejected during the operation of the superconducting thruster 3.

[0042] The experimental method of this experimental platform includes the following steps:

[0043] Step 1: Based on the actual needs of the experiment, before the experiment begins, adjust the relative positions between the superconducting thruster 3, the diagnostic device 5, and the thrust measuring device 6 using the three-dimensional moving installation platform 17.

[0044] Step 2: Establish a vacuum environment of not less than 0.01 Pa within vacuum chamber 1: First, turn on the coarse vacuum pump 18 to evacuate the vacuum level in vacuum chamber 1 to above 1 Pa. Then, turn on the fine vacuum pump 19 to evacuate the vacuum level in vacuum chamber 1 to above 0.01 Pa. Simultaneously with the evacuation, start the refrigerator 4 to cool the superconducting magnet of the superconducting thruster 3, bringing it to a superconducting state in preparation for excitation.

[0045] Step 3: When the vacuum level in the vacuum chamber 1 and the temperature of the superconducting magnet in the superconducting thruster 3 meet the experimental requirements, the shut-off valve 10 of the gas supply system is opened, and inert gas working fluid is supplied to the superconducting thruster 3 through the gas tank 9.

[0046] Step 4: Immediately following, plasma is generated by breaking down the inert gas working fluid using a high-voltage ignition power supply 8. The superconducting magnet of the superconducting thruster 3 is then energized by a DC power supply 7 to confine and adjust the plasma. Simultaneously, the performance parameters of the plasma plume and the thrust value are measured using a diagnostic device 5 and a thrust measurement device 6, thereby achieving the corresponding experimental objectives.

[0047] After the experimental platform is started, the status of the entire platform needs to be monitored at all times through the integrated control system. For example, during vacuuming, the vacuum level in the vacuum chamber 1 is detected by vacuum gauge 12; the temperature of the superconducting magnet of the superconducting thruster 3 is detected by cryothermometer 13; and the flow rate of the working fluid is detected and controlled by flow meter 14. Furthermore, the integrated control system needs to control the safety interlocks of the entire experimental platform to prevent situations such as quenching failure. For example, when the signal acquisition subsystem detects an increase in the superconducting power supply voltage, which may indicate a risk of quenching failure, the safety interlocks quickly cut off the power supply of the high-voltage ignition power supply 8 and the DC power supply 7, stop the gas supply system, and close the vacuuming shut-off valve (located between the vacuuming device 2 and the vacuum chamber 1) to ensure the safety of the experimental personnel and equipment.

[0048] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to interchangeably. Each embodiment focuses on describing the differences from other embodiments. In particular, the system embodiments are basically similar to the method embodiments, so the description is relatively simple; relevant parts can be referred to the descriptions in the method embodiments.

[0049] The above description is merely an embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of the present invention should be included within the scope of the claims of the present invention.

[0050] The contents not described in detail in this specification are existing technologies known to those skilled in the art.

Claims

1. A ground-based integrated experimental platform for a space superconducting electromagnetic propulsion device, characterized in that, include: The system comprises a vacuum system, an electric propulsion performance testing system, a power supply system, a gas supply system, and an integrated control system. The vacuum system includes a vacuum chamber and a vacuum pumping device located outside the vacuum chamber. The electric propulsion performance testing system is located inside the vacuum chamber of the vacuum system. The host computer and flow meter connected to the gas supply system in the power supply system, gas supply system, and integrated control system are all located outside the vacuum chamber and are connected to the corresponding equipment inside the chamber via pipelines passing through the vacuum chamber. The power supply system is used to power the superconducting magnet of the superconducting thruster and to generate plasma plumes for the superconducting thruster. The gas supply system's gas tank is connected to the superconducting thruster through a gas pipe passing through the vacuum chamber, providing the superconducting thruster with the required working fluid; the integrated control system includes a signal acquisition subsystem and a host computer, with the signals acquired by the signal acquisition subsystem being provided to the host computer.

2. The ground-based integrated experimental platform for the space superconducting electromagnetic propulsion device according to claim 1, characterized in that, The vacuum system includes a vacuum chamber and a vacuum pumping device. The vacuum chamber is used to provide a vacuum environment for electric thruster performance experiments, while the vacuum pumping device is located outside the vacuum chamber and is used to establish and maintain the vacuum level inside the vacuum chamber.

3. The ground-based integrated experimental platform for the space superconducting electromagnetic propulsion device according to claim 1, characterized in that, The electric propulsion performance testing system includes a superconducting thruster, a cryostat, a diagnostic device, and a thrust measurement device installed inside a vacuum chamber. The cryostat is installed on the superconducting magnet of the superconducting thruster to provide a cold source for the superconducting coil. The diagnostic device and the thrust measurement device are installed at the front end of the superconducting thruster and are used to measure the plasma plume performance parameters and thrust value during the operation of the superconducting thruster, respectively.

4. The ground-based integrated experimental platform for the space superconducting electromagnetic propulsion device according to claim 1, characterized in that, The power system includes a DC power supply and a high-voltage ignition power supply, which are independent of each other. The power supply line of the DC power supply passes through the vacuum cavity and is connected to the superconducting magnet to provide DC power to the superconducting magnet of the superconducting thruster. The power supply line of the high-voltage ignition power supply passes through the vacuum cavity and is connected to the electrode of the superconducting thruster to break down the inert gas working fluid and generate a plasma plume.

5. The ground-based integrated experimental platform for the space superconducting electromagnetic propulsion device according to claim 1, characterized in that, The gas supply system includes a gas tank and a shut-off valve. The gas tank passes through the vacuum chamber via a gas pipe and is connected to the superconducting thruster to provide the superconducting thruster with the required working fluid. The shut-off valve is located on the gas pipe between the gas tank and the vacuum chamber and is used to control the on / off state of the gas supply.

6. The ground-based integrated experimental platform for the space superconducting electromagnetic propulsion device according to claim 1, characterized in that, The signal acquisition subsystem includes: a vacuum gauge installed on the wall of the vacuum chamber and connected to the vacuum system; a flow meter installed outside the vacuum chamber and connected to the gas supply system; and several low-temperature thermometers, displacement sensors, and Langmuir probes installed inside the vacuum chamber and connected to the electric propulsion performance testing system. Vacuum gauges are used to detect the vacuum level inside a vacuum chamber; The flow meter is installed on the gas supply pipeline of the gas supply system to detect and control the flow rate of the inert gas working medium; Several low-temperature thermometers are respectively installed on the cold head of the refrigerator and the superconducting coil of the superconducting thruster to detect the temperature of the refrigerator and the superconducting magnet; A displacement sensor is installed in the thrust measurement device to collect minute deformations of the target plate of the thrust measurement device during the operation of the superconducting thruster, and convert the minute deformation signal into a thrust signal. The Langmuir probe is mounted at the end of the diagnostic device to collect parameters of the plasma plume ejected during the operation of the superconducting thruster.

7. The ground-based integrated experimental platform for the space superconducting electromagnetic propulsion device according to claim 1, characterized in that, A three-dimensional moving installation platform is set at the bottom inside the vacuum chamber to adjust the relative positions of the various devices in the electric propulsion performance testing system. The three-dimensional moving installation platform is a three-axis moving platform with X, Y, and Z axes. The X-axis is a guide rail laid along the length of the vacuum chamber, the Z-axis is a guide rail fixed on the X-axis to control vertical movement, and the Y-axis is a guide rail perpendicular to the X and Z axes to control horizontal movement. The Y-axis is mounted on the Z-axis, and a mounting surface is set on the Y-axis for mounting and fixing the superconducting thruster, diagnostic device, and thrust measurement device.

8. The ground-based integrated experimental platform for the space superconducting electromagnetic propulsion device according to claim 1, characterized in that, The vacuum pumping device includes a coarse vacuum pump and a fine vacuum pump. The coarse vacuum pump is located at the rear end of the vacuum pumping device and is used to pump the vacuum level inside the vacuum chamber to about 1 Pa. The fine vacuum pump is located at the front end of the vacuum pumping device and is used to pump the vacuum level inside the vacuum chamber to 0.01 Pa or higher.

9. The ground-based integrated experimental platform for a space superconducting electromagnetic propulsion device according to claim 1, characterized in that, The vacuum chamber is equipped with a vacuum breaking valve, which is used to break the vacuum at the end of the experiment or in an emergency. Glass windows are provided at both ends and symmetrically on both sides of the vacuum chamber for observing the experimental status of the electric thruster; The diagnostic device is equipped with a fast-drive telescopic mechanism to prevent the Langmuir probe from being damaged due to prolonged residence time in the high-temperature plasma region. The thrust measurement device is used to measure the thrust changes at different plume positions, and the distance between it and the superconducting thruster is adjusted via a three-dimensional moving installation platform.

10. A ground-based integrated experimental method for a space superconducting electromagnetic propulsion device, used on the ground-based integrated experimental platform for a space superconducting electromagnetic propulsion device as described in any one of claims 1 to 9, characterized in that, include: Step 1: Before the experiment begins, adjust the relative positions of the superconducting thruster, diagnostic device, and thrust measurement device using a three-dimensional moving installation platform. Step 2: Establish a vacuum environment of not less than 0.01 Pa in the vacuum chamber: First, turn on the coarse vacuum pump to pump the vacuum level in the vacuum chamber to more than 1 Pa. Then, turn on the fine vacuum pump to pump the vacuum level in the vacuum chamber to more than 0.01 Pa. While pumping the vacuum, start the refrigerator in time to cool the superconducting magnet of the superconducting thruster so that it reaches the superconducting state. Step 3: Once the vacuum level in the vacuum chamber and the temperature of the superconducting magnet in the superconducting thruster meet the experimental requirements, open the shut-off valve of the gas supply system and supply inert gas working fluid to the superconducting thruster through the gas tank. Step 4: Next, plasma is generated by breaking down the inert gas working fluid through a high-voltage ignition power supply, and the superconducting magnet of the superconducting thruster is excited by a DC power supply to confine and adjust the plasma; at the same time, the performance parameters of the plasma plume and the thrust value are measured using a diagnostic device and a thrust measurement device.

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