Hall thruster on-orbit thrust regulation device and method based on channel wall temperature

Abstract

The application provides an on-orbit thrust adjusting device and method for a Hall thruster based on a channel wall temperature, belongs to the technical field of aerospace plasma propulsion, and is characterized in that the channel wall temperature adjusting device is built for the Hall thruster under ground and on-orbit conditions. In the ground experiment stage, the parameters of different working conditions are adjusted, the wall temperature of the outer wall of the Hall thruster channel, the electron temperature and the electron density of the plume area are obtained, and a mapping database is established. In the on-orbit experiment stage, when the satellite-borne Hall thruster runs stably, the wall temperature of the outer wall of the satellite-borne Hall thruster channel, the electron temperature and the electron density of the plume area are obtained under different working conditions. The on-orbit adjustment of the thrust is carried out by changing the voltage, the excitation current and the airflow of the satellite-borne Hall thruster. The thrust is verified by combining the electron temperature and the electron density, so that the accuracy of the thrust is ensured.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aerospace plasma propulsion, and particularly relates to an on-orbit thrust adjusting device and method for a Hall thruster based on channel wall temperature. BACKGROUND

[0002] With the rapid development of aerospace technology and the successive start of China's space gravitational wave detection plans such as the Tianwen Plan and the Taiji Plan, electric propulsion technology has become an indispensable part of space missions. As one of the most representative types of electric propulsion technology, the Hall thruster has a small size, a high thrust density, and no space charge limiting, and thus has a broad application prospect in space missions such as position keeping and orbit raising of geosynchronous orbit satellites, main propulsion of near-Earth asteroid exploration, drag-free control of ultra-quiet satellite platforms, attitude adjustment of medium-low orbit spacecraft, and deep space exploration. It is very important to monitor and adjust the thrust of the Hall thruster during on-orbit operation. The thrust state of the Hall thruster during on-orbit operation can reflect the running state of the thruster, and timely monitoring and adjustment are important guarantees for the normal operation of the Hall thruster on orbit.

[0003] Currently, the thrust of the Hall thruster is mainly monitored and measured by the probe method and the spectral method. The probe method involves placing a bare metal wire at the tip of a probe into the plasma, applying a bias voltage to the probe to measure the volt-ampere characteristic curve, and analyzing the volt-ampere characteristic curve to obtain information such as the electron temperature and electron density inside the plasma. The spectral method involves analyzing the light emitted by atomic transitions and calculating the electron temperature and electron density by the collisional radiation model. The plasma temperature and density obtained by the probe method or the spectral method can be used to calculate the thrust. However, the probe method is an invasive diagnosis method that is subjected to bombardment by high-energy ions and causes interference with the discharge state of the Hall thruster, resulting in inaccurate measurement results. The spectral method also has some problems. Simply relying on spectral lines to analyze the thruster plume parameters can result in low spatial and spectral resolution, complex operation, and incomplete data, and the spectral instrument is relatively difficult to apply on orbit.

[0004] In addition, some engineering application units have found that there is a problem of inconsistency between on-orbit monitoring and adjustment of the thrust. Due to the special conditions of space such as gravity and vacuum, there is a certain difference between the on-orbit measurement of the thrust of the Hall thruster and the measurement results on the ground, which limits the application of the Hall thruster to some extent. SUMMARY

[0005] To solve the above problems, the application provides an on-orbit thrust adjusting device and method for a Hall thruster based on channel wall temperature. The method can monitor and adjust the on-orbit thrust of the Hall thruster and ensure the stable on-orbit running state of the Hall thruster.

[0006] This invention is achieved through the following technical solution:

[0007] An on-orbit thrust regulation device for Hall thrusters based on channel wall temperature:

[0008] The adjustment device is divided into an on-site adjustment module, an on-orbit adjustment module, and a data comparison module;

[0009] The local control module includes a power supply, a gas supply unit, a Hall thruster, a spectrometer, a vacuum tank, a thermocouple, and an optical probe.

[0010] The on-site adjustment module conducts monitoring and adjustment experiments on the Hall thruster in ground experiments; it obtains the wall temperature of the ceramic wall outside the Hall thruster channel, the electron temperature and electron density of the Hall thruster plume region;

[0011] The on-orbit adjustment module includes a satellite, a first onboard robotic arm, an onboard thermocouple, an onboard Hall thruster, an onboard optical camera, and a second onboard robotic arm.

[0012] The on-orbit adjustment module conducts on-orbit testing of the spaceborne Hall thruster, and obtains the wall temperature of the ceramic wall outside the channel of the spaceborne Hall thruster, the electron temperature and electron density of the plume region of the spaceborne Hall thruster.

[0013] The data comparison module is used to compare and adjust the wall temperature, electron temperature, and electron density obtained by the on-site adjustment module and the on-orbit adjustment module, so that the three parameters of the on-orbit adjustment module are the same as the three parameters of the on-site adjustment module, thereby realizing stable control of thrust and monitoring and adjustment of the Hall thruster's on-orbit thrust.

[0014] Furthermore, in the local control module, all components except the gas supply unit are housed within a vacuum tank.

[0015] The power supply provides power to the Hall thruster, and the gas supply unit provides the Hall thruster with a working gas of a certain flow rate.

[0016] The thermocouple is placed close to the outer channel wall of the Hall thruster to facilitate the measurement of its wall temperature;

[0017] An optical probe is installed in the direction of the Hall thruster plume and connected to a spectrometer outside the vacuum tank via an optical fiber through a flange. The spectrometer is used to measure spectral lines and calculate electron temperature and electron density.

[0018] Furthermore, the on-orbit adjustment module has an on-board thermocouple mounted on its first robotic arm and an on-board optical camera mounted on its second robotic arm.

[0019] When the satellite Hall thruster is running, the satellite first mechanical arm will extend the satellite thermocouple to the ceramic channel wall surface of the satellite Hall thruster to measure the temperature change thereof;

[0020] The satellite optical camera is extended to the plume direction of the satellite Hall thruster by the satellite second mechanical arm to measure the electron temperature and electron density at the time.

[0021] A method for adjusting the on-orbit thrust of a Hall thruster based on the temperature of the channel wall surface:

[0022] The method specifically comprises the following steps:

[0023] S1: For the Hall thruster, build a channel wall surface temperature adjustment device for the Hall thruster under ground and on-orbit conditions respectively;

[0024] S2: In the ground experiment stage, start the Hall thruster until it is running stably, adjust the parameters of different working conditions, obtain the wall surface temperature of the ceramic wall outside the Hall thruster channel, the electron temperature and electron density of the Hall thruster plume area;

[0025] S3: Based on the different working condition parameters and wall surface temperature, electron temperature and electron density in S2, fitting is performed to establish a mapping database of ground conditions and three obtained data;

[0026] S4: In the on-orbit experiment stage, the satellite Hall thruster is running, when the plasma plume is stable, the wall surface temperature of the ceramic wall outside the satellite Hall thruster channel, the electron temperature and electron density of the satellite Hall thruster plume area are obtained under the same working conditions as S2;

[0027] S5: The on-orbit adjustment of the thrust of the satellite Hall thruster is performed by changing the voltage, excitation current and airflow of the satellite Hall thruster;

[0028] S6: The thrust of the satellite Hall thruster is calculated combined with the electron temperature and electron density to verify the results of S5 and ensure the accuracy of the thrust.

[0029] Further, in S2, first, the vacuum tank is evacuated to reduce the pressure to 10 -3 Pa below, and the thermocouple is used to measure the temperature of the outer channel wall surface of the Hall thruster;

[0030] Then, the gas supply unit is started to supply the working gas with a certain airflow rate to the Hall thruster, and the power supply is started to supply a certain voltage and excitation current to the Hall thruster, and after the Hall thruster is running stably, the thermocouple is used to measure the temperature of the outer channel wall surface of the Hall thruster again to obtain the change of the Hall thruster outer channel wall surface temperature, and the plasma collision probability and the corresponding electron temperature are calculated from the temperature change;

[0031] At the same time, the spectrum line is measured by a spectrometer, the electron density at this time is calculated, and the Hall thruster thrust is calculated according to the electron density.

[0032] Further, in S4, the satellite-borne thermocouple is moved to the outside of the satellite by using a satellite-borne first manipulator, and is moved to the outside channel of the satellite-borne Hall thruster, so that the satellite-borne thermocouple is close to the outer wall surface, and the wall surface temperature of the ceramic wall outside the channel of the satellite-borne Hall thruster is measured.

[0033] The spectrum line is measured by a satellite-borne optical camera, the electron density at this time is calculated, and the Hall thruster thrust is calculated according to the electron density.

[0034] Further, in S5, when the satellite-borne Hall thruster thrust is adjusted, the voltage, excitation current and airflow of the satellite-borne Hall thruster are changed, and the satellite-borne thermocouple keeps monitoring the wall surface temperature of the ceramic wall outside the channel of the satellite-borne Hall thruster, so that the required on-orbit Hall thruster thrust can be obtained when the outer wall surface temperature is consistent with the required thrust temperature in the ground experiment of S2.

[0035] Further, in S6, the spectrum line is measured by a satellite-borne optical camera, the electron density at this time is calculated, and the satellite-borne Hall thruster thrust is calculated according to the electron temperature and the electron density; the result is verified to ensure the accuracy of the thrust.

[0036] An electronic device includes a memory and a processor, the memory stores a computer program, and the processor implements the steps of the above method when executing the computer program.

[0037] A computer readable storage medium for storing computer instructions, the computer instructions are executed by a processor to implement the steps of the above method.

[0038] Advantages of the present application

[0039] The monitoring device of the present application has simple structure and is easy to implement; the method principle has high reliability and accuracy, and has high spatial resolution and time resolution; the monitoring method can be used for batch testing of thrusters, and can greatly reduce the testing time and cost. BRIEF DESCRIPTION OF DRAWINGS

[0040] Figure 1 is a flowchart of the present application;

[0041] Figure 2 is a device schematic diagram of the ground thrust monitoring and adjustment of the Hall thruster of the embodiment of the present application;

[0042] Figure 3 is a device schematic diagram of the on-orbit thrust monitoring and adjustment of the Hall thruster of the embodiment of the present application.

[0043] Wherein power-1, gas supply unit-2, Hall thruster-3, spectrometer-4, vacuum tank-5, thermocouple 6, optical probe-7, satellite-8, on-board first manipulator-9, on-board thermocouple-10, on-board Hall thruster-11, on-board optical camera-12, on-board second manipulator-13. DETAILED DESCRIPTION

[0044] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0045] In combination Figures 1 to 3 .

[0046] The present application first carries out monitoring and adjustment experiment of the Hall thruster in ground experiment. The Hall thruster is placed in the vacuum tank, and the thermocouple is attached to the ceramic wall outside the Hall thruster channel to monitor the temperature change of the surface. The optical probe is installed in the direction of the Hall thruster plume, and is connected to the spectrometer outside the vacuum tank through the flange by the optical fiber. The wall temperature at this time is recorded by the thermocouple before starting the Hall thruster. The Hall thruster is started, and a certain current and airflow are given. When the Hall thruster runs stably, the thermocouple is used for measurement to obtain the temperature change of the ceramic wall. The wall temperature can reflect the discharge state of the plasma, and the plasma collision probability can be obtained from the temperature change of the ceramic wall, so as to calculate the thrust of the Hall thruster. At the same time, the spectrum line at this time is measured by the spectrometer, and the electronic temperature density at this time is calculated, so as to calculate the thrust at this time. Several groups of working conditions are made to obtain the corresponding relationship between the thrust and the wall temperature, the electronic temperature and the electronic density at this time

[0047] Then, the monitoring and adjustment of the Hall thruster are carried out in orbit. Two manipulators are designed on the satellite, and a thermocouple and a spectrometer are connected respectively. When the Hall thruster runs on the satellite, the thermocouple is stretched to the ceramic channel wall of the Hall thruster through the manipulator to measure the temperature change. The spectrometer is stretched to the plume direction of the Hall thruster through the other manipulator to measure the electronic temperature and the electronic density at this time. The wall temperature, the electronic temperature and the electronic density are compared with the ground measurement results, the airflow and the current of the Hall thruster at this time are adjusted to make the three parameters consistent with those in the ground experiment, so that the stable control of the thrust can be realized, and the monitoring and adjustment of the Hall thruster thrust in orbit can be realized.

[0048] Embodiment 1: The present application designs a Hall thruster in-orbit thrust adjustment device based on the channel wall temperature:

[0049] The adjusting device is divided into an on-ground adjusting module, an on-orbit adjusting module and a data comparison module;

[0050] The on-ground adjusting module includes a power supply 1, a gas supply unit 2, a Hall thruster 3, a spectrometer 4, a vacuum tank 5, a thermocouple 6 and an optical probe 7. Figure 2 The on-ground adjusting module performs monitoring and adjusting experiments of the Hall thruster 3 in ground experiments, and obtains the wall temperature of the ceramic wall outside the channel of the Hall thruster 3, the electron temperature and the electron density of the plume area of the Hall thruster 3.

[0051] The on-orbit adjusting module includes a satellite 8, a first on-orbit manipulator 9, a first on-orbit thermocouple 10, a first on-orbit Hall thruster 11, a first on-orbit optical camera 12 and a second on-orbit manipulator 13.

[0052] The on-orbit adjusting module performs monitoring and adjusting experiments of the first on-orbit Hall thruster 11 in on-orbit experiments, and obtains the wall temperature of the ceramic wall outside the channel of the first on-orbit Hall thruster 11, the electron temperature and the electron density of the plume area of the first on-orbit Hall thruster 11. Figure 3 The on-orbit adjusting module includes a satellite 8, a first on-orbit manipulator 9, a first on-orbit thermocouple 10, a first on-orbit Hall thruster 11, a first on-orbit optical camera 12 and a second on-orbit manipulator 13.

[0053] The on-orbit adjusting module performs monitoring and adjusting experiments of the first on-orbit Hall thruster 11 in on-orbit experiments, and obtains the wall temperature of the ceramic wall outside the channel of the first on-orbit Hall thruster 11, the electron temperature and the electron density of the plume area of the first on-orbit Hall thruster 11.

[0054] The data comparison module is used for comparing and adjusting the wall temperature, the electron temperature and the electron density obtained by the on-ground adjusting module and the on-orbit adjusting module, so that the three parameters of the on-orbit adjusting module are the same as those of the on-ground adjusting module, and the stable control of the thrust, the on-orbit monitoring and adjustment of the Hall thruster are realized.

[0055] In the on-ground adjusting module, all devices except the gas supply unit 2 are placed in the vacuum tank 5,

[0056] The power supply 1 supplies power to the Hall thruster 3, and the gas supply unit 2 supplies the working gas with a certain flow rate to the Hall thruster 3.

[0057] The thermocouple 6 is placed close to the outer channel wall of the Hall thruster 3, which is convenient for measuring the wall temperature.

[0058] An optical probe 7 is installed in the direction of the plume of the Hall thruster 3, and is connected to the spectrometer 4 outside the vacuum tank through a flange by an optical fiber. The spectrometer 4 is used for measuring the spectral line, and calculating the electron temperature and the electron density.

[0059] The first on-orbit thermocouple 10 is installed on the first on-orbit manipulator 9 of the on-orbit adjusting module, and the first on-orbit optical camera 12 is installed on the second on-orbit manipulator 13.

[0060] When the satellite Hall thruster 11 is running, the satellite first mechanical arm 9 extends the satellite thermocouple 10 to the ceramic channel wall surface of the satellite Hall thruster 11 to measure the temperature change thereof;

[0061] The satellite optical camera 12 extends to the plume direction of the satellite Hall thruster 11 through the satellite second mechanical arm 13 to measure the electron temperature and electron density at this time.

[0062] Embodiment 2: Based on the above-described mounting, the application designs a Hall thruster in-orbit thrust adjustment method based on the channel wall surface temperature:

[0063] As Figure 1 , the method specifically comprises the following steps:

[0064] S1: For any type of Hall thruster, a channel wall surface temperature adjustment device is built for the type of Hall thruster under the ground and in-orbit conditions;

[0065] S2: In the ground experiment stage, the Hall thruster 3 is started until it is running stably, the parameters of different working conditions are adjusted, the wall surface temperature of the ceramic wall outside the channel of the Hall thruster 3, the electron temperature and electron density of the plume region of the Hall thruster 3 are obtained;

[0066] In S2, as Figure 2 shown, first, the vacuum tank 5 is evacuated, and the pressure is reduced to 10 -3 Pa below, the temperature of the outer channel wall surface of the Hall thruster 3 is measured by using the thermocouple 6;

[0067] Then, the gas supply unit 2 is started to supply the working gas with a certain flow rate to the Hall thruster 3, and the power supply 1 is started to supply the Hall thruster 3 with a certain voltage and excitation current, and after the Hall thruster 3 is running stably, the temperature of the outer channel wall surface of the Hall thruster 3 is measured again by using the thermocouple 6, the change of the outer channel wall surface temperature of the Hall thruster is obtained, and the plasma collision probability and the corresponding electron temperature are calculated from the temperature change;

[0068] At the same time, the spectrum spectrometer 4 is used to measure the spectrum spectrum line at this time, and the electron density at this time is calculated, and the thrust of the Hall thruster can be calculated from the electron density.

[0069] S3: Based on the different working condition parameters and wall surface temperature, electron temperature and electron density in S2, fitting is performed to establish a mapping database of the ground condition and the three obtained data;

[0070] S4: In the in-orbit experiment stage, the satellite Hall thruster 11 is running, and when the plasma plume is stable, the wall surface temperature of the ceramic wall outside the channel of the satellite Hall thruster 11, the electron temperature and electron density of the plume region of the satellite Hall thruster 11 are obtained under the same working condition as S2;

[0071] In S4, the satellite electrothermal couple 10 is moved outside the satellite by using the satellite first mechanical arm 9, and is moved to the outside passage of the satellite Hall thruster 11, so that the satellite electrothermal couple 10 is close to the outer wall surface, and the wall surface temperature of the ceramic wall outside the passage of the satellite Hall thruster 11 is measured.

[0072] The spectral line at this time is measured by using the satellite optical camera 12, the electron density at this time is calculated, and the thrust of the Hall thruster is calculated.

[0073] S5: The on-orbit adjustment of the thrust of the satellite Hall thruster 11 is performed by changing the voltage, excitation current and airflow of the satellite Hall thruster 11.

[0074] In S5, when the thrust of the satellite Hall thruster 11 is adjusted, the voltage, excitation current and airflow of the satellite Hall thruster 11 are changed, and the monitoring of the wall surface temperature of the ceramic wall outside the passage of the satellite Hall thruster 11 by the satellite electrothermal couple 10 is maintained, and when the outer wall surface temperature is consistent with the temperature required by the ground experiment in S2, the required on-orbit Hall thruster thrust is obtained.

[0075] S6: The thrust of the satellite Hall thruster 11 is calculated by combining the electron temperature and the electron density, and the result of S5 is verified to ensure the accuracy of the thrust.

[0076] In S6, the spectral line at this time is measured by using the satellite optical camera 12, the electron density at this time is calculated, and the thrust of the satellite Hall thruster 11 is calculated by combining the electron temperature and the electron density; the result is verified to ensure the accuracy of the thrust.

[0077] An electronic device, comprising a memory and a processor, wherein the memory stores a computer program, and the processor implements the steps of the above method when executing the computer program.

[0078] A computer readable storage medium for storing computer instructions, wherein the computer instructions are executed by a processor to implement the steps of the above method.

[0079] The memory in the embodiments of the application can be a volatile memory or a nonvolatile memory, or can include both volatile and nonvolatile memory. Where the nonvolatile memory is a read-only memory (ROM), programmable ROM (PROM), erasable PROM (EPROM), electrically EPROM (EEPROM), or flash memory. The volatile memory can be a random access memory (RAM), which is used as an external cache. By way of example, and not limitation, many forms of RAM are available, for example, static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDR SDRAM), enhanced SDRAM (ESDRAM), synchlink DRAM (SLDRAM), and direct rambus RAM (DR RAM). Note that the memory described herein is intended to include, among others, these and any other memory suitable for storing the data adaptively described herein.

[0080] In the above embodiments, all or part of the embodiments can be implemented by software, hardware, firmware or any combination thereof. When implemented by software, all or part of the embodiments can be implemented in the form of a computer program product. The computer program product includes one or more computer instructions. When the computer instructions are loaded and executed on a computer, all or part of the processes or functions described in the embodiments of the present application are generated. The computer can be a general-purpose computer, a special-purpose computer, a computer network or other programmable apparatus. The computer instructions can be stored in a computer-readable storage medium or transferred from one computer-readable storage medium to another computer-readable storage medium, for example, the computer instructions can be transferred from one website, computer, server or data center to another website, computer, server or data center through wired, such as coaxial cable, optical fiber, digital subscriber line (DSL) or wireless, such as infrared, wireless, microwave, etc. The computer-readable storage medium can be any available medium that can be accessed by a computer or a data storage device such as a server, data center, etc. integrated with one or more available media. The available media can be magnetic media, such as floppy disks, hard disks, magnetic tapes, optical media, such as digital video discs (DVD), or semiconductor media, such as solid state discs (SSD), etc.

[0081] In the implementation process, each step of the above method can be completed by integrated logic circuit of hardware in the processor or instruction in the form of software. The steps of the method disclosed in the embodiments of the present application can be directly embodied as hardware processor execution or executed by combination of hardware and software modules in the processor. The software module can be located in random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, register or other mature storage medium in the art. The storage medium is located in the memory, and the processor reads the information in the memory and combines the hardware to complete the steps of the above method. To avoid repetition, it will not be described in detail here.

[0082] It should be noted that the processor in the embodiments of the present application can be an integrated circuit chip with signal processing capability. In the implementation process, each step of the method embodiments can be completed by integrated logic circuits or instructions in the form of software of the hardware in the processor. The processor mentioned above can be a general processor, a digital signal processor DSP, an application specific integrated circuit ASIC, a field programmable gate array FPGA or other programmable logic devices, discrete gates or transistor logic devices, discrete hardware components. The disclosed methods, steps and logic block diagrams in the embodiments of the present application can be implemented or executed. The general processor can be a microprocessor or the processor can be any conventional processor. The steps of the method disclosed in combination with the embodiments of the present application can be directly embodied as hardware code processor execution completion, or executed by hardware and software module combination in the code processor. The software module can be located in the random access memory, the flash memory, the read only memory, the programmable read only memory or the electrically erasable programmable memory, the register and other mature storage media in the art. The storage medium is located in the memory, and the processor reads the information in the memory, and combines the hardware to complete the steps of the above method.

[0083] The on-orbit thrust adjusting device and method of the Hall thruster based on the channel wall temperature are described in detail above, and the principles and implementation modes of the present application are described. The above embodiment is only used to help understand the method of the present application and its core idea; at the same time, for those skilled in the art, according to the idea of the present application, the specific implementation mode and application range will be changed, and the above description should not be understood as a limitation of the present application.

Claims

1. An on-orbit thrust adjustment device for a Hall thruster based on channel wall temperature, characterized in that: The adjustment device is divided into an on-site adjustment module, an on-orbit adjustment module, and a data comparison module; The local regulation module includes a power supply (1), a gas supply unit (2), a Hall thruster (3), a spectrometer (4), a vacuum tank (5), a thermocouple (6), and an optical probe (7). The on-site adjustment module conducts monitoring and adjustment experiments on the Hall thruster (3) in the ground experiment; obtains the wall temperature of the ceramic wall outside the channel of the Hall thruster (3), the electron temperature and electron density of the plume region of the Hall thruster (3); In the local regulation module, all components except the gas supply unit (2) are placed in the vacuum tank (5). The power supply (1) supplies power to the Hall thruster (3), and the gas supply unit (2) provides the Hall thruster (3) with a certain flow rate of working gas. The thermocouple (6) is placed close to the outer channel wall of the Hall thruster (3) to facilitate the measurement of its wall temperature; An optical probe (7) is installed in the plume direction of the Hall thruster (3) and connected to a spectrometer (4) outside the vacuum tank via an optical fiber through a flange. The spectrometer (4) is used to measure spectral lines and calculate electron temperature and electron density. The on-orbit adjustment module includes a satellite (8), a first onboard robotic arm (9), an onboard thermocouple (10), an onboard Hall thruster (11), an onboard optical camera (12), and a second onboard robotic arm (13). The on-orbit adjustment module conducts on-orbit testing of the spaceborne Hall thruster (11); and obtains the wall temperature of the ceramic wall outside the channel of the spaceborne Hall thruster (11), the electron temperature and electron density of the plume region of the spaceborne Hall thruster (11). The on-orbit adjustment module has an on-board thermocouple (10) mounted on its first on-board manipulator (9) and an on-board optical camera (12) mounted on its second on-board manipulator (13). When the spaceborne Hall thruster (11) is running, the spaceborne first manipulator (9) extends the spaceborne thermocouple (10) to the ceramic channel wall of the spaceborne Hall thruster (11) to measure its temperature change; The onboard optical camera (12) extends to the plume direction of the onboard Hall thruster (11) via the onboard second robotic arm (13) to measure the electron temperature and electron density at this time; The data comparison module is used to compare and adjust the wall temperature, electron temperature, and electron density obtained by the on-site adjustment module and the on-orbit adjustment module, so that the three parameters of the on-orbit adjustment module are the same as the three parameters of the on-site adjustment module, thereby realizing stable control of thrust and monitoring and adjustment of the Hall thruster's on-orbit thrust.

2. A method for adjusting the on-orbit thrust adjustment device of a Hall thruster based on channel wall temperature according to claim 1, characterized in that: The method specifically includes the following steps: S1: For a certain type of Hall thruster, a channel wall temperature regulation device is built for the Hall thruster under both on-ground and on-orbit conditions. S2: During the on-site experiment, the Hall thruster (3) was started until it was running stably. The parameters of different operating conditions were adjusted to obtain the wall temperature of the ceramic wall outside the Hall thruster (3) channel, the electron temperature and electron density of the Hall thruster (3) plume region. S3: Based on the different operating parameters in S2 and the wall temperature, electron temperature and electron density, a mapping database between the local operating conditions and the three acquired data is established by fitting the data. S4: During the on-orbit experiment, the spaceborne Hall thruster (11) is in operation. When the plasma plume is stable, under the same conditions as S2, the wall temperature of the ceramic wall outside the channel of the spaceborne Hall thruster (11), the electron temperature and electron density of the plume region of the spaceborne Hall thruster (11) are obtained. S5: The on-orbit thrust of the spaceborne Hall thruster (11) is adjusted by changing the voltage, excitation current and airflow of the spaceborne Hall thruster (11); S6: The thrust of the spaceborne Hall thruster (11) is calculated by combining the electron temperature and electron density. The result of S5 is then verified to ensure the accuracy of the thrust.

3. The adjustment method according to claim 2, characterized in that: In S2, the vacuum tank (5) is first evacuated to reduce its pressure to 10. -3 Below Pa, the temperature of the outer channel wall of the Hall thruster (3) is measured using a thermocouple (6); Next, the gas supply unit 2 is started to supply the Hall thruster (3) with a certain flow rate of working gas, and the power supply (1) is started to supply the Hall thruster (3) with a certain voltage and excitation current. After the Hall thruster (3) is running stably, the thermocouple (6) is used again to measure the temperature of the outer channel wall of the Hall thruster (3) to obtain the temperature change of the outer channel wall of the Hall thruster. The plasma collision probability and the corresponding electron temperature are calculated from the temperature change. At the same time, the spectral lines at this time are measured by a spectrometer (4), and the electron density at this time is calculated. The thrust of the Hall thruster can be calculated from the electron density.

4. The adjustment method according to claim 3, characterized in that: In S4, the onboard first manipulator (9) is used to move the onboard thermocouple (10) to the outside of the satellite and to the outer channel of the onboard Hall thruster (11) of the satellite, so that the onboard thermocouple (10) is in close contact with the outer wall surface, and the wall temperature of the ceramic wall outside the channel of the onboard Hall thruster (11) is measured. The spectral lines at this time are measured by the spaceborne optical camera (12), the electron density at this time is calculated, and the thrust of the Hall thruster is calculated accordingly.

5. The adjustment method according to claim 4, characterized in that: In S5, when adjusting the thrust of the spaceborne Hall thruster (11), the voltage, excitation current and airflow of the spaceborne Hall thruster (11) are changed, while the spaceborne thermocouple (10) monitors the wall temperature of the ceramic wall outside the channel of the spaceborne Hall thruster (11). When the temperature of the outer wall is consistent with the temperature of the thrust required in the S2 ground experiment, the required thrust of the on-orbit Hall thruster can be obtained.

6. The adjustment method according to claim 5, characterized in that: In S6, the spectral lines at this time are measured by the onboard optical camera (12), the electron density at this time is calculated, and the thrust of the onboard Hall thruster (11) is calculated from the electron temperature and electron density; the result is verified to ensure the accuracy of the thrust.

7. An electronic device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that, When the processor executes the computer program, it implements the steps of the method according to any one of claims 2 to 6.

8. A computer-readable storage medium for storing computer instructions, characterized in that, When the computer instructions are executed by the processor, they implement the steps of the method according to any one of claims 2 to 6.

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