Method and device for monitoring the ground ignition process of Hall thruster

Abstract

A method and device for monitoring the ground ignition process of a Hall thruster relates to the technical field of spacecraft equipment monitoring. To address the technical problem in the prior art that existing Hall thruster ignition process monitoring methods are unable to capture the details and rapid changes in the ignition process, the present invention provides a technical solution: the method includes: collecting the location and spatial evolution of the Hall thruster ignition within a vacuum tank; collecting the light beam during the Hall thruster ignition, separating the light beam according to a preset wavelength range, and collecting the light intensity and time evolution of different wavelengths; collecting the ion current density and beam divergence angle of the Hall thruster far-field plume; and determining the impact of the ignition phenomenon on plasma parameters based on the ignition location and spatial evolution, the light intensity of different wavelengths, and the ion current density and beam divergence angle. This method can be applied to the combined optoelectronic monitoring of the Hall thruster ignition process.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft equipment monitoring technology. Background Art

[0002] Electric propulsion is a relatively advanced space propulsion technology, offering the advantage of high specific impulse and currently being widely used on various spacecraft. Compared to traditional chemical propulsion, electric propulsion offers advantages such as small size, light weight, high specific impulse, and long lifespan. It can significantly reduce satellite launch costs and increase satellite lifespan, making it a research hotspot worldwide.

[0003] Hall thrusters are electromagnetic thrusters, devices that generate thrust by discharging orthogonal electromagnetic fields based on the Hall effect. The electric field along the channel and the magnetic field along the radial direction are perpendicular to each other. The magnetic field confines electrons, while the electric field accelerates and ejects ions. As advanced propulsion devices and key spacecraft components used in space systems, Hall thrusters face high demands for their lifespan and reliability in practical applications. Ensuring the long-term reliability of Hall thrusters is a key aspect of Hall thruster research. Ignition is a key factor affecting their lifespan and reliability.

[0004] Existing research uses ammeters and ICCD cameras to monitor the ignition process of Hall effect thrusters. By measuring the changes in the ammeter and recording the ignition process with an ICCD camera, the location and temporal evolution of the ignition phenomenon can be analyzed. However, this method has limited temporal resolution: the ammeter and ICCD camera method cannot provide a high enough temporal resolution to capture the details and rapid changes in the ignition process. Summary of the Invention

[0005] To solve the technical problem in the prior art of using an ammeter and an ICCD camera to monitor the ignition process of a Hall thruster, which cannot provide sufficiently high time resolution and cannot capture details and rapid changes in the ignition process, the present invention provides the following technical solutions:

[0006] A method for monitoring a ground ignition process of a Hall thruster, the method comprising:

[0007] The step of sending a pumping signal to the vacuum tank;

[0008] The step of collecting the location and spatial evolution law of the Hall thruster ignition in the vacuum tank;

[0009] The steps of collecting the light beam when the Hall thruster is ignited, separating the light beam according to a preset wavelength range, and collecting the light intensity and time evolution law of different wavelengths respectively;

[0010] The step of collecting the ion current density and beam divergence angle of the far-field plume of the Hall thruster;

[0011] The method further comprises the steps of obtaining the temporal and spatial evolution laws of the influence of the Hall thruster ignition phenomenon on plasma parameters based on the occurrence location and spatial evolution laws of the Hall thruster ignition, the light intensity of different wavelengths and the temporal evolution laws, and the ion current density and beam divergence angle of the Hall thruster far-field plume.

[0012] Furthermore, a preferred embodiment is provided, wherein the method further comprises the step of collecting the volt-ampere characteristics of the Hall thruster power supply to confirm whether sparking occurs.

[0013] Furthermore, a preferred embodiment is provided, wherein the ignition location and spatial evolution law of the Hall thruster are obtained based on ICCD camera monitoring.

[0014] Furthermore, a preferred embodiment is provided, wherein the ion current density and beam divergence angle of the far-field plume of the Hall thruster are obtained by a Faraday probe.

[0015] Furthermore, a preferred embodiment is provided, wherein the light beam is separated by a filter.

[0016] Furthermore, a preferred embodiment is provided, wherein the pumping signal reduces the air pressure in the vacuum tank to 10 - 3 Below Pa.

[0017] Furthermore, a preferred embodiment is provided in which the ignition location and spatial evolution law of the Hall thruster are collected after the Hall thruster operates stably.

[0018] Based on the same inventive concept, the present invention also provides a device for monitoring the ground ignition process of a Hall thruster, the device comprising:

[0019] A module that sends a pumping signal to the vacuum tank;

[0020] A module for collecting the location and spatial evolution of Hall thruster ignition in the vacuum tank;

[0021] A module for collecting the light beam when the Hall thruster is ignited, separating the light beam according to a preset wavelength range, and respectively collecting the light intensity and time evolution law of different wavelengths;

[0022] a module for collecting the ion current density and beam divergence angle of the far-field plume of the Hall thruster;

[0023] A module is provided for obtaining the temporal and spatial evolution of the influence of the Hall thruster ignition phenomenon on plasma parameters based on the location and spatial evolution of the Hall thruster ignition, the light intensity of different wavelengths and the temporal evolution, and the ion current density and beam divergence angle of the Hall thruster far-field plume.

[0024] Based on the same inventive concept, the present invention also provides a computer storage medium for storing a computer program. When the computer program is read by a computer, the computer executes the method described above.

[0025] Based on the same inventive concept, the present invention also provides a computer, comprising a processor and a storage medium. When the processor reads the computer program stored in the storage medium, the computer executes the method described above.

[0026] Compared with the prior art, the advantages and benefits of the technical solution provided by the present invention are:

[0027] The present invention provides a method for monitoring the ground ignition process of a Hall thruster, using a photomultiplier tube (PMT) and an ICCD camera. This method enables high temporal and spatial resolution monitoring of the Hall thruster ignition process. The PMT's rapid response enables high temporal resolution of Hall thruster ignition characteristics, while the ICCD camera compensates for its limited spatial resolution.

[0028] The method for monitoring the ground-based ignition process of a Hall thruster, provided by this invention, uses a Faraday probe to obtain the ion current density and beam divergence angle of the Hall thruster's far-field plume. This can help analyze the impact of the Hall thruster's ignition effect on the plume divergence angle.

[0029] The method for monitoring the ground ignition process of a Hall thruster provided by the present invention uses a combined optoelectronic monitoring method to accurately monitor the ignition process of the Hall thruster, especially with its precise temporal and spatial resolution capabilities. This helps to understand the ignition mechanism and principle of the Hall thruster, thereby providing a reference for the high-reliability design of the Hall thruster and its impact on satellites.

[0030] The method for monitoring the ground-based ignition process of a Hall thruster, provided by this invention, utilizes the fast response speed of a photomultiplier tube to obtain Hall thruster ignition characteristics with high temporal resolution. It also utilizes an ICCD camera to compensate for its limited spatial resolution. Furthermore, a Faraday probe is combined to analyze the impact of the Hall thruster ignition effect on far-field plume characteristics. This method combines high temporal resolution with spatial resolution, enabling spatiotemporal analysis of Hall thruster ignition characteristics.

[0031] The Hall thruster ground ignition process monitoring method provided by the present invention can be applied to perform photoelectric joint monitoring of the Hall thruster ignition process to understand the ignition mechanism and principle of the Hall thruster, and provide a reference for the high-reliability design of the Hall thruster and its impact on satellites. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 This is a flow chart of a method for monitoring the ground ignition process of a Hall thruster;

[0033] Figure 2 This is a schematic diagram of the structure of the optoelectronic combined detection device for the ground ignition process of the Hall thruster;

[0034] Among them, 1 represents the Hall thruster vacuum tank, 2 represents the Hall thruster, 3 represents the Hall thruster power supply assembly, 4 represents the light receiver, 5 represents the spectrometer, 6 represents the filter, 7 represents the photomultiplier tube, 8 represents the ICCD camera, and 9 represents the Faraday probe. DETAILED DESCRIPTION

[0035] In order to make the advantages and benefits of the technical solution provided by the present invention more clearly reflected, the technical solution provided by the present invention is now further described in detail with reference to the accompanying drawings, specifically:

[0036] Embodiment 1: This embodiment provides a method for monitoring the ground ignition process of a Hall thruster, the method comprising:

[0037] The step of sending a pumping signal to the vacuum tank;

[0038] The step of collecting the location and spatial evolution law of the Hall thruster ignition in the vacuum tank;

[0039] The steps of collecting the light beam when the Hall thruster is ignited, separating the light beam according to a preset wavelength range, and collecting the light intensity and time evolution law of different wavelengths respectively;

[0040] The step of collecting the ion current density and beam divergence angle of the far-field plume of the Hall thruster;

[0041] The method further comprises the steps of obtaining the temporal and spatial evolution laws of the influence of the Hall thruster ignition phenomenon on plasma parameters based on the occurrence location and spatial evolution laws of the Hall thruster ignition, the light intensity of different wavelengths and the temporal evolution laws, and the ion current density and beam divergence angle of the Hall thruster far-field plume.

[0042] Specifically:

[0043] The Hall thruster is housed within a vacuum tank and connected to the thruster power supply and air supply unit. The optoelectronic monitoring system includes a wide-range light receiver, optical fiber, filters, a photomultiplier tube (PMT), an ICCD camera, a Faraday probe, and an ammeter. The light receiver is housed within the vacuum tank and connected to the PMT via optical fiber and filters of different wavelengths. The Faraday probe is housed within the vacuum tank, oriented toward the axis of the Hall thruster.

[0044] The air pressure in the vacuum tank of the Hall thruster is 10 -3 Pa and below.

[0045] The number of the photomultiplier tubes is at least 4, the number of the filters is at least 4, and the bandwidth of the filters is no more than 5 nm.

[0046] like Figure 1 As shown, the optoelectronic combined monitoring method for the Hall thruster ignition process includes the following steps:

[0047] Step 1: Pump down the vacuum tank of the Hall thruster to below the set pressure, ignite the thruster, and after the thruster runs stably, use an ammeter to obtain the volt-ampere characteristics of the Hall thruster power supply to confirm whether ignition occurs.

[0048] Step 2: Use an ICCD camera to monitor the Hall thruster and determine the location and spatial evolution of the spark phenomenon.

[0049] Step 3: Use filters to separate the light beams collected by the light receiver into different wavelengths, and use photomultiplier tubes to obtain the light intensity of different wavelengths and their time evolution.

[0050] Step 4: Use a Faraday probe to obtain the ion current density and beam divergence angle of the Hall thruster far-field plume.

[0051] Step 5: Combine the data measured in the above steps to obtain the temporal and spatial evolution laws of the influence of the Hall thruster ignition phenomenon on the plasma parameters.

[0052] Embodiment 2: This embodiment further limits the method for monitoring the ground ignition process of a Hall thruster provided in Embodiment 1. The method further includes: collecting the volt-ampere characteristics of the Hall thruster power supply to confirm whether ignition occurs.

[0053] Implementation method three: This implementation method further limits the method for monitoring the ground ignition process of a Hall thruster provided in implementation method one. The ignition location and spatial evolution law of the Hall thruster are obtained by monitoring with an ICCD camera.

[0054] Embodiment 4: This embodiment further limits the method for monitoring the ground ignition process of a Hall thruster provided in Embodiment 1. The ion current density and beam divergence angle of the far-field plume of the Hall thruster are obtained by a Faraday probe.

[0055] Embodiment 5: This embodiment further limits the method for monitoring the ground ignition process of a Hall thruster provided in Embodiment 1, and separates the light beam by a filter.

[0056] Implementation 6: This implementation further limits the method for monitoring the ground ignition process of the Hall thruster provided in Implementation 1. The pumping signal reduces the pressure in the vacuum tank to 10 -3 Below Pa.

[0057] Embodiment 7: This embodiment further limits the method for monitoring the ground ignition process of a Hall thruster provided in Embodiment 1. The ignition location and spatial evolution law of the Hall thruster are collected after the Hall thruster is running stably.

[0058] Embodiment 8: This embodiment provides a device for monitoring the ground ignition process of a Hall thruster, the device comprising:

[0059] A module that sends a pumping signal to the vacuum tank;

[0060] A module for collecting the location and spatial evolution of Hall thruster ignition in the vacuum tank;

[0061] A module for collecting the light beam when the Hall thruster is ignited, separating the light beam according to a preset wavelength range, and respectively collecting the light intensity and time evolution law of different wavelengths;

[0062] a module for collecting the ion current density and beam divergence angle of the far-field plume of the Hall thruster;

[0063] A module is provided for obtaining the temporal and spatial evolution of the influence of the Hall thruster ignition phenomenon on plasma parameters based on the location and spatial evolution of the Hall thruster ignition, the light intensity of different wavelengths and the temporal evolution, and the ion current density and beam divergence angle of the Hall thruster far-field plume.

[0064] Implementation method 9: This implementation method provides a computer storage medium for storing a computer program. When the computer program is read by a computer, the computer executes the method provided in implementation method 1.

[0065] Implementation 10: This implementation provides a computer, including a processor and a storage medium. When the processor reads the computer program stored in the storage medium, the computer executes the method provided in Implementation 1.

[0066] Implementation Method 11: Combination Figure 1-2 This embodiment further illustrates the above-mentioned technical solution through specific examples, specifically:

[0067] See also Figure 2 This embodiment describes an optoelectronic monitoring device for the ignition process of a Hall thruster. A Hall thruster 2 is disposed within a vacuum tank 1 and connected to a Hall thruster power supply assembly 3. The optical monitoring device includes an ICCD camera 8 and a photomultiplier tube 7. The photomultiplier tube 7 is connected to filters 6 of different wavelengths, which are connected to the channels of a spectrometer 5. The spectrometer 5 is connected to a light receiver 4 located adjacent to the Hall thruster. The electrical monitoring device includes an ammeter within the Hall thruster power supply assembly 3 and a Faraday probe 9. The Faraday probes 9 are arranged radially and at regular intervals along the axis of the Hall thruster 2.

[0068] The central wavelengths of the filters 6 are respectively 460 nm, 823 nm, 828 nm, and 881 nm.

[0069] The Faraday probe 9 is a naked Faraday probe.

[0070] This embodiment is a photoelectric combined monitoring method for the ignition process of a Hall thruster. Figure 1 As shown, the monitoring method monitors plasma parameters and beam characteristics based on a photoelectric combined monitoring device, and specifically includes the following steps.

[0071] Step 1: Place the Hall thruster 2, the light receiver 4 and the Faraday probe assembly into the vacuum tank 1 and connect the relevant circuits to evacuate the Hall thruster vacuum tank 1 to the set pressure of 10 -3 Pa and below, ignite the thruster. After the thruster runs stably, use an ammeter to obtain the volt-ampere characteristics of the Hall thruster power supply assembly 3 to confirm whether there is any ignition.

[0072] Step 2: Use the ICCD camera 8 to monitor the Hall thruster 2, and when the ignition phenomenon of the Hall thruster 2 occurs, determine the location and spatial evolution law of the occurrence.

[0073] Step 3: Use a light receiver 4 to collect the emitted light from the Hall thruster 2. The light is evenly split into four beams by a beam splitter 5. After passing through filters 6 at 460nm, 823nm, 828nm, and 881nm, it is transmitted to a photomultiplier tube 7. By analyzing the response data of the photomultiplier tube, the intensity of the emitted light at different wavelengths can be determined. By comparing the light intensity data at different wavelengths, three different spectral line ratios can be obtained: 881nm / 823nm, 823nm / 828nm, and 460nm / 828nm. The theoretical spectral line ratios are calculated using a collision radiation model and fitted using the least squares method to obtain information such as electron temperature and plasma density. Taking advantage of the fast response speed of the photomultiplier tube, the plasma parameters of the Hall thruster ignition process can be obtained with high temporal resolution, thereby analyzing the temporal evolution characteristics of the Hall thruster ignition process.

[0074] Step 4: The ion plume divergence angle of the electric propulsion device is defined as the angle between the 95% boundary line of the total ion beam flux and the central axis of the plume. The most critical parameter is the ion current represented by the ion beam flux, and the most reliable probe device for detecting ion current is the Faraday probe in this platform. The Faraday probe consists of an inner collector and an outer shield, both of which are connected to a -25V bias voltage. The main function of the collector bias voltage is to guide the ions to flow toward the collector, generate a current signal, and measure the ion flux corresponding to its position. Using the position of the central Faraday probe and the position of the edge Faraday probe at 5% of the central Faraday probe ion flux, the thruster plume divergence angle can be calculated using trigonometric functions. This allows the influence of the Hall thruster ignition effect on the plume divergence angle to be analyzed.

[0075] Step 5: Combined with the data measured in the above steps, obtain the temporal and spatial evolution of the influence of the Hall thruster ignition phenomenon on the plasma parameters and its possible impact on the satellite.

[0076] The above further describes the technical solution provided by the present invention in detail through several specific embodiments in order to highlight the advantages and benefits of the technical solution provided by the present invention. However, the several specific embodiments described above are not intended to limit the present invention. Any reasonable modification and improvement of the present invention, combination of embodiments and equivalent replacement based on the spirit and principles of the present invention should be included in the scope of protection of the present invention.

[0077] The descriptions in this specification refer only to preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Furthermore, reference to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples" implies that a specific feature, structure, material, or characteristic described in conjunction with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative descriptions of these terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or N embodiments or examples. Furthermore, those skilled in the art may combine and integrate the different embodiments or examples described in this specification, as well as features from different embodiments or examples, unless otherwise specified. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed to indicate or imply relative importance or to implicitly specify the number of the technical features indicated. Therefore, features designated "first" or "second" may explicitly or implicitly include at least one of these features. In the description of the present invention, "N" means at least two, for example, two, three, etc., unless otherwise specifically defined. Any process or method description in a flowchart or otherwise described herein can be understood to represent a module, segment, or portion of code comprising one or more executable instructions for implementing a custom logic function or process, and the scope of the preferred embodiments of the present invention includes alternative implementations in which functions may be performed in a different order than shown or discussed, including substantially simultaneously or in reverse order depending on the functions involved, as will be understood by those skilled in the art to which the embodiments of the present invention pertain. The logic and / or steps shown in a flowchart or otherwise described herein, for example, can be considered as a sequenced list of executable instructions for implementing the logic function, and can be embodied in any computer-readable medium for use by an instruction execution system, apparatus, or device (e.g., a computer-based system, a system including a processor, or other system that can fetch and execute instructions from an instruction execution system, apparatus, or device), or for use in conjunction with such instruction execution systems, apparatuses, or devices. For purposes of this specification, a "computer-readable medium" can be any device that can contain, store, communicate, propagate, or transmit a program for use by an instruction execution system, apparatus, or device, or in conjunction with such instruction execution systems, apparatuses, or devices. More specific examples (a non-exhaustive list) of computer-readable media include the following: an electrical connection having one or N wires (electronic device), a portable computer disk cartridge (magnetic device), a random access memory (RAM), a read-only memory (ROM), an erasable and programmable read-only memory (EPROM or flash memory), a fiber optic device, and a portable compact disc read-only memory (CDROM).Furthermore, the computer-readable medium may even be paper or other suitable medium on which the program is printed, since the program can be obtained electronically, for example, by optically scanning the paper or other medium, followed by editing, deciphering, or processing in other suitable ways as necessary, and then stored in a computer memory. It should be understood that various aspects of the present invention may be implemented using hardware, software, firmware, or a combination thereof. In the above embodiment, the N steps or methods may be implemented using software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented using hardware, as in another embodiment, any one or a combination of the following technologies known in the art may be used: a discrete logic circuit having logic gates for implementing logic functions on data signals, an application-specific integrated circuit having suitable combinational logic gates, a programmable gate array (PGA), a field-programmable gate array (FPGA), etc.

[0078] Those skilled in the art will appreciate that all or part of the steps carried out in the above-mentioned embodiment method can be completed by instructing the relevant hardware through a program, and the program can be stored in a computer-readable storage medium, which, when executed, includes one or a combination of the steps of the method embodiment. In addition, the functional units in the various embodiments of the present invention can be integrated into a processing module, or each unit can exist physically alone, or two or more units can be integrated into one module. The above-mentioned integrated module can be implemented in the form of hardware or in the form of a software functional module. If the integrated module is implemented in the form of a software functional module and sold or used as an independent product, it can also be stored in a computer-readable storage medium.

Claims

1. A method for monitoring the ground ignition process of a Hall thruster, characterized in that: The method comprises: The step of sending a pumping signal to the vacuum tank; The step of collecting the location and spatial evolution law of the Hall thruster ignition in the vacuum tank; The steps of collecting the light beam when the Hall thruster is ignited, separating the light beam according to a preset wavelength range, and collecting the light intensity and time evolution law of different wavelengths respectively; The step of collecting the ion current density and beam divergence angle of the far-field plume of the Hall thruster; The step of obtaining the temporal and spatial evolution laws of the influence of the Hall thruster ignition phenomenon on plasma parameters based on the occurrence position and spatial evolution laws of the Hall thruster ignition, the light intensity of different wavelengths and the temporal evolution laws, and the ion current density and beam divergence angle of the Hall thruster far-field plume; Specifically, an ICCD camera is used to monitor the Hall thrust, and when the Hall thruster ignition occurs, its location and spatial evolution pattern are determined; The light emitted by the Hall thruster is collected using a light-collecting mirror and evenly divided into four beams by a spectrometer. After passing through filters at 460nm, 823nm, 828nm, and 881nm, it is transmitted to the photomultiplier tube. By analyzing the response data of the photomultiplier tube, the intensity of the emitted light at different wavelengths is obtained. By comparing the light intensity data at different wavelengths, three different spectral line ratios are obtained: 881nm / 823nm, 823nm / 828nm, and 460nm / 828nm. The Faraday probe consists of an inner collector and an outer shield. Both the collector and the shield are connected to a bias voltage of -25V. The ion current density and beam divergence angle of the far-field plume of the Hall thruster are measured.

2. The method for monitoring the ground ignition process of a Hall thruster according to claim 1, characterized in that: The method further includes the step of collecting the volt-ampere characteristics of the Hall thruster power supply to confirm whether sparking occurs.

3. The method for monitoring the ground ignition process of a Hall thruster according to claim 1, characterized in that: The ignition location and spatial evolution law of the Hall thruster are obtained through ICCD camera monitoring.

4. The method for monitoring the ground ignition process of a Hall thruster according to claim 1, characterized in that: The ion current density and beam divergence angle of the far-field plume of the Hall thruster are obtained through a Faraday probe.

5. The method for monitoring the ground ignition process of a Hall thruster according to claim 1, characterized in that: The light beams are separated by filters.

6. The method for monitoring the ground ignition process of a Hall thruster according to claim 1, characterized in that: The pumping signal reduces the air pressure in the vacuum tank to 10 -3 Below Pa.

7. The method for monitoring the ground ignition process of a Hall thruster according to claim 1, characterized in that: The ignition occurrence position and spatial evolution law of the Hall thruster are collected after the Hall thruster operates stably.

8. Hall thruster ground ignition process monitoring device, characterized in that: For implementing the method for monitoring the ground ignition process of a Hall thruster according to claim 1, the device comprises: A module that sends a pumping signal to the vacuum tank; A module for collecting the location and spatial evolution of Hall thruster ignition in the vacuum tank; A module for collecting the light beam when the Hall thruster is ignited, separating the light beam according to a preset wavelength range, and respectively collecting the light intensity and time evolution law of different wavelengths; a module for collecting the ion current density and beam divergence angle of the far-field plume of the Hall thruster; A module is provided for obtaining the temporal and spatial evolution of the influence of the Hall thruster ignition phenomenon on plasma parameters based on the location and spatial evolution of the Hall thruster ignition, the light intensity of different wavelengths and the temporal evolution, and the ion current density and beam divergence angle of the Hall thruster far-field plume.

9. A computer storage medium for storing a computer program, characterized in that When the computer program is read by a computer, the computer executes the method according to claim 1 .

10. A computer comprising a processor and a storage medium, characterized in that When the processor reads the computer program stored in the storage medium, the computer executes the method according to claim 1 .

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