Hall thruster oscillation photoelectric joint monitoring device and method

Abstract

The device and method for the combined photoelectric monitoring of Hall thruster oscillations relate to the field of electric propulsion technology. The problems of errors in the existing monitoring methods for electric propulsion plume thrust fluctuations, difficulty in collecting spectral data, and high calculation costs are solved. The device includes: a plane, a Hall thruster, a two-dimensional data acquisition device, a probe holder, a Faraday probe, an RPA probe, a thruster plume, and a holder; the Hall thruster is fixed on the plane, the Hall thruster propels to form a thruster plume, and the two-dimensional data acquisition device is fixed on the plane through a holder; the probe array composed of the Faraday probe and the RPA probe is fixed on the probe holder. The present invention is applied to the field of electric thruster monitoring.

Description

Technical Field

[0001] The present invention relates to the field of electric propulsion technology, and in particular to a Hall thruster oscillation photoelectric combined monitoring device. Background Art

[0002] With the launch of the StarNet constellation project, the demand for mass production, efficient operation and high-accuracy electric propulsion plume detection and evaluation technology has become particularly urgent. During the on-orbit operation of electric thrusters, the monitoring of thrust fluctuations is crucial. By monitoring the thrust fluctuations, the working state of the electric thrusters can be inferred and the plume divergence angle can be calculated to avoid the problem of excessive contamination of solar panels. Accurate monitoring of the thrust fluctuations of the electric propulsion plume can provide important information for the successful implementation of space missions. It not only helps researchers understand the working state of the thrusters, but also helps to evaluate the reliability and performance of mass-produced thrusters when they oscillate or fluctuate.

[0003] The monitoring technologies for electric propulsion plume thrust fluctuations are mainly divided into two types: spectroscopy and GPS detection. Spectroscopy infers thrust fluctuations by analyzing the spectrum emitted by atomic transitions. By analyzing and calculating the density ratio of monovalent and divalent ions in the plasma, the thrust fluctuations and the value of the plume divergence angle can be obtained; while GPS on-orbit detection uses the GPS system to monitor thrust fluctuations. Over a period of time, by measuring the position and velocity changes of the spacecraft, the corresponding momentum changes can be inferred, and then the thrust fluctuations can be obtained by calculating the momentum changes.

[0004] The accuracy of GPS measurement methods in space is lower than that in terrestrial environments, which may cause errors. Even under the protection of the Earth's magnetosphere, the solar wind may still affect satellites and spacecraft, causing orbital positions to shift. In space, especially for spacecraft at low orbital altitudes, space debris poses a major threat. Once an impact occurs, it may affect the measurement results of the propulsion plume. In addition, electric propulsion systems may be affected by mechanical vibrations, which may cause errors in thrust measurements.

[0005] Although spectral detection avoids the drawbacks of GPS detection methods to a certain extent, the spectral data collected in the space environment may be complex, and processing this data requires a high degree of algorithm and computing power. Due to the particularity of the space environment, the challenges of data processing may increase and fail to meet the low cost requirements of on-orbit. Summary of the invention

[0006] Aiming at the problems that the existing monitoring method of electric propulsion plume thrust fluctuation has errors, spectral data is difficult to collect, and the calculation cost is high, the present invention proposes a Hall thruster oscillation photoelectric joint monitoring device, the scheme includes:

[0007] A Hall thruster oscillation optoelectronic combined monitoring device, the device comprising:

[0008] Planar, Hall thrusters, 2D data acquisition devices, probe holders, Faraday probes, RPA probes, thruster plumes and holders;

[0009] The Hall thruster is fixed on a plane, the Hall thruster propels to form a thruster plume, and the two-dimensional data acquisition device is fixed on the plane through a bracket; the probe array composed of the Faraday probe and the RPA probe is fixed on the probe bracket.

[0010] Furthermore, a preferred embodiment is proposed, in which the number of the Faraday probes and the number of the RPA probes are the same.

[0011] Furthermore, a preferred embodiment is proposed, in which the Faraday probes and the RPA probes form an alternating array and are evenly distributed on a probe holder, and the probe holder is a flat plate structure.

[0012] Furthermore, a preferred embodiment is proposed, wherein the two-dimensional data acquisition device is a camera.

[0013] Based on the same inventive concept, the present invention also proposes a Hall thruster oscillation photoelectric joint monitoring method, which is implemented based on the above-mentioned Hall thruster oscillation photoelectric joint monitoring device, and the method includes:

[0014] S1: Turn on the Hall thruster during the grounding process, introduce xenon gas, and obtain the voltage flowing through the Hall thruster under normal working conditions With current ;

[0015] S2: After the Hall thruster works stably, the probe array obtains the single-charged ion current, double-charged ion current, plume divergence angle and ion energy at different positions of the thruster plume under normal working conditions to obtain ion energy distribution data, and uploads the ion energy distribution data to the terminal;

[0016] S3: Start the two-dimensional data acquisition device to measure the thruster plume image in real time, upload the measurement data to the host computer, and the host computer analyzes and obtains the plume electron temperature The temperature distribution and ion density of the plume are obtained The distribution data is uploaded to the terminal;

[0017] S4: Process the data obtained in step S2 and step S3 to obtain the real-time situation of the thrust oscillation of the Hall thruster.

[0018] Furthermore, a preferred method is proposed, wherein step S4 comprises:

[0019] Get the ion current:

[0020]

[0021] in, is the single ion current, is the dual ion current;

[0022] Obtain divergence angle correction factor according to ion current, plume divergence angle and ion density, and correct the divergence angle;

[0023] The thrust of the Hall thruster is obtained according to the divergence angle correction factor and thrust correction processing;

[0024] The real-time situation of the Hall thruster thrust oscillation is determined according to the Hall thruster thrust.

[0025] Furthermore, a preferred embodiment is proposed, wherein the divergence angle correction factor is:

[0026]

[0027] Where r is the thruster radius, is the ion density, is the plume divergence angle at different positions, is the ion current.

[0028] Furthermore, a preferred method is proposed, wherein the thrust of the Hall thruster is obtained according to the divergence angle correction factor and the thrust correction processing, specifically:

[0029]

[0030] in, is the thrust correction factor, is the accelerating voltage, is the mass flow rate of xenon gas, and vt is the velocity of ions.

[0031] Furthermore, a preferred embodiment is proposed, wherein the thrust correction factor The divergence correction factor and doubly charged ion correction factor The product of gets:

[0032] .

[0033] Furthermore, a preferred embodiment is proposed, wherein the double-charged ion correction factor for:

[0034] .

[0035] The present invention is beneficial in that:

[0036] The present invention solves the problems of errors in the existing monitoring methods for electric propulsion plume thrust fluctuations, difficulty in collecting spectral data and high calculation costs.

[0037] The Hall thruster oscillation optoelectronic joint monitoring device proposed in the present invention can directly obtain electrical parameters by using the joint monitoring of Hall thrusters, Faraday probes and RPA probes, reducing the dependence on complex spectral data, thereby possibly reducing the computing cost. The use of Hall thrusters and probe arrays can more directly obtain data related to the thruster plume, avoiding the complex spectral data acquisition process and simplifying the design and use of the monitoring device. The accuracy of thrust fluctuations may be improved through the joint monitoring of multiple sensors. Faraday probes and RPA probes can provide additional electromagnetic information, which helps to more fully understand the working status of the thruster.

[0038] The Hall thruster in the Hall thruster oscillation optoelectronic joint monitoring device proposed in the present invention generates an electromagnetic field through the Hall effect, which is used to propel and form a thruster plume. The Hall effect is a physical phenomenon based on magnetic fields and electric currents. The Faraday probe is used to measure the electric field strength, while the RPA (Retarding Potential Analyzer) probe is used to measure the ion energy distribution in the plasma. The probe array composed of the two can provide detailed information about the plasma state. Through a two-dimensional data acquisition device, relevant information about the thruster plume, such as flow field distribution, velocity, etc., can be obtained. The device described in the present invention solves the problems of difficult spectral data acquisition and high computational cost in the traditional electric propulsion plume thrust fluctuation monitoring method. By introducing the combined monitoring of Hall thrusters, Faraday probes and RPA probes, it is intended to simplify the data acquisition process, improve the accuracy of thrust fluctuation monitoring, and reduce computational costs.

[0039] The photoelectric joint monitoring method for Hall thruster oscillation proposed in the present invention combines multi-dimensional data such as current, ion energy distribution, plume image, electron temperature and ion density, and can comprehensively and deeply monitor the working state of the Hall thruster. By real-time acquisition and uploading of various data to the terminal, the host computer can timely analyze the plume characteristics, electron temperature and ion density of the thruster, and realize real-time monitoring of the thrust oscillation of the Hall thruster. By processing the acquired multi-dimensional data, the real-time situation of the thrust oscillation of the Hall thruster can be comprehensively analyzed to provide timely feedback and adjustment for the thruster in operation. Through joint multi-dimensional data monitoring, the working state of the Hall thruster, especially the situation of thrust oscillation, is fully understood. Through real-time monitoring and comprehensive analysis, timely feedback on the performance of the thruster is provided to ensure that the thruster operates stably within the normal working range. The purpose of this method is to improve the accuracy and real-time performance of monitoring in order to optimize and improve the working performance of the Hall thruster.

[0040] The present invention is applied to the field of electric thruster monitoring. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 Schematic diagram of the Hall thruster oscillation optoelectronic combined monitoring device according to the first embodiment, wherein 1 is a plane, 2 is a Hall thruster, 3 is a two-dimensional data acquisition device, 4 is a probe bracket, 5 is a Faraday probe, 6 is an RPA probe, 7 is a thruster plume, and 8 is a bracket;

[0042] Figure 2 This is a flow chart of the Hall thruster oscillation photoelectric joint monitoring method described in Implementation Mode 5. DETAILED DESCRIPTION

[0043] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments.

[0044] Implementation method 1, see Figure 1 The Hall thruster oscillation optoelectronic combined monitoring device described in this embodiment includes:

[0045] Plane 1, Hall thruster 2, two-dimensional data acquisition device 3, probe bracket 4, Faraday probe 5, RPA probe 6, thruster plume 7 and bracket 8;

[0046] The Hall thruster 2 is fixed on the plane 1 , and the Hall thruster 2 propels to form a thruster plume 7 . The two-dimensional data acquisition device 3 is fixed on the plane 1 through a bracket 8 . The probe array composed of the Faraday probe 5 and the RPA probe 6 is fixed on the probe bracket 4 .

[0047] The device described in this embodiment can directly obtain electrical parameters by using the combined monitoring of Hall thrusters, Faraday probes and RPA probes, reducing the reliance on complex spectral data, thereby possibly reducing the computational cost. The use of Hall thrusters and probe arrays can more directly obtain data related to the thruster plume, avoiding the complex spectral data acquisition process and simplifying the design and use of the monitoring device. The accuracy of thrust fluctuations may be improved through the combined monitoring of multiple sensors. Faraday probes and RPA probes can provide additional electromagnetic information, which helps to more fully understand the working status of the thruster.

[0048] The Hall thruster in the device described in this embodiment generates an electromagnetic field through the Hall effect, which is used to propel and form a thruster plume. The Hall effect is a physical phenomenon based on magnetic fields and electric currents. The Faraday probe is used to measure the electric field strength, while the RPA (Retarding Potential Analyzer) probe is used to measure the ion energy distribution in the plasma. The probe array composed of the two can provide detailed information about the plasma state. Through a two-dimensional data acquisition device, relevant information about the thruster plume, such as flow field distribution, velocity, etc., can be obtained. The device described in this embodiment solves the problems of difficult spectral data acquisition and high computational cost in traditional electric propulsion plume thrust fluctuation monitoring methods. By introducing the combined monitoring of Hall thrusters, Faraday probes and RPA probes, it is intended to simplify the data acquisition process, improve the accuracy of thrust fluctuation monitoring, and reduce computational costs.

[0049] Embodiment 2: This embodiment further limits the Hall thruster oscillation optoelectronic joint monitoring device described in Embodiment 1, and the number of the Faraday probes 5 and the RPA probes 6 are the same.

[0050] The same number of Faraday probes and RPA probes described in this embodiment can achieve more uniform monitoring of plasma parameters and improve the overall perception of the electromagnetic environment. The same number of Faraday probes and RPA probes can make data analysis easier, reduce the complexity caused by different numbers of probes, and make the monitoring results easier to understand. The same number of probes can improve the repeatability of the experiment, because the same number of probes can provide consistent monitoring data in different experiments, which helps the stability of the results.

[0051] In this embodiment, the Faraday probe is used to measure the electric field strength, and the RPA probe is used to measure the ion energy distribution in the plasma. By using the same number of these two probes, the electric field and plasma parameters can be monitored more comprehensively, providing more detailed data. The electromagnetic field generated by the Hall thruster is used to propel and form a thruster plume. The characteristics of the plume affect the behavior of the plasma, and the probe array obtains information about thrust fluctuations by monitoring these characteristics. This embodiment further optimizes the first embodiment by matching the number of Faraday probes and RPA probes to achieve more uniform and comprehensive electromagnetic environment monitoring. Such a design helps to improve the accuracy and stability of monitoring, making the device more reliable in practical applications.

[0052] Embodiment 3: This embodiment further limits the Hall thruster oscillation optoelectronic joint monitoring device described in Embodiment 2. The Faraday probe 5 and the RPA probe 6 form an alternating array and are evenly distributed on the probe holder 4. The probe holder 4 is a flat plate structure.

[0053] In this embodiment, the alternating array design of Faraday probes and RPA probes can more effectively cover the entire monitoring area and improve the comprehensiveness and uniformity of monitoring. The probe holder adopts a flat structure, which helps to evenly distribute the probes. This design can reduce the difference in the impact of probes at different positions on the plasma and improve the accuracy of the measurement. The probe holder with a flat structure is relatively simple, easy to manufacture and install, and helps to improve the manufacturability and maintainability of the device.

[0054] The alternating Faraday probes and RPA probes can monitor the electric field and plasma parameters alternately. This design can obtain more comprehensive information about the electromagnetic environment at different locations, thereby better understanding the characteristics of thrust fluctuations. The flat-plate structure of the probe holder enables the probes to be evenly distributed throughout the monitoring area. This helps to reduce the non-uniformity caused by spatial position and ensure that the measurement results are more reliable and accurate. The electric propulsion Hall thruster oscillation optoelectronic joint monitoring device is further optimized through the design of alternating arrays and flat-plate structures. This design improves the comprehensiveness, uniformity and reliability of monitoring, making the device more practical in actual applications.

[0055] Embodiment 4: This embodiment further limits the Hall thruster oscillation optoelectronic combined monitoring device described in Embodiment 1, and the two-dimensional data acquisition device 3 is a camera.

[0056] In this embodiment, a camera is used as a two-dimensional data acquisition device, which can provide high-resolution image data, making the monitored optical information more detailed and clear. The camera can observe the Hall thruster at different angles and directions to obtain multi-angle information. This is crucial for a comprehensive understanding of the oscillation characteristics and optical parameters of the thruster. The camera can usually collect image data in real time, realize real-time monitoring of the Hall thruster status, and help to respond immediately to possible problems or fluctuations.

[0057] The camera collects images of the surrounding environment through optical sensors. In Hall thruster monitoring, the camera captures optical signals on the thruster surface, including visual changes that may be caused by vibrations. The collected image data can be processed by image processing and analysis algorithms to extract information about the state of the Hall thruster. The camera is used as a two-dimensional data acquisition device to improve the accuracy and sensitivity of optical monitoring. By obtaining high-resolution image data, a more comprehensive understanding of the vibration of the Hall thruster can be obtained, and the monitoring and analysis of the thruster state can be further improved. In practical applications, CCD cameras or other commercial cameras can be used.

[0058] Implementation method 5: See Figure 2The present embodiment describes the Hall thruster oscillation optoelectronic combined monitoring method described in the present embodiment, which is implemented based on the Hall thruster oscillation optoelectronic combined monitoring device described in the first embodiment, and the method includes:

[0059] S1: Turn on Hall thruster 2 during the grounding process, introduce xenon gas, and obtain the voltage flowing through Hall thruster 2 under normal working conditions. With current ;

[0060] S2: After the Hall thruster 2 works stably, the probe array obtains the single-charged ion current, double-charged ion current, plume divergence angle and ion energy at different positions of the thruster plume 7 under normal working conditions to obtain ion energy distribution data, and uploads the ion energy distribution data to the terminal;

[0061] S3: Start the two-dimensional data acquisition device 3 to measure the thruster plume 7 image in real time, upload the measurement data to the host computer, and the host computer analyzes and obtains the plume electron temperature The temperature distribution and ion density of the plume are obtained The distribution data is uploaded to the terminal;

[0062] S4: Process the data obtained in step S2 and step S3 to obtain the real-time situation of the thrust oscillation of the Hall thruster 2.

[0063] The method described in this embodiment combines multi-dimensional data such as current, ion energy distribution, plume image, electron temperature and ion density, and can comprehensively and deeply monitor the working status of the Hall thruster. By real-time acquisition and uploading of various data to the terminal, the host computer can timely analyze the plume characteristics, electron temperature and ion density of the thruster, and realize real-time monitoring of the thrust oscillation of the Hall thruster. By processing the multi-dimensional data obtained in steps S2 and S3, the real-time situation of the thrust oscillation of the Hall thruster can be comprehensively analyzed to provide timely feedback and adjustment for the thruster in operation.

[0064] Specific:

[0065] In S1, by measuring the current and voltage flowing through the Hall thruster, the electrical performance data of the thruster under normal working conditions can be obtained. The single-charged ion current, double-charged ion current, plume divergence angle and ion energy at different positions of the plume are obtained through the probe array in S2, so as to obtain the ion energy distribution data. The thruster plume image is measured in real time by the two-dimensional data acquisition device in S3, uploaded to the host computer for analysis, and the temperature distribution and ion density distribution data of the plume are obtained. In S4, the data obtained by S2 and S3 are processed, and the real-time situation of the thrust oscillation of the Hall thruster is obtained by analysis. This embodiment comprehensively understands the working state of the Hall thruster, especially the situation of thrust oscillation, by combining multi-dimensional data monitoring. Through real-time monitoring and comprehensive analysis, timely feedback on the performance of the thruster is provided to ensure that the thruster operates stably within the normal working range. The purpose of this method is to improve the accuracy and real-time performance of monitoring in order to optimize and improve the working performance of the Hall thruster.

[0066] Embodiment 6: This embodiment further limits the Hall thruster oscillation photoelectric joint monitoring method described in Embodiment 5, and the step S4 includes:

[0067] Get the ion current:

[0068]

[0069] in, is the single ion current, is the dual ion current;

[0070] Obtain divergence angle correction factor according to ion current, plume divergence angle and ion density, and correct the divergence angle;

[0071] The thrust of the Hall thruster is obtained according to the divergence angle correction factor and thrust correction processing;

[0072] The real-time situation of the Hall thruster thrust oscillation is determined according to the Hall thruster thrust.

[0073] This embodiment obtains parameters such as ion current, divergence angle correction factor, and ion density, and adopts thrust correction processing to more accurately calculate and obtain the thrust of the Hall thruster. This helps to eliminate errors in thrust and improve the accuracy of thrust. By performing thrust correction processing based on the corrected divergence angle, the thrust of the Hall thruster can be obtained in real time. This is of great significance for instantly understanding thrust changes and monitoring oscillations, and helps to instantly adjust and optimize the performance of the thruster. By introducing the divergence angle correction factor, the divergence angle can be corrected according to the actual ion current and ion density. Such a correction can more accurately reflect the characteristics of the Hall thruster plume and improve the credibility of the monitoring results.

[0074] By measuring the single ion current and the double ion current, the relevant data of the ion current when the Hall thruster is working is obtained. According to the ion current, the plume divergence angle and the ion density, the divergence angle correction factor is calculated, and the accuracy of the divergence angle is improved by correcting the divergence angle. The thrust correction processing is performed using the divergence angle correction factor, and the thrust of the Hall thruster is calculated according to the corrected parameters, thereby reducing the error in the thrust calculation. This embodiment further improves the accuracy and real-time performance of the Hall thruster oscillation optoelectronic joint monitoring method. By introducing the divergence angle correction factor and the thrust correction processing, the calculation of the Hall thruster thrust is optimized, which helps to more accurately monitor and evaluate the real-time situation of the thrust, and further ensure the stable operation of the thruster.

[0075] Embodiment 7: This embodiment further limits the Hall thruster oscillation photoelectric joint monitoring method described in Embodiment 6, and the divergence angle correction factor is:

[0076]

[0077] Where r is the thruster radius, is the ion density, is the plume divergence angle at different positions, is the ion current.

[0078] The divergence angle correction factor in this embodiment takes into account the plume divergence angle at different positions, making the correction more accurate and taking into account the plume characteristics at different parts of the thruster, thereby improving the accuracy of monitoring. The divergence angle correction factor includes factors such as thruster radius, ion density and ion current, and comprehensively considers multiple key parameters, making the correction more comprehensive and more in line with actual working conditions. By introducing the divergence angle correction factor, the divergence angle can be quantitatively corrected rather than simply corrected, which helps to more accurately reflect the actual characteristics of the thruster plume.

[0079] In practical applications, the plume divergence angles at different positions are different. Therefore, by introducing r (thruster radius) and the plume divergence angles at different positions, the divergence angle can be corrected more accurately to adapt to different working conditions. The divergence angle correction factor includes parameters such as the thruster radius, ion density, and ion current. These parameters combined affect the correction of the divergence angle, making the correction more comprehensive. All the parameters in the formula are measurable, so the introduction of the divergence angle correction factor realizes the quantitative correction of the divergence angle, rather than simply correcting the direction, which improves the accuracy of the correction. This implementation method is more detailed and comprehensive. The divergence angle correction improves the accuracy of the Hall thruster oscillation optoelectronic joint monitoring method. By considering more influencing factors, a more accurate correction of the divergence angle when the thruster is working can be achieved to better monitor and evaluate the real-time situation of the thrust.

[0080] Embodiment 8: This embodiment further limits the Hall thruster oscillation optoelectronic joint monitoring method described in Embodiment 6. The thrust of the Hall thruster is obtained by performing thrust correction processing according to the divergence angle correction factor, specifically:

[0081]

[0082] in, is the thrust correction factor, is the accelerating voltage, is the mass flow rate of xenon gas, and vt is the velocity of ions.

[0083] In this embodiment, a thrust correction factor is introduced, and additional correction factors are taken into account, so that the thrust of the Hall thruster obtained is more accurate, and multiple factors in the system are taken into account. Factors such as the mass flow rate of xenon gas and the speed of ions are taken into account, so that the correction of thrust is more adaptable to different working conditions, and the applicability of the method is improved. Each parameter in the thrust correction factor plays a certain role in the correction of thrust. These parameters include the thrust correction factor itself, the acceleration voltage, the mass flow rate of xenon gas and the speed of ions. Through the comprehensive consideration of these parameters, a more accurate correction of thrust is achieved. The influence of different parameters on thrust is comprehensively considered. The acceleration voltage affects the intensity of the electric field, and the mass flow rate of xenon gas and the speed of ions affect the flow characteristics of the propulsion material. By taking these parameters into account, the actual situation of thrust is better reflected.

[0084] Embodiment 9: This embodiment further limits the Hall thruster oscillation optoelectronic joint monitoring method described in Embodiment 8. The thrust correction factor The divergence correction factor and doubly charged ion correction factor The product of gets:

[0085] .

[0086] In this embodiment, the product of the divergence angle correction factor and the doubly-charged ion correction factor is used as the thrust correction factor, which more comprehensively considers the influence of different factors on the thrust and improves the accuracy of thrust measurement. The introduction of the divergence angle correction factor considers the influence of the divergence angle of the ion beam on the thrust, making the thrust correction under different divergence angle conditions more accurate. The doubly-charged ion correction factor is considered, which involves the charge state of the ions in the propulsion material, thereby correcting the thrust more accurately.

[0087] The thrust correction factor is calculated by multiplying the divergence angle correction factor and the doubly-charged ion correction factor. This means that the effects of the two correction factors are considered comprehensively, and through their product, the thrust value is corrected more comprehensively. The divergence angle correction factor is introduced to consider the influence of the ion beam divergence angle on the thrust. The larger the divergence angle, the actual thrust effect may deviate from the theoretical value. Through the divergence angle correction, it can better adapt to the thrust measurement under different conditions. The doubly-charged ion correction factor may involve the charge state of the ions in the propulsion material, which plays an important role in the accuracy of the corrected thrust value. By comprehensively considering the divergence angle and the correction factor of the doubly-charged ions, the accuracy of thrust measurement by the Hall thruster oscillation optoelectronic joint monitoring method is improved. By correcting the thrust more comprehensively and accurately, more accurate monitoring and evaluation of the working status of the Hall thruster can be achieved.

[0088] Embodiment 10: This embodiment is a combined photoelectric monitoring method for Hall thruster oscillation described in Embodiment 9, characterized in that the double-charged ion correction factor for:

[0089] .

[0090] Embodiment 11: This embodiment provides a specific example of the Hall thruster oscillation optoelectronic combined monitoring device described in Embodiment 1, and is also used to explain Embodiments 2 to 4. Specifically:

[0091] The Hall thruster 2 is fixed on the plane 1, the two-dimensional image acquisition device (camera) 3 is fixed on the bracket 8, the bracket 8 and the Hall thruster 2 are fixed on the same plane 1, the probe array composed of the Faraday probe 5 and the RPA probe 6 is fixed on the bracket 4 to monitor the thruster plume 7 in real time, and feed back the monitoring data to the terminal, the plume image acquisition device (camera) 3 fixed on the bracket 8 surrounds the thruster 2, and monitors the thruster plume 7 in real time, and feeds back the data to the terminal for calculating the thrust of the Hall thruster.

[0092] Through the above arrangement process, the whole set of equipment can monitor the plasma plume during the thruster's operation on the ground and upload it to the data processing terminal, through which the thruster's working status can be analyzed.

[0093] The device described in this embodiment has the following advantages:

[0094] 1. The device used is simple to operate at the ground stage. It only requires a circular array of Faraday probes and RPA probes. The plume fluctuation data recorded at the same time is more accurate than the conventional single electrical probe method.

[0095] 2. Through contact measurement, the device used can test the thruster plume during on-orbit operation more accurately, ensuring the correctness of the data.

[0096] 3. The data collection device measures the thruster plume from multiple angles, avoiding insufficient single-probe measurement data during the test and improving the accuracy of capturing plume fluctuations during the test.

[0097] 4. It has high spatial resolution, temporal resolution and measurement accuracy.

[0098] 5. Use a probe array and plume detection device (camera) to measure the fluctuations of the thruster plume. The operation is simple and does not require additional equipment or calibration.

[0099] 6. The whole set of equipment and procedures have extremely fast response capabilities, and data can be obtained quickly to facilitate timely adjustments to the thrusters.

[0100] The Hall thruster oscillation optoelectronic joint monitoring method comprises the following steps:

[0101] Step 1: Turn on the thruster during the ground process and pass a certain mass flow of xenon gas and the voltage flowing through the thruster under normal working conditions With current ;

[0102] Step 2: Turn on the thruster during the ground process. After the thruster is working stably, the probe array composed of the Faraday probe 5 and the PRA probe as shown in the figure is used to obtain the single-charged ion current at different positions of the thruster plume under normal working conditions. , doubly charged ion current , plume divergence angle and ion energy Obtain ion energy distribution and upload the obtained data to the terminal;

[0103] Step 3: When the Hall thruster is working stably, turn on the two-dimensional data acquisition device (camera) to measure the thruster plume image in real time, upload the data to the host computer for analysis to obtain the plume electron temperature The temperature distribution and ion density of the plume are obtained The distribution data is uploaded to the terminal;

[0104] Step 4: After all the data of the target to be measured are completely uploaded to the terminal, the obtained data are processed to obtain the real-time situation of the Hall thruster thrust oscillation.

[0105] First, before the experiment begins, it is necessary to check whether the cooling water device is operating normally and whether the coolant is in good condition to ensure that the camera can operate normally.

[0106] Since the working fluid of the thruster is common xenon, the thrust of the thruster is:

[0107]

[0108] in, is the thrust correction factor, is the ion current, is the accelerating voltage.

[0109] Correction Factor The divergence correction factor and doubly charged ion correction factor The product of:

[0110]

[0111] Among them, the divergence angle correction factor for:

[0112]

[0113] Where r is the thruster radius, is the ion density, is the plume divergence angle at different positions, is the ion current.

[0114] The ion current in the above formula is:

[0115]

[0116] in is the single ion current, is the dual ion current.

[0117] Correction Factor for Doubly Charged Ions for:

[0118]

[0119] The above processing combined with the ion energy distribution measured by the probe array and the plume temperature distribution obtained by the camera can obtain the oscillation of the Hall thruster in real time.

[0120] The present embodiment provides a Hall thruster oscillation optoelectronic joint monitoring method, which collects thruster plume images through a fixed camera device and feeds them back to the receiving end, and combines an array composed of a Faraday probe and an RPA probe to provide reliable test data for local testing, research and development, and mass production of thrusters. Compared with traditional methods, this method has the advantages of high degree of automation, time and labor saving, accurate test data, low interference, and high credibility.

[0121] Although the preferred embodiments of the present disclosure have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concepts. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present disclosure.

[0122] Obviously, those skilled in the art can make various changes and modifications to the present disclosure without departing from the spirit and scope of the present disclosure. Thus, if these modifications and variations of the present disclosure fall within the scope of the claims of the present disclosure and their equivalents, the present disclosure is also intended to include these modifications and variations.

[0123] It should be understood by those skilled in the art that the embodiments of the present disclosure may be provided as methods, systems or computer program products. Therefore, the present disclosure may take the form of a complete hardware embodiment, a complete software embodiment or an embodiment combining software and hardware aspects. Moreover, the present disclosure may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0124] The present disclosure is described with reference to flowcharts and / or block diagrams of methods, devices (systems) and computer program products according to embodiments of the present disclosure. It should be understood that each process and / or block in the flowchart and / or block diagram and the combination of processes and / or blocks in the flowchart and / or block diagram can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 A process or multiple processes and / or boxes Figure 1 These computer program instructions can also be stored in a computer-readable memory that can guide a computer or other programmable data processing device to work in a specific way, so that the instructions stored in the computer-readable memory produce a product including an instruction device, which implements the functions specified in the process. Figure 1 A process or multiple processes and / or boxes Figure 1 A function specified in one or more boxes.

[0125] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operating steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing instructions for implementing the process. Figure 1 A process or multiple processes and / or boxes Figure 1The steps for the functions specified in one or more boxes.

[0126] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present disclosure rather than to limit its protection scope. Although the present disclosure has been described in detail with reference to the above embodiments, ordinary technicians in the relevant field should understand that after reading the present disclosure, those skilled in the art can still make various changes, modifications or equivalent substitutions to the specific implementation methods of the invention, but these changes, modifications or equivalent substitutions are all within the protection scope of the disclosed claims to be approved.

Claims

1. A combined photoelectric monitoring method for Hall thruster oscillation, characterized in that: The method is implemented by a Hall thruster oscillation optoelectronic combined monitoring device, which includes: Plane (1), Hall thruster (2), two-dimensional data acquisition device (3), probe bracket (4), Faraday probe (5), RPA probe (6), thruster plume (7) and bracket (8); The Hall thruster (2) is fixed on the plane (1), and the Hall thruster (2) propels to form a thruster plume (7). The two-dimensional data acquisition device (3) is fixed on the plane (1) via a bracket (8); and the probe array composed of the Faraday probe (5) and the RPA probe (6) is fixed on the probe bracket (4); The number of the Faraday probes (5) and the number of the RPA probes (6) are the same; The Faraday probes (5) and the RPA probes (6) form an alternating array and are evenly distributed on the probe support (4), and the probe support (4) is a flat plate structure; The two-dimensional data acquisition device (3) is a camera; The method comprises: S1: Turn on the Hall thruster (2) during the grounding process, introduce xenon gas, and obtain the voltage flowing through the Hall thruster (2) under normal working conditions. With current ; S2: After the Hall thruster (2) is working stably, the probe array obtains the single-charged ion current, double-charged ion current, plume divergence angle and ion energy at different positions of the thruster plume (7) under normal working conditions to obtain ion energy distribution data, and uploads the ion energy distribution data to the terminal; S3: Start the two-dimensional data acquisition device (3) to measure the thruster plume (7) image in real time, upload the measurement data to the host computer, and the host computer analyzes and obtains the plume electron temperature The temperature distribution and ion density of the plume are obtained The distribution data is uploaded to the terminal; S4: Processing the data acquired in step S2 and step S3 to obtain the real-time situation of the thrust oscillation of the Hall thruster (2); The step S4 comprises: Get the ion current: in, is the single ion current, is the dual ion current; Obtain divergence angle correction factor according to ion current, plume divergence angle and ion density, and correct the divergence angle; Perform thrust correction processing according to the divergence angle correction factor and the double-charged ion correction factor to obtain the thrust of the Hall thruster; Determine the real-time situation of the thrust oscillation of the Hall thruster according to the thrust of the Hall thruster; The thrust correction processing is performed according to the divergence angle correction factor and the double-charged ion correction factor to obtain the thrust of the Hall thruster, specifically: in, is the thrust correction factor, is the accelerating voltage, is the mass flow rate of xenon, v i is the velocity of the ion; The thrust correction factor The divergence correction factor and doubly charged ion correction factor The product of gets: 。 2. The Hall thruster oscillation photoelectric joint monitoring method according to claim 1 is characterized in that: The divergence angle correction factor is: Where r is the thruster radius, is the ion density, is the plume divergence angle at different positions, is the ion current.

3. The Hall thruster oscillation photoelectric joint monitoring method according to claim 1 is characterized in that: The double-charged ion correction factor for: 。

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