Autonomous Satellite Orbit Control Method Based on Continuously Tunable Performance Ion Electric Propulsion

Abstract

The present invention discloses a method for autonomous control of satellite orbits based on continuously adjustable ion electric propulsion, comprising the following steps: S1: constructing an optimal matching feature database for continuously adjustable thrust performance of ion electric propulsion; S2: constructing an atmospheric damping-thrust correlation matrix for typical orbital altitudes; S3: performing real-time processing of multi-source data based on satellite real-time orbital parameters, atmospheric density parameters and satellite structure design parameters, and using an on-board computer to calculate the atmospheric damping corresponding to the orbital altitude in real time; S4: the control module of the ion electric propulsion system with continuously adjustable performance quickly completes high-precision thrust output to achieve continuous variable thrust output; S5: comparing the real-time orbital altitude of the satellite with the preset corresponding nominal value, calculating the deviation, and realizing orbit control altitude calibration; S6: autonomously and continuously carrying out orbit maintenance tasks based on ion electric propulsion to achieve autonomous on-orbit operation. This method realizes the transformation and improvement of the orbit control means of low-earth orbit satellites from long-term manned participation to unmanned autonomous control.

Description

Technical Field

[0001] The present invention relates to the field of advanced aerospace propulsion - space electric propulsion technology. Specifically, it relates to a method for autonomous control of the orbit of a low - earth orbit satellite based on continuously adjustable ion electric propulsion performance. Background Art

[0002] A significant feature of the on - orbit application of space electric propulsion is continuous operation in the small - thrust mode for a long time. Therefore, when a satellite uses space electric propulsion to perform complex tasks, restricted by different orbital environments, its application modes and application control strategies are diverse and very complex. Coupled with the relatively complex working timing of the electric propulsion system, it leads to great difficulties, low efficiency, and many faults in the ground artificial measurement, control, and application management of satellites based on electric propulsion. For satellites with high task frequencies and complex control rates in some tasks, it requires a large amount of manpower, material resources, and resource guarantees on the ground. Therefore, there is an extremely urgent need to seek a method for autonomous on - orbit management of satellites based on space electric propulsion, enabling electric propulsion satellites to have the ability of autonomous on - orbit management work, which can greatly reduce the difficulty and cost of ground artificial control. Summary of the Invention

[0003] Aiming at the problems existing in the prior art, the purpose of the present invention is to provide a method for autonomous control of the orbit of a low - earth orbit satellite based on continuously adjustable ion electric propulsion performance, so as to solve the problems of large orbit control tasks, low efficiency, easy error, and high cost when the existing ion electric propulsion executes the satellite orbit maintenance task.

[0004] To achieve the above - mentioned purpose, the present invention provides a method for autonomous control of a satellite orbit based on continuously adjustable ion electric propulsion performance. The method includes the following steps:

[0005] S1: Based on the ground performance test data set of the continuously adjustable ion electric propulsion system, construct an optimal matching feature database for continuously adjustable ion electric propulsion thrust performance;

[0006] S2: Based on the nominal typical orbital altitude damping database, construct an atmospheric damping - thrust correlation matrix for the typical orbital altitude;

[0007] S3: Perform real - time processing of multi - source data based on the satellite's real - time orbit parameters, atmospheric density parameters, and satellite structure design parameters, and use the on - board computer to calculate the atmospheric damping corresponding to the orbital altitude in real time;

[0008] S4: The control module of the continuously adjustable ion electric propulsion system quickly completes high - precision thrust output to achieve continuous variable - thrust output;

[0009] S5: Compare the real - time orbital altitude of the satellite with the preset corresponding nominal value, calculate the deviation, and achieve orbit control altitude calibration;

[0010] S6: Independently and continuously carry out orbit maintenance tasks based on ion electric propulsion to achieve autonomous on-orbit operation.

[0011] Furthermore, step S1 specifically includes:

[0012] S11: Based on the ground performance test dataset of the continuously performance-adjustable ion electric propulsion system, establish a multi-parameter matching feature database with optimal thrust performance.

[0013] S12: Combine the optimal feature database of thrust performance and the performance test results to form a specific regulation method database for quickly achieving different thrust performances.

[0014] Furthermore, the multi-parameters include the working voltage, current, propellant flow rate, and thrust adjustment resolution of the ion electric propulsion.

[0015] Furthermore, the regulation method can be a quick adjustment of a single parameter or a coordinated regulation of two or more parameters.

[0016] Furthermore, in step S2, according to the area of the windward side of the satellite's overall design structure and the typical orbital nominal damping rate, calculate the minimum orbit maintenance thrust value required at different orbital altitudes to form a one-to-one mapping relationship between damping and thrust.

[0017] Furthermore, step S3 includes:

[0018] S31: Use the sensors on the satellite to obtain the satellite orbit parameters, orbital atmospheric density, and satellite attitude parameters in real time.

[0019] S32: Carry out multi-information fusion processing to obtain the damping compensation thrust value required for the current orbit.

[0020] Furthermore, the multi-information includes orbital atmospheric density, satellite orbit parameters, satellite attitude, and thrust-damping mapping correlation.

[0021] Furthermore, in step S4, according to the need for real-time damping compensation, the ion electric propulsion control module executes thrust adjustment and output operations based on the preset on-orbit application strategy and the regulation method formed in step S1.

[0022] Furthermore, in step S5, use the ion electric propulsion system control module to carry out a deviation comparison analysis between the real-time orbital altitude of the satellite and the preset orbital altitude of the module.

[0023] Furthermore, in step S6, according to the need for overall satellite orbit control, use the continuously performance-adjustable ion electric propulsion system to independently carry out orbit maintenance operations in the long term.

[0024] Beneficial effects: The low-orbit satellite orbit autonomous control method based on continuously adjustable ion electric propulsion performance proposed by the present invention provides a new idea for satellite autonomous orbit maintenance based on the continuously adjustable ion electric propulsion that has been applied in engineering and its ground performance adjustment tests, and combines the real-time working and operating environment parameters of on-orbit satellites. It supports autonomous orbit maintenance under non-telemetry and control conditions and has important engineering application value; it enables the electric propulsion satellite to have the ability to manage its work autonomously on orbit and can reduce the difficulty and cost of ground manual control and management. Brief Description of the Drawings

[0025] Figure 1 Shows the flowchart of the satellite orbit autonomous control method based on continuously adjustable ion electric propulsion performance according to the present invention;

[0026] Figure 2 Shows the flowchart of constructing the feature database of the satellite orbit autonomous control method based on continuously adjustable ion electric propulsion performance according to the present invention;

[0027] Figure 3 Shows the flowchart of multi-source information fusion processing of the satellite orbit autonomous control method based on continuously adjustable ion electric propulsion performance according to the present invention. Detailed Embodiments

[0028] Next, the technical solutions of the present invention will be described clearly and completely in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0029] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be construed as a limitation of the present invention. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0030] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection", and "coupling" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0031] The following will be combined with Figures 1 - 3 to describe the specific embodiments of the present invention in detail. It should be understood that the specific embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0032] As Figures 1 - 3 shown, the present invention provides a method for autonomous control of a low-earth orbit satellite orbit based on continuously adjustable ion electric propulsion performance, which is realized based on an existing continuously adjustable ion electric propulsion test data set and a multi-source data fusion algorithm. Based on the electrical parameter data set obtained from the ground adjustment test of continuously adjustable ion electric propulsion performance, this method formulates an optimal matching feature database with a wide thrust output range depending on multiple parameters such as the working voltage, current, and flow rate of the ion electric propulsion system, and correlates the feature database with the damping value of the nominal typical orbit altitude, and then constructs a damping-thrust correlation matrix. Then, using the satellite orbit and structure parameter data and the orbital atmospheric density detection data, the on-board computer calculates the damping required for orbit maintenance in real time. Synchronously, the ion electric propulsion system control module quickly adjusts and outputs the high-precision thrust performance of the ion electric propulsion according to the real-time orbit damping calculation result and the damping-thrust correlation matrix, and autonomously completes the control of the satellite orbit altitude. Finally, the real-time orbit semi-major axis of the satellite is compared with the semi-major axis of the nominal orbit altitude to ensure the accuracy and reliability of orbit control.

[0033] The method for autonomous control of a satellite orbit based on continuously adjustable ion electric propulsion performance of the present invention includes the following steps:

[0034] Step S1: Based on the ground performance test data set of the continuously adjustable ion electric propulsion system, construct an optimal matching feature database for continuously adjustable ion electric propulsion thrust performance. Specifically, it includes:

[0035] Step S11: Based on the ground performance test data set of the continuously adjustable ion electric propulsion system, which includes the performance test results of traversing multiple parameters such as different powers, different thrusts, different specific impulses, different voltages, different flow rates, different background pressures, different magnetic fields, and different neutralizer currents, propose key feature influencing parameters, and establish a multi-parameter feature database of ion electric propulsion with optimal wide-range thrust performance.

[0036] The parameters used in the ion electric propulsion multi-parameter characteristic database include: the supply flow rate of the electric propulsion propellant, the external magnetic field strength, the anode current of the electric propulsion, and the output thrust of the electric propulsion.

[0037] Since the on-orbit application of electric propulsion mainly focuses on the thrust output performance, the optimal screening strategy mainly optimally sorts the accuracy of the output thrust and the thrust rapid adjustment time.

[0038] As Figure 2 shown, the process of establishing the characteristic database is as follows:

[0039] S111. Based on the results of long-term ground test data, conduct multi-dimensional data processing and analysis to obtain the respective dependencies of the thrust adjustment variation of the performance continuously adjustable ion electric propulsion system on the supply flow rate of the propellant, the anode current of the electric propulsion, and the external magnetic field strength. Using the obtained evolution curves of the thrust variation and a single parameter, combined with the least squares data fitting method, obtain the linear relationship between the thrust variation and the above three parameters;

[0040] S112. Verify the linear relationship obtained in S111 through experiments. Synchronously, measure the thrust response time and thrust adjustment accuracy during the test when the above three parameters are adjusted. Among them, the average value of the results of 5 groups of repeated tests is taken at each response time point. Using the analysis method in S111, obtain the linear relationships between the thrust response time, the thrust adjustment accuracy and the above three parameters respectively; obtain:

[0041] The linear relationship between the thrust variation ( ) and the working medium flow rate, the linear relationship between the thrust variation ( ) and the anode current, the linear relationship between the thrust variation ( ) and the magnetic field current; the linear relationship between the thrust response time ( ) and the working medium flow rate, the linear relationship between the thrust response time ( ) and the anode current, the linear relationship between the thrust response time ( ) and the magnetic field current; the linear relationship between the thrust adjustment accuracy ( ) and the working medium flow rate, the linear relationship between the thrust adjustment accuracy ( ) and the anode current, the linear relationship between the thrust adjustment accuracy ( ) and the magnetic field current;

[0042] S113. According to the linear relationships obtained in S111 and S112, adopt the method of polynomial fitting analysis to obtain the multi-dimensional functions of the influence of the working medium flow rate on the thrust variation, the thrust response time, and the thrust adjustment accuracy; according to this method, similarly obtain the multi-dimensional functions corresponding to the external magnetic field strength and the anode current:

[0043] S114. Based on the three groups of multi-dimensional functions obtained in S113, a thrust adjustment function based on three adjustable parameters is constructed by using the method of function summation;

[0044]

[0045] S115. Conduct experimental verification on the adjustment function obtained in S114, and eliminate the data points that are difficult to implement and unreasonable in engineering, so as to construct a database with one-to-one correspondence between propellant flow rate, applied magnetic field strength, and anode current for thrust adjustment:

[0046] 。

[0047] Step S12: Combining the constructed optimal thrust performance characteristic database, conduct thrust performance adjustment test. According to the performance test results, conduct weighted analysis using the SWOT method from the four dimensions of "fastest, steadiest, most efficient, and most feasible", and select the result with the highest weight to screen and form a database of specific control methods for quickly realizing different thrust performances (under different thrust performances, the dominant working parameters are different).

[0048] Among them, "fastest" is characterized by the time index, "steadiest" is characterized by the accuracy of thrust output, "most efficient" is characterized by the number of adjustment parameters, and "most feasible" is characterized by engineering feasibility. The selection basis for the four dimensions of indicators are: the shortest time, the smallest deviation of thrust output, the fewest adjustment parameters, and the most reliable discharge state.

[0049] SWOT is an analysis method, similar to the quadrant in mathematics, that is, the results are divided into four categories: strengths, weaknesses, opportunities, and threats. According to the previous performance test results, summarize and classify the test results respectively, and retain the adjustment strategies with strengths and opportunities; at the same time, for the data points with repeated thrust in the retained results, conduct weighted analysis from the four dimensions of the shortest time, the smallest deviation of thrust output, the fewest adjustment parameters, and the most reliable discharge state, and form control methods with different priorities in combination with application strategies.

[0050] Different control methods refer to the adjustment methods of using a single adjustment of flow rate, magnetic field, current, or simultaneously adjusting two of them, or synchronously adjusting all three parameters in engineering applications to achieve high-precision thrust output.

[0051] The control method can be a rapid adjustment of a single parameter or a coordinated control of two or more parameters. According to the results of the previous performance tests, the test results are summarized and classified respectively, and the adjustment strategies with advantages and opportunities are retained; at the same time, for the data points with repeated thrust in the retained results, a weighted analysis is carried out in four dimensions: the shortest time, the smallest thrust output deviation, the fewest adjustment parameters, and the most reliable discharge state, and combined with the application strategy to form control methods with different priorities.

[0052] Step S2: Based on the nominal typical orbital altitude damping database, construct an atmospheric damping-thrust correlation matrix for the typical orbital altitude. Specifically, according to the area of the windward side of the satellite's overall design structure, combined with the typical orbital nominal damping rate in the high or low solar activity years, calculate the atmospheric damping suffered by different satellite flight attitudes at different orbital altitudes, obtain the average thrust compensation value required for orbit maintenance according to the damping force, and construct a one-to-one mapping relationship matrix between the damping and the average thrust; the calculation formula for the constructed mapping relationship is:

[0053] H (orbital damping ∝ orbital altitude, equivalent windward area, side area) = T (thrust).

[0054] The rapid and efficient adjustment database of thrust is established in S1, and the atmospheric damping database of different orbital altitudes already used in the aerospace field is used in S2. In engineering applications, it is necessary to associate the atmospheric damping database with the thrust database to achieve damping balance at different orbital altitudes through thrust adjustment (that is, to offset the damping with thrust).

[0055] Step S3: Perform real-time processing of multivariate data based on the satellite's real-time orbital parameters, atmospheric density parameters, and satellite structure design parameters, and use the on-board computer to calculate the atmospheric damping corresponding to the orbital altitude in real time. Specifically, step S31: Use the sensors, star catalog, and navigation and positioning system carried by the satellite to obtain the parameters such as the satellite's operating orbit, orbital atmospheric density, and satellite attitude in real time; step S32: Use the on-board computer and the multivariate information fusion processing algorithm based on the vector machine to carry out the fusion calculation and processing of multivariate information such as orbital atmospheric density, orbital parameters, satellite attitude, and corresponding damping rate to obtain the average thrust value of the damping compensation required for the current orbit;

[0056] As Figure 3 shown, the multivariate information fusion processing flow is as follows:

[0057] S311. Based on the real-time measurement data of the star catalog carried by the satellite, obtain the real-time information of the satellite's orbital altitude, atmospheric density, damping force, and satellite attitude;

[0058] S312. Based on the real-time measurement data of the satellite ground control station, obtain the satellite's orbital altitude, and compare it with the data measured in S311. If the error is within 1%, it is considered appropriate;

[0059] S313. Combine the data such as the orbital altitude, damping force, and satellite attitude measured in S311 and S312 with the existing orbital atmospheric density database, orbital damping rate database, satellite structure parameters (windward area), etc. for data fusion processing to calculate the real-time orbital damping force;

[0060] S314. Based on the real-time orbital damping force calculated in S313, combine the electric propulsion application control strategy based on the orbital altitude measured in S311 and S312, the damping-thrust correlation matrix obtained in S12, etc. for data fusion processing, and then accurately obtain the real-time orbital compensation thrust and its implementation method.

[0061] The multi-information fusion processing algorithm is a variety of mature calculation and processing methods represented by the vector machine.

[0062] Compensation average thrust value: According to parameters such as the satellite revisit period, the orbital altitude to be maintained, the satellite flight attitude, the solar power, and the orbital damping rate, calculate the total damping force that the satellite needs to overcome to maintain the orbital altitude and the on-orbit operation time when the electric propulsion can be turned on, and then obtain the average thrust of the electric propulsion required to offset the total damping force.

[0063] Step S4: The performance continuously adjustable ion electric propulsion system control module quickly completes high-precision thrust output to achieve variable thrust continuous output. Specifically, according to the damping real-time compensation requirement obtained in step S3, use the on-board management system to send specific thrust output instructions to the ion electric propulsion system control module; the ion electric propulsion system control module, based on the preset on-orbit application strategy and the control method formed in step S1, responds to the instructions and autonomously activates the working mode of the ion electric propulsion system, quickly executes the thrust adjustment and output operations, thereby completing the damping real-time compensation;

[0064] Step S5: Compare the real-time orbital altitude of the satellite with the preset corresponding nominal value, calculate the deviation, and achieve orbital control altitude calibration. Specifically, use the ion electric propulsion system control module to conduct a deviation comparison and analysis of the real-time orbital altitude of the satellite (obtained in step S3) and the deviation of the module preset for the orbital altitude. If the deviation is higher than 10%, continue to execute the next orbital maintenance task. If the situation where the deviation exceeds 10% occurs continuously three times, keep the satellite state unchanged, abort the task and notify the ground, and let the ground intervene manually; if the deviation is lower than 10%, continue to execute the autonomous orbital maintenance task until the deviation between the real-time satellite orbital altitude and the expected value is also lower than 10%, then stop this round of orbital control task;

[0065] The real-time orbital altitude is obtained through methods such as the altimeter carried by the satellite itself, the navigation and positioning system, and ground station measurement and control.

[0066] Nominal value: The nominal value is the orbital altitude designed for the satellite and is a design value.

[0067] Step S6: Independently and continuously carry out orbit maintenance tasks based on ion electric propulsion to achieve on-orbit autonomous operation. Specifically, according to the overall satellite orbit control requirements and the workflow of Steps S1 - S5, use an ion electric propulsion system with continuously adjustable performance to long-term and independently carry out orbit maintenance operations for low-earth orbit satellites.

[0068] This method solves the problem of low efficiency of ground artificial measurement and control orbit maintenance caused by factors such as high orbit maintenance frequency of low-earth orbit satellites, long orbit maintenance time of small-thrust ion electric propulsion, and complex orbit control strategies, and realizes the transformation and improvement of the orbit control means of low-earth orbit satellites from long-term manned participation and on-duty to unmanned autonomous control, with high engineering application value and good application prospects.

[0069] Any process or method description in the flowchart of the present invention or described in other ways herein can be understood as representing a module, segment, or part of code including one or more executable instructions for implementing a specific logical function or process, which can be implemented in any computer-readable medium for an instruction execution system, apparatus, or device. The computer-readable medium can be any medium including storage, communication, propagation, or transmission of a program for use by an instruction execution system, apparatus, or device, including read-only memory, magnetic disks, or optical discs, etc.

[0070] In the description of this specification, the description referring to terms such as "embodiment", "example", etc. means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. In addition, those skilled in the art can combine or combine different embodiments or examples described in this specification and the features therein without contradiction.

[0071] Although the above content has shown and described the embodiments of the present invention, it can be understood that the above embodiments are exemplary and cannot be construed as limiting the present invention. Those of ordinary skill in the art can perform update operations such as changes, modifications, substitutions, and variations on the above embodiments within the scope of the present invention.

Claims

1. A satellite orbit autonomous control method based on performance-continuously adjustable ion electric propulsion, characterized in that: The method comprises the following steps: S1: Based on the ground performance test data set of the continuously adjustable ion electric propulsion system, a database of optimal matching characteristics of continuously adjustable ion electric propulsion thrust performance is constructed; S2: Based on the nominal typical orbit altitude damping database, the atmospheric damping-thrust correlation matrix of typical orbit altitude is constructed; S3: Based on the satellite's real-time orbit parameters, atmospheric density parameters and satellite structure design parameters, multivariate data is processed in real time, and the atmospheric damping corresponding to the orbital altitude is calculated in real time using the onboard computer; S4: Performance continuously adjustable ion electric propulsion system control module quickly completes high-precision thrust output and realizes variable thrust continuous output; S5: Compare the satellite's real-time orbit altitude with the preset corresponding nominal value, calculate the deviation, and realize orbit control altitude calibration; S6: Self-service continuous orbit maintenance mission based on ion electric propulsion, and achieve autonomous operation in orbit; The process of establishing the feature database is as follows: S111. Based on the test data of long-term ground experiments, the linear relationship between the thrust change and the propellant supply flow rate, the electric propulsion anode current, and the external magnetic field strength is obtained by using the obtained thrust change and the evolution curve of a single parameter; S112. Based on the linear relationship obtained in S111, using the analysis method in S111, obtain the linear relationship between the thrust response time, the thrust adjustment accuracy and the propellant supply flow rate, the electric propulsion anode current, and the external magnetic field strength respectively; get: Thrust change ( ) and the linear relationship between the working fluid flow rate, the thrust change ( ) and the linear relationship between the anode current and the thrust change ( ) and the linear relationship between the magnetic field current; thrust response time ( ) and the linear relationship between the working fluid flow rate, thrust response time ( )) and the linear relationship between the anode current and the thrust response time ( ) and the linear relationship between the magnetic field current; thrust adjustment accuracy ( ) and the linear relationship between the working fluid flow rate and the thrust adjustment accuracy ( ) and the linear relationship between the anode current and the thrust adjustment accuracy ( ) and the linear relationship between magnetic field current; S113. Based on the linear relationship obtained from S111 and S112, a multidimensional function of the effect of working fluid flow on thrust variation, thrust response time, and thrust regulation accuracy is obtained by using a polynomial fitting analysis method: S114. Based on the three sets of multidimensional functions obtained in S113, a thrust adjustment function based on three adjustable parameters is constructed by using a function summation method; S115. Test and verify the regulation function obtained in S114, remove the unreasonable data points that are difficult to implement in engineering, and thus construct a database with one-to-one correspondence between propellant flow rate, external magnetic field strength, and anode current and thrust regulation: 。 2. The satellite orbit autonomous control method based on performance continuously adjustable ion electric propulsion according to claim 1 is characterized in that: Step S1 specifically includes: S11: Based on the ground performance test data set of the continuously adjustable ion electric propulsion system, establish a multivariate parameter matching feature database with optimal thrust performance; S12: Combine the thrust performance optimal characteristic database and performance test results to form a database of specific control methods for quickly achieving different thrust performances.

3. The satellite orbit autonomous control method based on performance continuously adjustable ion electric propulsion according to claim 2 is characterized in that: The multivariate parameters include ion electric propulsion operating voltage, current, propellant flow rate and thrust adjustment resolution.

4. The satellite orbit autonomous control method based on performance continuously adjustable ion electric propulsion according to claim 2 is characterized in that: The control method is to quickly adjust a single parameter, or to control multiple parameters by coupling.

5. The satellite orbit autonomous control method based on performance continuously adjustable ion electric propulsion according to claim 1 is characterized by: In step S2, the minimum orbit-maintaining thrust values ​​required for different orbital altitudes are calculated according to the windward surface area of ​​the satellite's entire design structure and the typical orbit nominal damping rate, forming a one-to-one mapping relationship between damping and thrust.

6. The satellite orbit autonomous control method based on performance continuously adjustable ion electric propulsion according to claim 1 is characterized by: Step S3 includes: S31: Use the satellite's own sensors to obtain satellite orbit parameters, orbital atmospheric density and satellite attitude parameters in real time; S32: Carry out multi-information fusion processing to obtain the damping compensation thrust value required for the current orbit.

7. The method for autonomous satellite orbit control based on performance-continuously adjustable ion electric propulsion according to claim 6 is characterized in that: The multivariate information includes orbital atmospheric density, satellite orbital parameters, satellite attitude and thrust-damping mapping association.

8. The satellite orbit autonomous control method based on performance continuously adjustable ion electric propulsion according to claim 1 is characterized by: In step S4, according to the need for real-time damping compensation, the ion electric propulsion control module performs thrust adjustment and output operations based on the preset on-orbit application strategy and the control method formed in step S1.

9. The satellite orbit autonomous control method based on performance continuously adjustable ion electric propulsion according to claim 1 is characterized by: In step S5, the ion electric propulsion system control module is used to perform a comparison analysis of the deviation between the satellite's real-time orbital altitude and the module's preset orbital altitude.

10. The satellite orbit autonomous control method based on performance continuously adjustable ion electric propulsion according to claim 1 is characterized by: In step S6, according to the orbit control needs of the entire satellite, the ion electric propulsion system with continuously adjustable performance is used to carry out orbit maintenance operations autonomously for a long time.

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