On-orbit monitoring method for thruster erosion status of high-value space platforms

Abstract

The present invention belongs to the field of plasma spectrum testing technology and provides an on-orbit monitoring method for the erosion status of a high-value space platform thruster. An on-orbit monitoring platform is constructed; an ICCD camera running on the constructed platform is used to monitor the signals of erosion products and pollutants; the ICCD camera is used to monitor the key components of the on-orbit monitoring platform to obtain information on the content of thruster erosion products and carbon atom pollutants in the key components; based on the spectral information-atomic number density database constructed on the ground, the collected spectral signals are converted into the density of erosion products and pollutants to determine the health information of the space platform thruster and the on-orbit space platform. This method is used to solve the problem that when a Hall thruster is used on a space platform, due to the inconsistency between the orbital space environment and the ground laboratory environment, special phenomena that cannot be observed in ground tests will occur, resulting in a sudden drop in the life of the thruster.

Description

Technical Field

[0001] The present invention belongs to the technical field of plasma spectrum testing, and in particular relates to an on-orbit monitoring method for the erosion state of a thruster of a high-value space platform. Background Art

[0002] In recent years, large, high-value space platforms have become a key area of ​​development in the aerospace industry. Hall thrusters, with their high thrust-to-power ratio, simple structure, and high reliability, have been widely used. The Hall thruster channel utilizes concentric annular walls made of ceramic. During operation, charged particles are accelerated along magnetic field lines by the potential difference between the anode and cathode. Some ions avoid colliding with the ceramic channel, causing channel erosion, a major factor limiting the lifespan of Hall thrusters. Typically, detailed lifespan testing is conducted on the ground during development to optimize the design for channel erosion. However, the Hall thruster plume can damage critical components of large, high-value space platforms. Furthermore, wall material sputtered by the thrusters themselves can deposit on spacecraft surfaces, solar panels, or optical components, adversely affecting the spacecraft. Therefore, the development of on-orbit monitoring is crucial and urgent.

[0003] Traditional thruster erosion life monitoring methods, such as quartz microcrystal balance, profilometer, cavity ring-down spectroscopy, laser-induced fluorescence technology, and mass spectrometry, are limited by the size of the experimental platform and the complexity of the system, which brings a heavy burden to the payload of the launch vehicle and space platform, making it difficult to achieve on-orbit application.

[0004] Therefore, how to diagnose thruster erosion products and the health status of high-value large-scale space platforms under on-orbit conditions has become a technical problem that needs to be urgently solved in this field. Summary of the Invention

[0005] The present invention provides an on-orbit monitoring method for the erosion status of a high-value space platform thruster, which is used to solve the problem that when a Hall thruster is used on a space platform, due to the inconsistency between the orbital space environment and the ground laboratory environment, special phenomena that cannot be observed in ground tests may occur. For example, the thruster may fail quickly after being launched into space, or its performance may drop sharply, resulting in a sudden reduction in the thruster life.

[0006] The present invention also provides an image processing system for processing images of on-orbit monitoring of the erosion status of thrusters of high-value space platforms.

[0007] The present invention also provides a computer-readable storage medium for storing an image processing algorithm for on-orbit monitoring of the erosion status of a thruster of a high-value space platform.

[0008] The present invention is achieved through the following technical solutions:

[0009] An on-orbit monitoring method for the erosion status of a high-value space platform thruster, the on-orbit monitoring method comprising the following steps:

[0010] Step 1: Build an on-orbit monitoring platform;

[0011] Step 2: Use the ICCD camera 5 running on the platform built in step 1 to monitor the signals of corrosion products and pollutants;

[0012] Step 3: Use the ICCD camera 5 of step 2 to monitor the key components of the on-orbit monitoring platform to obtain information on the content of thruster erosion products and carbon atomic pollutants in the key components;

[0013] Step 4: Based on the spectral information-atomic number density database built on the ground, the collected spectral signals are converted into the density of erosion products and pollutants to determine the health information of space platform thruster 2 and on-orbit space platform 3.

[0014] Furthermore, the step 1 specifically includes an experimental cabin 1, a space platform thruster 2, a space platform 3, an ICCD camera connecting mechanism 4, an ICCD camera 5 and a filter 6,

[0015] An experimental cabin 1 is placed inside the space platform 3, a space platform thruster 2 is set at the center of the space platform 3, an ICCD camera connecting mechanism 4 is set in the experimental cabin 1, an ICCD camera 5 is set on the ICCD camera connecting mechanism 4, and a filter 6 is installed on the ICCD camera 5.

[0016] Furthermore, the step 3 specifically includes converting the image signal obtained by the ICCD camera 5 into a spectral signal using an image processing algorithm according to the monitoring result, and obtaining the light intensity information of the working fluid atoms, corrosion products and pollutants.

[0017] Furthermore, step 2 is specifically as follows: the ICCD camera 5 is pushed out of the experimental cabin 1 by the mechanical arm of the ICCD camera connecting mechanism 4 and moved to the channel outlet position of the space platform thruster 2. The lens of the ICCD camera 5 is kept perpendicular to the plume direction of the space platform thruster 2, and the boron atom image signal at the ceramic channel outlet of the space platform thruster 2 is monitored, and the erosion characteristics of at least 5 identical positions are changed along the circumferential direction, and the monitoring time of each position is equal.

[0018] Furthermore, the calculated working fluid atom light intensity is first compared with the light intensity calculated after shooting with a new filter under the same position and working conditions in the ground test. If the ratio is less than 0.7, it is considered that the filter is seriously contaminated and the signal of the erosion product is no longer reliable. It is necessary to replace a filter and re-collect the signal.

[0019] Furthermore, the light intensity is calculated as follows:

[0020] The distribution of the spectral signal along the X and Y directions is Gaussian, so the spectral signal can be expressed by the following expression:

[0021] Signal = Para(1) + Para(2)×exp(-((x-Para(3)) 2 / (2×(Para(4) 2 )) + (y-Para(5)) 2 / (2×(Para(6) 2 ))));

[0022] Where Para(1) is the background noise; Para(2) is the maximum value of the image signal; Para(3) is the wavelength position of the target spectrum line; Para(4) is the half width of the target spectrum line in the X direction; Para(5) is the pixel number at the center of the target spectrum line in the Y direction; Para(6) is the width of the target spectrum line in the Y direction.

[0023] Para(1) and Para(2) are the data parameters obtained by the ICCD camera; Para(3) is the theoretical wavelength value of the target spectral line, which is a fixed value; Para(5) is the design parameter of the ICCD camera; Para(4) and Para(6) are fitting parameters, which can be determined through ground tests.

[0024] Furthermore, the density of the erosion products and contaminants in step 4 is calculated by the simultaneous formulas (1)–(3):

[0025] (1)

[0026] (2)

[0027] (3)

[0028] in, I 1, I 2 is the intensity of the metastable excitation spectrum of the working fluid atom, I 3 is the ground state direct excitation spectrum intensity of the working medium atom, n e is the electron density; n g is the ground state working fluid atomic density; n m is the atomic density of the metastable working fluid; Q is the excitation rate coefficient of the energy level, is the electron temperature T e function, is the excitation rate coefficient of the ground state working medium to energy level 1, is the excitation rate coefficient of the ground state working medium to energy level 2, is the excitation rate coefficient of the ground state working medium to energy level 3, is the excitation rate coefficient of the metastable working medium excited to energy level 1, is the excitation rate coefficient of the metastable working medium excited to energy level 2, is the excitation rate coefficient of the metastable working medium excited to energy level 3, β 1 is the first branch ratio, β 2 is the second branch ratio, β 3 is the third branch ratio.

[0029] Furthermore, the two line ratio relations (4)–(5) are constructed as follows:

[0030] (4)

[0031] (5)

[0032] The equations of formula (4) and (5) have only two unknowns. T e and n m / n g , solve the two equations for the two unknowns and obtain the electron temperature T e .

[0033] Further,

[0034] (6)

[0035] (7)

[0036] Spectral line ratio R The relationship (8)

[0037] (8)

[0038] For formulas (6)–(7), β B is the branching ratio of the erosion products, β Xe is the branching ratio of Xe atoms, Q B is the excitation rate coefficient of the erosion product energy level, Q Xe is the excitation rate coefficient of the Xe atom’s inaccessible energy level, IB is the spectral line intensity of the corrosion product monitored by the spectrometer, I Xe is the Xe atomic spectral line intensity monitored by the spectrometer, is the light intensity information obtained after the spectrometer measures the image signal based on step 4, which is a known value, or is the spectral line intensity of other ground states directly excited.

[0039] An image processing system includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the above method is implemented.

[0040] A computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the image processing method is implemented.

[0041] The beneficial effects of the present invention are:

[0042] The present invention utilizes the characteristics of simple system and good flexibility of the optical monitoring platform with ICCD camera as the core, and designs an optical monitoring system that can be used for high-value platforms on orbit. It realizes the online monitoring of the thruster erosion status and the health characteristics of high-value platforms on orbit. Compared with traditional methods, this method can obtain on-orbit data, which helps to understand the inconsistency between the earth and the sky, thereby providing data support for the optimized design of thrusters and space platforms.

[0043] The present invention explores the adaptability of the detection device to the space environment. The performance changes of the optical monitoring system in the space environment obtained can be used to guide the development of diagnostic equipment specifically for deep space exploration missions. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 It is a front view of the present invention.

[0045] Figure 2 It is a side view of the present invention.

[0046] Figure 3 It is a flow chart of the method of the present invention.

[0047] Reference numerals: 1-experimental cabin, 2-space platform thruster, 3-space platform, 4-ICCD camera connecting mechanism, 5-ICCD camera, 6-filter. DETAILED DESCRIPTION

[0048] In the following description, specific details such as specific system structures and technologies are provided for illustration rather than limitation to facilitate a thorough understanding of the embodiments of the present application. However, it should be clear to those skilled in the art that the present application may be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to avoid obstructing the description of the present application with unnecessary details.

[0049] It will be understood that when used in this specification and the appended claims, the term "comprising" indicates the presence of described features, integers, steps, operations, elements and / or components, but does not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or groups thereof.

[0050] It should also be understood that the terms used in this specification are only for the purpose of describing specific embodiments and are not intended to limit the present application. As used in this specification and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms unless the context clearly indicates otherwise.

[0051] The following is attached to this application specification Figure 1-3 , clearly and completely describe the technical solutions in the embodiments of this application. Obviously, the described embodiments are only part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of this application.

[0052] In the following description, many specific details are set forth to facilitate a full understanding of the present application. However, the present application may also be implemented in other ways different from those described herein. Those skilled in the art may make similar generalizations without violating the connotation of the present application. Therefore, the present application is not limited to the specific embodiments disclosed below.

[0053] Example 1

[0054] This embodiment provides an on-orbit monitoring method for the erosion status of a thruster of a high-value space platform. The on-orbit monitoring method includes the following steps:

[0055] Step 1: Build an on-orbit monitoring platform;

[0056] Step 2: Use the ICCD camera 5 running on the platform built in step 1 to monitor the signals of corrosion products and pollutants;

[0057] Step 3: Use the ICCD camera 5 in step 2 to monitor the key components of the on-orbit monitoring platform to obtain information on the content of thruster erosion products and carbon atomic pollutants in the key components;

[0058] Step 4: Based on the spectral information-atomic number density database built on the ground, the collected spectral signals are converted into the density of erosion products and pollutants to determine the health information of space platform thruster 2 and on-orbit space platform 3.

[0059] Specifically, when the filter performance drops by more than a 20% threshold, the filter assembly at the front end of the ICCD is used to replace the filter.

[0060] Furthermore, the on-orbit monitoring platform constructed in step 1 specifically includes an experimental cabin 1, a space platform thruster 2, a space platform 3, an ICCD camera connection mechanism 4, an ICCD camera 5, the ICCD camera 5 including a matching cooling and protection device and a filter 6, and the ICCD camera connection mechanism 4 includes a robotic arm and a platform for fixing the camera;

[0061] An experimental cabin 1 is placed inside the space platform 3, a space platform thruster 2 is set at the center of the space platform 3, an ICCD camera connecting mechanism 4 is set in the experimental cabin 1, an ICCD camera 5 is set in the ICCD camera connecting mechanism 4, and a filter 6 is installed on the ICCD camera 5.

[0062] Furthermore, step 2 is specifically as follows: the ICCD camera 5 is pushed out of the experimental cabin 1 by the mechanical arm of the ICCD camera connecting mechanism 4 and moved to the channel outlet position of the space platform thruster 2. The lens of the ICCD camera 5 is kept perpendicular to the plume direction of the space platform thruster 2, and the boron atom image signal at the ceramic channel outlet of the space platform thruster 2 is monitored, and the erosion characteristics of at least 5 identical positions are changed along the circumferential direction, and the monitoring time of each position is equal.

[0063] The data collection interval and the duration of signal acquisition at each location are determined by the task requirements. The one-hour interval mentioned in this implementation example is for reference only. Before each erosion product image signal acquisition, image signals of the working fluid atoms must be acquired, and the acquisition duration must be consistent with the duration of the erosion product signal acquisition. To avoid background light interference, image signals at different locations must be compared to comprehensively determine the image information of erosion products and contaminants.

[0064] Furthermore, the step 3 specifically includes converting the image signal obtained by the ICCD camera 5 into a spectral signal using an image processing algorithm according to the monitoring result, and obtaining the light intensity information of the working fluid atoms, corrosion products and pollutants.

[0065] Signal processing:

[0066] The ICCD spectrometer monitoring results are analyzed using image processing algorithms to obtain light intensity signals. By comparing them with the light intensity-erosion rate database constructed by ground tests, the density of erosion products can be quickly determined and the current erosion status can be evaluated.

[0067] Furthermore, the calculated working fluid atom light intensity is first compared with the light intensity calculated after shooting with a new filter under the same position and working conditions in the ground test. If the ratio is less than 0.7, it is considered that the filter is seriously contaminated and the signal of the erosion product is no longer reliable. It is necessary to replace a filter and re-collect the signal.

[0068] Furthermore, the light intensity is calculated as follows:

[0069] The distribution of the spectral signal along the X and Y directions is Gaussian, so the spectral signal can be expressed by the following expression:

[0070] Signal = Para(1) + Para(2)×exp(-((x-Para(3)) 2 / (2×(Para(4) 2 )) + (y-Para(5)) 2 / (2×(Para(6) 2 ))));

[0071] Where Para(1) is the background noise; Para(2) is the maximum value of the image signal; Para(3) is the wavelength position of the target spectrum line; Para(4) is the half width of the target spectrum line in the X direction; Para(5) is the pixel number at the center of the target spectrum line in the Y direction; Para(6) is the width of the target spectrum line in the Y direction.

[0072] Para(1) and Para(2) are the data parameters obtained by the ICCD camera; Para(3) is the theoretical wavelength value of the target spectrum line, which is a fixed value; Para(5) is the design parameter of the ICCD camera; Para(4) and (6) are fitting parameters, which can be determined through ground tests.

[0073] Furthermore, the density of the erosion products and pollutants in step 4 is calculated by the simultaneous formulas (1)–(3):

[0074] (1)

[0075] (2)

[0076] (3)

[0077] in, I 1, I 2,I 3 is the emission line intensity of the three working fluid atoms, which is the intensity information obtained after the spectrometer measures the image signal based on step 4. It is a known value and its selection is based on I 1, I 2 is the intensity of the metastable excitation spectrum of the working fluid atom, I 3 is the ground state direct excitation spectrum intensity of the working medium atom, n e is the electron density; n g is the ground state working fluid atomic density; n m is the atomic density of the metastable working fluid; Q is the excitation rate coefficient of the energy level, is the electron temperature T e function, is the excitation rate coefficient of the ground state working medium to energy level 1, is the excitation rate coefficient of the ground state working medium to energy level 2, is the excitation rate coefficient of the ground state working medium to energy level 3, is the excitation rate coefficient of the metastable working medium excited to energy level 1, is the excitation rate coefficient of the metastable working medium excited to energy level 2, is the excitation rate coefficient of the metastable working medium excited to energy level 3, β 1 is the first branch ratio, β 2 is the second branch ratio, β 3 is the third branch ratio.

[0078] Furthermore, a method for on-orbit monitoring of the erosion state of a high-value space platform thruster is proposed, which constructs two spectral line ratio equations (4)–(5) as follows:

[0079] (4)

[0080] (5)

[0081] The equations of formula (4) and (5) have only two unknowns. T e and n m / n g , solve the two equations for the two unknowns and obtain the electron temperature T e ;

[0082] (6)

[0083] (7)

[0084] Spectral line ratio R The relationship (8)

[0085] (8)

[0086] For formulas (6)–(7), β B is the branching ratio of the erosion product, β Xe is the branching ratio of Xe atoms, Q B is the excitation rate coefficient of the erosion product energy level, Q Xe is the excitation rate coefficient of the Xe atom’s inaccessible energy level, I B is the spectral line intensity of the corrosion product monitored by the spectrometer, I Xe is the Xe atomic spectral line intensity monitored by the spectrometer, and is the light intensity information obtained after the spectrometer measures the image signal based on the calculation in step 4. It can be considered as a known value, specifically the 828.0 nm spectral line intensity, or the intensity of other spectral lines directly excited by the ground state. These two parameters are known values; n B is the boron atomic density, n Xe is the ground state xenon atomic density;

[0087] Combining equations (6)–(7), we construct a line ratio relationship (8). For equation (8), I B and I Xe known; T e is the result of calculation of formula (4)–(5), so Q known; n Xe Through simulation, it is accurately obtained that the only unknown quantity in formula (8) is the boron atom density n B , and the solution can be obtained by substituting the known quantities.

[0088] Example 3

[0089] An embodiment of the present invention provides an image processing system comprising a memory, a processor, and a computer program stored in the memory and executable on the processor. The memory is used to store software programs and modules, and the processor executes the software programs and modules stored in the memory to perform various functional applications and data processing. The memory and processor are connected via a bus. Specifically, the processor implements any of the steps in the first embodiment above by executing the computer program stored in the memory.

[0090] It should be understood that in the embodiments of the present invention, the processor referred to may be a central processing unit (CPU), and the processor may also be other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor may be a microprocessor or any conventional processor, etc.

[0091] The memory may include a read-only memory, a flash memory, and a random access memory, and provides instructions and data to the processor. A portion or all of the memory may also include a non-volatile random access memory.

[0092] As can be seen from the above, the image processing system provided by the embodiments of the present invention can implement the self-image processing method described in Example 1 by running a computer program to obtain light intensity signals of working fluid atoms, erosion products, and contaminants, as well as the density of trace products, for use in determining the erosion status of the thruster channel and the health of the space platform. By obtaining the density of erosion products and contaminants, not only can on-orbit data be obtained to help understand the inconsistency between the Earth and the sky, but the performance changes of the optical monitoring system in the space environment can also be used to guide the development of diagnostic equipment specifically for deep space exploration missions, thereby determining the erosion status of the thruster channel and the health of the space platform.

[0093] It should be understood that if the above-mentioned integrated modules / units are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the present invention can also implement all or part of the processes in the above-mentioned method embodiments by instructing the relevant hardware through a computer program. The above-mentioned computer program can be stored in a computer-readable storage medium. When executed by a processor, the computer program can implement the steps of each of the above-mentioned method embodiments. The above-mentioned computer program includes computer program code, which can be in source code form, object code form, executable file, or some intermediate form. The above-mentioned computer-readable medium can include: any entity or device capable of carrying the above-mentioned computer program code, recording medium, USB flash drive, mobile hard drive, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signal, telecommunication signal, and software distribution medium. It should be noted that the content contained in the above-mentioned computer-readable storage medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction.

[0094] The above description of the disclosed embodiments is intended to enable one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be readily apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not limited to the embodiments shown herein but is intended to conform to the widest scope consistent with the principles and novel features disclosed herein.

[0095] Those skilled in the art can clearly understand that, for the convenience and brevity of description, only the division of the above-mentioned functional units and modules is used as an example for illustration. In actual applications, the above-mentioned functions can be distributed and completed by different functional units and modules as needed, that is, the internal structure of the above-mentioned device can be divided into different functional units or modules to complete all or part of the functions described above. The functional units and modules in the embodiment can be integrated into one processing unit, or each unit can exist physically alone, or two or more units can be integrated into one unit. The above-mentioned integrated unit can be implemented in the form of hardware or in the form of software functional units. In addition, the specific names of the functional units and modules are only for the convenience of distinguishing each other, and are not used to limit the scope of protection of the present invention. The specific working process of the units and modules in the above-mentioned system can refer to the corresponding process in the aforementioned method embodiment, and will not be repeated here.

[0096] It should be noted that the methods and detailed examples provided in the above embodiments can be combined with the devices and equipment provided in the embodiments, and references can be made to each other, and no further details will be given.

[0097] Those skilled in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professionals and technicians can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of the present invention.

[0098] In the embodiments provided by the present invention, it should be understood that the disclosed apparatus / terminal equipment and methods can be implemented in other ways. For example, the apparatus / device embodiments described above are merely illustrative. For example, the division of the modules or units described above is merely a logical functional division. In actual implementation, other division methods may be used. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not implemented.

[0099] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or make equivalent replacements for some of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be included in the scope of protection of the present invention.

Claims

1. A method for on-orbit monitoring of the erosion status of a high-value space platform thruster, characterized in that: The on-orbit monitoring method comprises the following steps: Step 1: Build an on-orbit monitoring platform; Step 2: Monitor the signals of erosion products and contaminants using the ICCD camera (5) running on the platform built in step 1; Step 3: Use the ICCD camera (5) of step 2 to monitor the key components of the on-orbit monitoring platform to obtain information on the content of thruster erosion products and carbon atomic pollutants in the key components; Step 4: Based on the spectral information-atomic number density database built on the ground, the collected spectral signals are converted into the density of erosion products and pollutants to determine the health information of the space platform thruster (2) and the on-orbit space platform (3); The step 1 specifically includes an experimental cabin (1), a space platform thruster (2), a space platform (3), an ICCD camera connecting mechanism (4), an ICCD camera (5) and a filter (6), An experimental cabin (1) is placed inside the space platform (3), a space platform thruster (2) is provided at the center of the space platform (3), an ICCD camera connection mechanism (4) is provided in the experimental cabin (1), an ICCD camera (5) is provided on the ICCD camera connection mechanism (4), and a filter (6) is installed on the ICCD camera (5); Specifically, the step 2 comprises the following steps: the ICCD camera (5) is pushed out of the experimental cabin (1) by the mechanical arm of the ICCD camera connection mechanism (4), and is moved to the channel outlet position of the space platform thruster (2), the lens of the ICCD camera (5) is kept perpendicular to the plume direction of the space platform thruster (2), the boron atom image signal at the ceramic channel outlet of the space platform thruster (2) is monitored, and the erosion characteristics of at least five identical positions are replaced along the circumferential direction, and the monitoring time of each position is equal; First, the calculated working fluid atom light intensity is compared with the light intensity calculated after shooting with a new filter at the same position and under the same working conditions in the ground test. If the ratio is less than 0.7, it is considered that the filter is seriously contaminated and the signal of the erosion product is no longer reliable. It is necessary to replace a filter and re-acquire the signal.

2. The on-orbit monitoring method for the erosion status of a high-value space platform thruster according to claim 1, characterized in that: Specifically, step 3 is to convert the image signal obtained by the ICCD camera (5) into a spectral signal using an image processing algorithm according to the monitoring results, and obtain light intensity information of the working fluid atoms, corrosion products and pollutants.

3. The on-orbit monitoring method for the erosion status of a high-value space platform thruster according to claim 1, characterized in that: The light intensity is calculated as follows: The distribution of the spectral signal along the X and Y directions is Gaussian, so the spectral signal can be expressed by the following expression: Signal = Para(1) + Para(2)×exp(-((x-Para(3)) 2 / (2×(For(4) 2 )) + (and-For(5)) 2 / (2×(For(6) 2 )))); Where Para(1) is the background noise; Para(2) is the maximum value of the image signal; Para(3) is the wavelength position of the target spectrum line; Para(4) is the half width of the target spectrum line in the X direction; Para(5) is the pixel number at the center of the target spectrum line in the Y direction; Para(6) is the width of the target spectrum line in the Y direction. Para(1) and Para(2) are the data parameters obtained by the ICCD camera; Para(3) is the theoretical wavelength value of the target spectral line, which is a fixed value; Para(5) is the design parameter of the ICCD camera; Para(4) and Para(6) are fitting parameters, which can be determined through ground tests.

4. The on-orbit monitoring method for the erosion status of a high-value space platform thruster according to claim 1, characterized in that: The density of the erosion products and pollutants in step 4 is calculated by the simultaneous formulas (1)–(3): （1） （2） （3） in, I 1, I 2 is the intensity of the metastable excitation spectrum of the working fluid atom, I 3 is the ground state direct excitation spectrum intensity of the working medium atom, n e is the electron density; n g is the ground state working fluid atomic density; n m is the atomic density of the metastable working fluid; Q is the excitation rate coefficient of the energy level, is the electron temperature T e function, is the excitation rate coefficient of the ground state working medium to energy level 1, is the excitation rate coefficient of the ground state working medium to energy level 2, is the excitation rate coefficient of the ground state working medium to energy level 3, is the excitation rate coefficient of the metastable working medium excited to energy level 1, is the excitation rate coefficient of the metastable working medium excited to energy level 2, is the excitation rate coefficient of the metastable working medium excited to energy level 3, β 1 is the first branch ratio, β 2 is the second branch ratio, β 3 is the third branch ratio.

5. The on-orbit monitoring method for the erosion status of a high-value space platform thruster according to claim 4, characterized in that: The two line ratio relations (4)–(5) are constructed as follows: （4） （5） There are only two unknowns in the equations (4) and (5). T e and n m / n g , solve the two equations for the two unknowns and obtain the electron temperature T e ; （6） （7） Spectral line ratio R The relationship (8) （8） For formulas (6)–(7), β B is the branching ratio of the erosion product, β Xe is the branching ratio of Xe atoms, Q B is the excitation rate coefficient of the erosion product energy level, Q Xe is the excitation rate coefficient of the Xe atom’s inaccessible energy level, I B is the spectral line intensity of the corrosion product monitored by the spectrometer, I Xe is the Xe atomic spectral line intensity monitored by the spectrometer, is the light intensity information obtained after the spectrometer measures the image signal based on step 4, which is a known value, or the spectral line intensity directly excited by other ground states, is the ground-state xenon atomic density.

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