A method and apparatus for optimizing the magnetic induction intensity of the discharge chamber of a variable thrust ion thruster

Abstract

This application relates to the field of spacecraft propulsion technology, specifically to a method and apparatus for optimizing the magnetic induction intensity design of the discharge chamber of a variable-thrust ion thruster. The method includes: defining the variable-thrust adjustment range of the thruster and determining the anode gas flow rate at integer thrust operating points; using particle simulation to obtain the required magnetic induction intensity and discharge current combination and plasma density distribution characteristics for each operating point; screening magnetic induction intensity parameters that meet uniformity and voltage conditions to form a corresponding relationship table; conducting optimization verification tests, collecting four parameters: discharge loss, voltage oscillation amplitude, propellant utilization rate, and beam current density distribution; and comprehensively evaluating to obtain the target magnetic induction intensity at the target thrust operating point. This application establishes a synergistic optimization mechanism for magnetic induction intensity and discharge current, solving the technical challenge of wide-range adjustment of variable-thrust ion thrusters, and providing a design basis for the control strategy of variable-thrust electric propulsion systems.

Description

Technical Field

[0001] This application relates to the field of spacecraft propulsion technology, and more specifically, to a method and apparatus for optimizing the magnetic induction intensity of the discharge chamber of a variable thrust ion thruster. Background Technology

[0002] To meet the demands of complex missions such as long-term deployment in ultra-low Earth orbit, multi-satellite networking and coordination, and high-precision remote sensing and scientific exploration, continuously variable thrust electric propulsion, as a significant breakthrough in the field of aerospace propulsion, is gradually becoming a core technology for improving satellite mission adaptability and engineering energy efficiency. The working mechanism of ion thrusters allows them to maintain relatively good performance even within a power range deviating from their optimal operating point, thus possessing a wide-range, high-precision continuous thrust adjustment capability. Furthermore, they achieve high levels of performance in key indicators such as thrust adjustment rate, resolution, and thrust noise.

[0003] To meet the demand for wide-range, high-precision continuous variable thrust adjustment, ion thrusters primarily optimize the sensitive parameters of the discharge chamber to construct a relatively optimal operating parameter range. This allows for effective control of plasma discharge intensity while maintaining a wide range of overall performance adjustment, thus achieving wide-range, high-precision thrust adjustment while ensuring a stable and reliable discharge process. The main factors affecting the operating thrust of an ion thruster include the anode gas supply flow rate, magnetic induction intensity, and plasma discharge current. Each thrust point corresponds to a unique optimal combination of anode gas supply, magnetic induction intensity, and discharge current, determined by the self-consistent equilibrium condition between the plasma and the electromagnetic field. With a fixed gas supply and discharge current, continuous thrust adjustment can be achieved simply by adjusting the magnetic induction intensity; conversely, if the magnetic induction intensity is fixed while other parameters are adjusted, it is impossible to reproduce the same thrust point without compromising discharge stability and continuity.

[0004] Therefore, to ensure the repeatability and reliability of the variable thrust electric propulsion system, the optimal magnetic flux density must be pre-calibrated and locked for each target thrust point. Given a fixed thruster diameter and discharge chamber configuration, how to quickly and effectively determine the optimal magnetic flux density required for different thrust points to meet the wide range of thrust adjustment needs is a critical problem that urgently needs to be solved in the engineering application of variable thrust ion electric propulsion systems. Summary of the Invention

[0005] This application provides a method and apparatus for optimizing the magnetic induction intensity design of the discharge chamber of a variable thrust ion thruster. By constructing a dynamically matched magnetic induction intensity-discharge current coordinated control mechanism, it solves key technical problems of variable thrust ion thrusters in terms of wide-range thrust output, plasma density adjustment, discharge stability and reliability.

[0006] To achieve the above objectives, in a first aspect, this application provides a method for optimizing the magnetic induction intensity design of the discharge chamber of a variable-thrust ion thruster, comprising the following steps: Based on the on-orbit application requirements and the structural status of the ion thruster, the variable thrust adjustment range that the ion thruster can achieve is determined, and the anode gas supply flow rate at the integer thrust operating point is determined. Using particle simulation, the magnetic induction intensity and plasma discharge current combination required to output a specified value of ion beam at each integer thrust operating point under a determined anode gas supply flow rate are obtained, and the circumferential distribution characteristics of plasma density and discharge voltage parameters under the corresponding combination are obtained. For each integer target thrust operating point, magnetic induction intensity parameters that meet the preset conditions for plasma distribution uniformity and have discharge voltage below the preset threshold are selected, and a table is compiled to show the correspondence between target thrust and magnetic induction intensity. Based on the table of the correspondence between target thrust and magnetic induction intensity, optimization verification tests of magnetic induction intensity were carried out for each integer target thrust operating point. During the test, four core parameters were collected simultaneously: plasma discharge loss, voltage oscillation amplitude, discharge chamber working fluid utilization rate, and ion beam density distribution. The four core parameters under each test condition are evaluated, and the combination of magnetic induction intensity and plasma discharge current that makes plasma discharge loss meet the preset requirements, voltage oscillation amplitude is lower than the preset threshold, working fluid utilization rate meets the preset requirements, and ion beam uniformity meets the preset requirements is selected. The magnetic induction intensity corresponding to this combination is the target magnetic induction intensity at the target thrust operating point.

[0007] Furthermore, the range of variable thrust adjustment achievable by the ion thruster is clarified, including: determining the upper limit threshold of variable thrust adjustment based on the maximum thrust condition that the ion thruster can stably output, the impact of the plasma sputtering effect in the discharge chamber on the on-orbit life under this condition, and the maximum power constraints and application requirements that the satellite platform can provide; and determining the lower limit threshold of variable thrust adjustment based on the minimum thrust condition that the ion thruster can stably output, and the impact of the plasma discharge oscillation characteristics in the discharge chamber on the safety and efficiency of the power supply under this condition.

[0008] Furthermore, the anode gas supply flow rate for integer thrust operating points is determined, including at least one of the following flow patterns: a one-to-one flow pattern, where each integer thrust operating point corresponds to an independent anode gas supply flow rate; and a one-to-many flow pattern, where the same anode gas supply flow rate covers 2-3 adjacent integer thrust operating points, and the maximum number of integer thrust operating points covered by the same anode gas supply flow rate is 4.

[0009] Furthermore, the circumferential distribution characteristics of plasma density include: the circumferential distribution characteristics of plasma density 1-3 mm downstream of the cathode shoe inside the discharge chamber and the circumferential distribution characteristics of plasma density 4-6 mm upstream of the gate assembly and from the screen grid.

[0010] Furthermore, optimization and verification tests of magnetic induction intensity were carried out, including: for each integer thrust operating point, fixing the anode gas supply flow rate, dynamically adjusting the magnetic induction intensity and discharge current according to a preset rule, ensuring that the ion beam flow rate extracted by the thruster always matches the requirements of the current thrust operating point, and obtaining multiple sets of different combinations of magnetic induction intensity and discharge current.

[0011] Furthermore, the voltage oscillation amplitude includes the plasma discharge voltage oscillation amplitude in the discharge chamber and the voltage oscillation amplitude of the main cathode contact electrode.

[0012] Furthermore, the ion beam uniformity is calculated using the following formula: , Where ξ is the ion beam uniformity, I bavg I is the average beam current density. bmax This represents the maximum beam current density.

[0013] Secondly, this application provides a magnetic induction intensity optimization design device for the discharge chamber of a variable-thrust ion thruster, comprising: a flow rate determination module, used to determine the achievable variable thrust adjustment range of the ion thruster based on on-orbit application requirements and the structural state of the ion thruster, and to determine the anode gas supply flow rate at integer thrust operating points; a combination acquisition module, used to acquire, using particle simulation methods, the magnetic induction intensity and plasma discharge current combination required for outputting a specified value of ion beam at each integer thrust operating point under its determined anode gas supply flow rate condition, and to obtain the circumferential distribution characteristics of plasma density and discharge voltage parameters under the corresponding combination; and a relationship compilation module, used to screen out magnetic induction ... The system employs several modules: an intensity parameter module to create a table showing the relationship between target thrust and magnetic induction intensity; an optimization and verification module to conduct optimization and verification tests on magnetic induction intensity for each integer target thrust operating point, based on the table; and a selection and acquisition module to evaluate the four core parameters under each test condition and select the magnetic induction intensity and plasma discharge current combination that meets preset requirements for plasma discharge loss, voltage oscillation amplitude, propellant utilization, and ion beam uniformity. The magnetic induction intensity corresponding to this combination is the target magnetic induction intensity for that target thrust operating point.

[0014] Furthermore, the flow determination module includes: an independent gas supply unit, used to adopt a one-to-one flow mode, that is, each integer thrust operating point corresponds to an independent anode gas supply flow; and a multi-element gas supply unit, used to adopt a one-to-many flow mode, where the same anode gas supply flow covers 2-3 adjacent integer thrust operating points, and the maximum number of integer thrust operating points covered by the same anode gas supply flow is 4.

[0015] Furthermore, the voltage oscillation amplitude collected by the verification module is optimized, including the voltage oscillation amplitude of the plasma discharge in the discharge chamber and the voltage oscillation amplitude of the main cathode contact electrode.

[0016] Thirdly, this application also provides a computer device, including a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to perform the following processes: Based on the on-orbit application requirements and the structural status of the ion thruster, the variable thrust adjustment range that the ion thruster can achieve is determined, and the anode gas supply flow rate at the integer thrust operating point is determined. Using particle simulation, the magnetic induction intensity and plasma discharge current combination required to output a specified value of ion beam at each integer thrust operating point under a determined anode gas supply flow rate are obtained, and the circumferential distribution characteristics of plasma density and discharge voltage parameters under the corresponding combination are obtained. For each integer target thrust operating point, magnetic induction intensity parameters that meet the preset conditions for plasma distribution uniformity and have discharge voltage below the preset threshold are selected, and a table is compiled to show the correspondence between target thrust and magnetic induction intensity. Based on the table of the correspondence between target thrust and magnetic induction intensity, optimization verification tests of magnetic induction intensity were carried out for each integer target thrust operating point. During the test, four core parameters were collected simultaneously: plasma discharge loss, voltage oscillation amplitude, discharge chamber working fluid utilization rate, and ion beam density distribution. The four core parameters under each test condition are evaluated, and the combination of magnetic induction intensity and plasma discharge current that makes plasma discharge loss meet the preset requirements, voltage oscillation amplitude is lower than the preset threshold, working fluid utilization rate meets the preset requirements, and ion beam uniformity meets the preset requirements is selected. The magnetic induction intensity corresponding to this combination is the target magnetic induction intensity at the target thrust operating point.

[0017] Fourthly, this application also provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, performs the following processes: Based on the on-orbit application requirements and the structural status of the ion thruster, the variable thrust adjustment range that the ion thruster can achieve is determined, and the anode gas supply flow rate at the integer thrust operating point is determined. Using particle simulation, the magnetic induction intensity and plasma discharge current combination required to output a specified value of ion beam at each integer thrust operating point under a determined anode gas supply flow rate are obtained, and the circumferential distribution characteristics of plasma density and discharge voltage parameters under the corresponding combination are obtained. For each integer target thrust operating point, magnetic induction intensity parameters that meet the preset conditions for plasma distribution uniformity and have discharge voltage below the preset threshold are selected, and a table is compiled to show the correspondence between target thrust and magnetic induction intensity. Based on the table of the correspondence between target thrust and magnetic induction intensity, optimization verification tests of magnetic induction intensity were carried out for each integer target thrust operating point. During the test, four core parameters were collected simultaneously: plasma discharge loss, voltage oscillation amplitude, discharge chamber working fluid utilization rate, and ion beam density distribution. The four core parameters under each test condition are evaluated, and the combination of magnetic induction intensity and plasma discharge current that makes plasma discharge loss meet the preset requirements, voltage oscillation amplitude is lower than the preset threshold, working fluid utilization rate meets the preset requirements, and ion beam uniformity meets the preset requirements is selected. The magnetic induction intensity corresponding to this combination is the target magnetic induction intensity at the target thrust operating point.

[0018] Fifthly, this application also provides a computer program product, including a computer program that, when executed by a processor, can implement the above-described method for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster.

[0019] This application provides a method and apparatus for optimizing the magnetic induction intensity design of the discharge chamber of a variable-thrust ion thruster, which has the following beneficial effects: This application constructs a dynamically matched magnetic induction intensity-discharge current coordinated control mechanism, realizing the matching adjustment and optimization of magnetic induction intensity, discharge current, and anode gas flow. It solves key technical problems of Kaufman-type variable thrust ion thrusters in terms of wide-range thrust output, plasma density adjustment, discharge stability, and reliability, providing methodological support for the design and optimization of discharge chamber configuration of variable thrust ion thrusters. It also achieves performance improvement of continuously variable thrust ion thrusters across the entire operating range, expanding their applicable scenarios and working modes in complex space environments, and effectively promoting the engineering application of Kaufman-type ion thrusters. At the same time, it constructs an innovative technical framework for the control strategy of variable thrust electric propulsion systems, laying the theoretical foundation for high-precision thrust control. Attached Figure Description

[0020] The accompanying drawings, which form part of this application, are used to provide a further understanding of the application and to make other features, objects, and advantages of the application more apparent. The illustrative embodiments and descriptions of this application are used to explain the application and do not constitute an undue limitation of the application. In the drawings: Figure 1 This is a schematic diagram illustrating the steps of the method for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster according to an embodiment of this application. Figure 2 This is a schematic diagram of the workflow of the magnetic induction intensity optimization design method for the discharge chamber of a variable thrust ion thruster provided in the embodiments of this application; Figure 3 This is a schematic diagram of the magnetic induction intensity optimization design device for the discharge chamber of a variable thrust ion thruster provided in the embodiments of this application; Figure 4 This is a schematic diagram of a computer device provided according to an embodiment of this application. Detailed Implementation

[0021] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of the present application.

[0022] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be used interchangeably where appropriate for the embodiments of this application described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0023] In this application, the terms "upper," "lower," "left," "right," "front," "rear," "top," "bottom," "inner," "outer," "middle," "vertical," "horizontal," "lateral," and "longitudinal" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These terms are primarily for the purpose of better describing this application and its embodiments, and are not intended to limit the indicated device, element, or component to having a specific orientation, or to be constructed and operated in a specific orientation.

[0024] Furthermore, in addition to indicating location or positional relationship, some of the aforementioned terms may also have other meanings. For example, the term "above" may also be used in some cases to indicate a certain dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this application based on the specific circumstances.

[0025] In addition, the term "multiple" should mean two or more.

[0026] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0027] like Figure 1-2 As shown, this application provides a method for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster. It constructs a dynamically matched magnetic induction intensity-discharge current coordinated control mechanism. By adjusting and optimizing the matching of magnetic induction intensity with discharge current and anode gas flow, it solves key technical challenges in wide-range thrust output, plasma density regulation, discharge stability, and reliability of the Kaufman-type variable-thrust ion thruster. The specific steps include the following: Step S1: Based on the on-orbit application requirements and the structural status of the ion thruster, determine the variable thrust adjustment range that the ion thruster can achieve, and determine the anode gas supply flow rate at the integer thrust operating point. Furthermore, the range of variable thrust adjustment achievable by the ion thruster is clarified, including: determining the upper limit threshold of variable thrust adjustment based on the maximum thrust condition that the ion thruster can stably output, the impact of the plasma sputtering effect in the discharge chamber on the on-orbit life under this condition, and the maximum power constraints and application requirements that the satellite platform can provide; and determining the lower limit threshold of variable thrust adjustment based on the minimum thrust condition that the ion thruster can stably output, and the impact of the plasma discharge oscillation characteristics in the discharge chamber on the safety and efficiency of the power supply under this condition.

[0028] Furthermore, the anode gas supply flow rate for integer thrust operating points is determined, including at least one of the following flow patterns: a one-to-one flow pattern, where each integer thrust operating point corresponds to an independent anode gas supply flow rate; and a one-to-many flow pattern, where the same anode gas supply flow rate covers 2-3 adjacent integer thrust operating points, and the maximum number of integer thrust operating points covered by the same anode gas supply flow rate is 4.

[0029] Step S2: Using particle simulation, obtain the magnetic induction intensity and plasma discharge current combination required for each integer thrust operating point to output a specified value of ion beam under its determined anode gas supply flow rate, and obtain the circumferential distribution characteristics of plasma density and discharge voltage parameters under the corresponding combination. Furthermore, the circumferential distribution characteristics of plasma density include: the circumferential distribution characteristics of plasma density 1-3 mm downstream of the cathode shoe inside the discharge chamber and the circumferential distribution characteristics of plasma density 4-6 mm upstream of the gate assembly and from the screen grid.

[0030] Specifically, the preferred particle simulation method is the PIC / MCC method, i.e., the particle grid / Monte Carlo collision simulation method. For each integer thrust operating point under a defined anode gas supply flow rate, the required combination of magnetic induction intensity and plasma discharge current is calculated to output a specified value of ion beam current. The circumferential distribution characteristics of plasma density are examined at two key locations. The first location is the circumferential distribution characteristics of plasma density 1-3 mm downstream of the cathode shoe inside the discharge chamber. This location is close to the cathode outlet, and its plasma density distribution reflects the initial state of ionization from the collision of electrons emitted by the cathode with the neutral gas, directly affecting the ionization efficiency and plasma stability inside the discharge chamber. The second location is the circumferential distribution characteristics of plasma density 4-6 mm upstream of the grid assembly. This location is adjacent to the grid inlet, and its plasma density distribution directly determines the uniformity and quality of the ion beam current drawn from the grid assembly.

[0031] Step S3: For each integer target thrust operating point, select the magnetic induction intensity parameters that meet the preset conditions for plasma distribution uniformity and have a discharge voltage lower than the preset threshold, and compile a table showing the correspondence between target thrust and magnetic induction intensity. Specifically, for each integer target thrust operating point, the magnetic flux density parameter that optimizes plasma distribution uniformity and minimizes discharge voltage is selected, forming a table of the "target thrust - optimal magnetic flux density" correspondence. This table uses the target thrust as an index to record the magnetic flux density reference value corresponding to each integer thrust operating point, providing an initial reference benchmark for subsequent optimization and verification tests. This effectively narrows the parameter scanning range in the experimental verification stage and reduces the testing workload.

[0032] Step S4: Based on the table of the correspondence between target thrust and magnetic induction intensity, conduct optimization verification tests on magnetic induction intensity for each integer target thrust operating point. During the test, four core parameters are collected simultaneously: plasma discharge loss, voltage oscillation amplitude, discharge chamber working fluid utilization rate, and ion beam density distribution. Furthermore, optimization and verification tests of magnetic induction intensity were carried out, including: for each integer thrust operating point, fixing the anode gas supply flow rate, dynamically adjusting the magnetic induction intensity and discharge current according to a preset rule, ensuring that the ion beam flow rate extracted by the thruster always matches the requirements of the current thrust operating point, and obtaining multiple sets of different combinations of magnetic induction intensity and discharge current.

[0033] Specifically, for each integer thrust operating point, the anode gas supply flow rate is first fixed, and then the magnetic induction intensity and discharge current are dynamically adjusted according to a preset rule to ensure that the ion beam flow rate extracted by the thruster always matches the requirements of the current thrust operating point. Through the above dynamic adjustment, multiple different combinations of magnetic induction intensity and discharge current are obtained. Each combination corresponds to a set of test conditions, and under each set of test conditions, four core parameters are simultaneously collected: Plasma discharge loss reflects the efficiency of the discharge chamber in converting electrical energy into plasma energy, and is an important indicator for evaluating the energy conversion efficiency of the discharge chamber. The lower the discharge loss, the more efficient the energy utilization.

[0034] Voltage oscillation amplitude: This includes the voltage oscillation amplitude of the plasma discharge in the discharge chamber and the voltage oscillation amplitude of the main cathode contact electrode. The voltage oscillation amplitude reflects the stability of the plasma discharge in the discharge chamber. The lower the oscillation amplitude, the more stable the discharge process, which is more beneficial to the safety of the power supply.

[0035] Discharge chamber working propellant utilization rate: This reflects the proportion of propellant that is effectively ionized and extracted in the discharge chamber, and is an important indicator for evaluating propellant utilization efficiency.

[0036] Ion beam density distribution: Reflects the distribution of ion beam density on the gate exit cross section and is used to evaluate the spatial uniformity of the ion beam.

[0037] Step S5: Analyze the four core parameters under each test condition, and select the combination of magnetic induction intensity and plasma discharge current that minimizes plasma discharge loss, minimizes discharge voltage oscillation amplitude, maximizes working fluid utilization, and optimizes ion beam uniformity. The magnetic induction intensity corresponding to this combination is the final optimal magnetic induction intensity at the target thrust operating point.

[0038] Furthermore, the ion beam uniformity is calculated using the following formula: , Where ξ is the ion beam uniformity, I bavg I is the average beam current density. bmax This represents the maximum beam density. The ion beam uniformity index reflects the consistency of the ion beam distribution on the gate exit cross-section and is one of the important criteria for evaluating the performance of the thruster. The closer the uniformity value is to 1, the more uniform the beam distribution and the more ideal the performance of the gate assembly.

[0039] Specifically, the embodiments of this application construct a three-stage magnetic induction intensity optimization design process through the above five steps: "particle simulation pre-screening - experimental verification fine calibration - comprehensive judgment of core parameters". This process can obtain the optimal magnetic induction intensity of the discharge chamber of the variable thrust ion thruster, ensuring the scientificity and reliability of the magnetic induction intensity parameters at each thrust operating point.

[0040] like Figure 3 As shown, this application also provides a device for optimizing the magnetic induction intensity design of the discharge chamber of a variable thrust ion thruster, comprising: The flow rate determination module is used to determine the variable thrust adjustment range that the ion thruster can achieve, and to determine the anode gas supply flow rate at the integer thrust operating point, based on the on-orbit application requirements and the structural status of the ion thruster. Furthermore, the flow determination module includes: an independent gas supply unit, used in a one-to-one flow mode, where each integer thrust operating point corresponds to an independent anode gas supply flow. This unit is suitable for application scenarios with a small number of thrust points and high requirements for gas supply accuracy; and a multi-source gas supply unit, used in a one-to-many flow mode, where the same anode gas supply flow covers 2-3 adjacent integer thrust operating points, and the maximum number of integer thrust operating points covered by the same anode gas supply flow is 4. This unit is suitable for application scenarios with dense thrust points and high requirements for the response speed of the gas supply system.

[0041] The combined acquisition module is used to obtain the magnetic induction intensity and plasma discharge current combination required for outputting a specified value of ion beam when each integer thrust operating point is under the determined anode gas supply flow condition, using particle simulation method, and to obtain the circumferential distribution characteristics of plasma density and discharge voltage parameters under the corresponding combination. The relation table creation module is used to select magnetic induction intensity parameters that meet the preset conditions for plasma distribution uniformity and have a discharge voltage below a preset threshold for each integer target thrust operating point, and form a table of the correspondence between target thrust and magnetic induction intensity. The optimization verification module is used to conduct optimization verification tests on magnetic induction intensity based on the table of the correspondence between target thrust and magnetic induction intensity for each integer target thrust operating point. During the test, four core parameters are collected simultaneously: plasma discharge loss, voltage oscillation amplitude, discharge chamber working fluid utilization rate, and ion beam density distribution. Among them, the voltage oscillation amplitude collected by the optimization verification module includes the plasma discharge voltage oscillation amplitude in the discharge chamber and the voltage oscillation amplitude of the main cathode contact electrode.

[0042] The screening and acquisition module is used to analyze the four core parameters under each test condition and screen out the combination of magnetic induction intensity and plasma discharge current that makes the plasma discharge loss meet the preset requirements, the voltage oscillation amplitude is lower than the preset threshold, the working fluid utilization rate meet the preset requirements, and the ion beam uniformity meet the preset requirements. The magnetic induction intensity corresponding to this combination is the target magnetic induction intensity at the target thrust operating point.

[0043] like Figure 4As shown in the illustration, this application also provides a computer device, including a processor, a communication bus, a user interface, a network interface, and a memory. The communication bus is used to enable communication between the components. The user interface may include a display screen, camera, keyboard, etc., for human-computer interaction. The network interface may optionally include a standard wired interface or a wireless interface. The memory may be a high-speed random access memory or a stable non-volatile memory. The memory stores a computer program, specifically including an operating system, a network communication module, a user interface module, and an application program for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster. When the processor calls the computer program stored in the memory, it executes the operating system to achieve unified management and scheduling of the computer device's hardware and software resources, realizes data interaction with external devices through the network communication module, realizes information transmission between the user and the computer device through the user interface module, and calls the application program for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster to implement the optimization design method for the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster provided in this application embodiment.

[0044] This application also provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the aforementioned method for optimizing the magnetic induction intensity design of the discharge chamber of a variable-thrust ion thruster. The storage medium can be at least one of a read-only memory, magnetic tape, floppy disk, flash memory, optical memory, or high-density embedded non-volatile memory.

[0045] This application also provides a computer program product, including a computer program that, when executed by a processor, implements the above-described method for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster.

[0046] Those skilled in the art will understand that all or part of the process in the above-described method for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods.

[0047] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A method for optimizing the magnetic induction intensity design of the discharge chamber of a variable-thrust ion thruster, characterized in that, The process includes the following: Based on the on-orbit application requirements and the structural status of the ion thruster, the variable thrust adjustment range that the ion thruster can achieve is determined, and the anode gas supply flow rate at the integer thrust operating point is determined. Using particle simulation, the magnetic induction intensity and plasma discharge current combination required to output a specified value of ion beam at each integer thrust operating point under a determined anode gas supply flow rate are obtained, and the circumferential distribution characteristics of plasma density and discharge voltage parameters under the corresponding combination are obtained. For each integer target thrust operating point, magnetic induction intensity parameters that meet the preset conditions for plasma distribution uniformity and have discharge voltage below the preset threshold are selected, and a table is compiled to show the correspondence between target thrust and magnetic induction intensity. Based on the table of the correspondence between target thrust and magnetic induction intensity, optimization verification tests of magnetic induction intensity were carried out for each integer target thrust operating point. During the test, four core parameters were collected simultaneously: plasma discharge loss, voltage oscillation amplitude, discharge chamber working fluid utilization rate, and ion beam density distribution. The four core parameters under each test condition are evaluated, and the combination of magnetic induction intensity and plasma discharge current that makes plasma discharge loss meet the preset requirements, voltage oscillation amplitude is lower than the preset threshold, working fluid utilization rate meets the preset requirements, and ion beam uniformity meets the preset requirements is selected. The magnetic induction intensity corresponding to this combination is the target magnetic induction intensity at the target thrust operating point.

2. The method for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster according to claim 1, characterized in that, Define the adjustable thrust range achievable by the ion thruster, including: Based on the maximum thrust condition that the ion thruster can stably output, the impact of the plasma sputtering effect in the discharge chamber on the on-orbit life under this condition, and the maximum power constraints and application requirements that the satellite platform can provide, the upper limit threshold for the variable thrust adjustment of the ion thruster is determined. Based on the minimum thrust condition under which the ion thruster can stably output, and the impact of the plasma discharge oscillation characteristics of the discharge chamber on the safety and efficiency of the power supply under this condition, the lower limit threshold for the variable thrust adjustment of the ion thruster is determined.

3. The method for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster according to claim 2, characterized in that, Determine the anode gas supply flow rate at the integer thrust operating point, including at least one of the following flow patterns: One-to-one flow mode, meaning that each integer thrust operating point corresponds to an independent anode gas supply flow rate; One-to-many flow mode, that is, the same anode gas supply flow covers 2-3 adjacent integer thrust operating points, and the maximum number of integer thrust operating points covered by the same anode gas supply flow is 4.

4. The method for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster according to claim 1, characterized in that, The circumferential distribution characteristics of plasma density include: The circumferential distribution characteristics of plasma density at a distance of 1-3 mm downstream of the cathode shoe inside the discharge chamber, and the circumferential distribution characteristics of plasma density at a distance of 4-6 mm upstream of the gate assembly from the screen grid.

5. The method for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster according to claim 1, characterized in that, Conduct optimization and verification tests on magnetic induction intensity, including: For each integer thrust operating point, the anode gas supply flow rate is fixed, and the magnetic induction intensity and discharge current are dynamically adjusted according to a preset rule to ensure that the ion beam flow rate extracted by the thruster always matches the requirements of the current thrust operating point, thus obtaining multiple different combinations of magnetic induction intensity and discharge current.

6. The method for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster according to claim 5, characterized in that, The voltage oscillation amplitude includes the plasma discharge voltage oscillation amplitude in the discharge chamber and the voltage oscillation amplitude of the main cathode contact electrode.

7. The method for optimizing the magnetic induction intensity design of the discharge chamber of a variable-thrust ion thruster according to claim 6, characterized in that, Ion beam uniformity is calculated using the following formula: ， Where ξ is the ion beam uniformity, I bavg I is the average beam current density. bmax This represents the maximum beam current density.

8. A device for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster, characterized in that, include: The flow rate determination module is used to determine the variable thrust adjustment range that the ion thruster can achieve, and to determine the anode gas supply flow rate at the integer thrust operating point, based on the on-orbit application requirements and the structural status of the ion thruster. The combined acquisition module is used to obtain the magnetic induction intensity and plasma discharge current combination required for outputting a specified value of ion beam when each integer thrust operating point is under the determined anode gas supply flow condition, using particle simulation method, and to obtain the circumferential distribution characteristics of plasma density and discharge voltage parameters under the corresponding combination. The relation table creation module is used to select magnetic induction intensity parameters that meet the preset conditions for plasma distribution uniformity and have a discharge voltage below a preset threshold for each integer target thrust operating point, and form a table of the correspondence between target thrust and magnetic induction intensity. The optimization and verification module is used to conduct optimization and verification tests of magnetic induction intensity based on the table of the correspondence between target thrust and magnetic induction intensity for each integer target thrust operating point. During the test, four core parameters are collected simultaneously: plasma discharge loss, voltage oscillation amplitude, discharge chamber working fluid utilization rate, and ion beam density distribution. The screening and acquisition module is used to analyze the four core parameters under each test condition and screen out the combination of magnetic induction intensity and plasma discharge current that makes the plasma discharge loss meet the preset requirements, the voltage oscillation amplitude is lower than the preset threshold, the working fluid utilization rate meet the preset requirements, and the ion beam uniformity meet the preset requirements. The magnetic induction intensity corresponding to this combination is the target magnetic induction intensity at the target thrust operating point.

9. The device for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster according to claim 8, characterized in that, The flow determination module includes: Independent gas supply unit, used to adopt a one-to-one flow mode, that is, each integer thrust operating point corresponds to an independent anode gas supply flow; The multi-anode gas supply unit is used in a one-to-many flow mode, where the gas supply flow of the same anode covers 2-3 adjacent integer thrust operating points, and the maximum number of integer thrust operating points covered by the gas supply flow of the same anode is 4.

10. The device for optimizing the magnetic induction intensity of the discharge chamber of a variable-thrust ion thruster according to claim 8, characterized in that, The voltage oscillation amplitude collected by the optimization verification module includes the voltage oscillation amplitude of the plasma discharge in the discharge chamber and the voltage oscillation amplitude of the main cathode contact electrode.

11. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that, When the processor executes the computer program, it implements the method of any one of claims 1-7.

12. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the method of any one of claims 1-7.

13. A computer program product, comprising a computer program, characterized in that, When the computer program is executed by a processor, it implements the method of any one of claims 1-7.

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