An air-breathing electric propulsion system and supply method with multiple working fluid supply modes

Abstract

This invention relates to a multi-propellant supply mode air-breathing tangential field electric propulsion system and its supply method. The invention pertains to the technical field of air-breathing electric propulsion systems. The system includes: an electric thruster and collection device module, a microwave cathode module, a xenon gas storage and supply module, and a control and energy supply module. The multi-propellant supply mode air-breathing tangential field electric propulsion system provided by this invention, in addition to fully utilizing the thin atmosphere of the ultra-low Earth orbit (ULE), enhances the adaptability of the electric thruster under complex operating conditions by utilizing its own xenon propellant. Beyond ULE air-breathing electric propulsion missions, the xenon propellant it carries enables it to operate over a wider orbital range, covering the orbital range of traditional xenon electric propulsion and ULE space above 150 km.

Description

Technical Field

[0001] This invention relates to the field of air-breathing electric propulsion system technology, specifically an air-breathing field-cutting electric propulsion system and its supply method with multiple working fluid supply modes. Background Technology

[0002] Satellites operating in ultra-low Earth orbit have inherent advantages such as low launch cost, high imaging resolution, and short communication latency, and hold enormous application potential and profound strategic significance.

[0003] However, as the orbit decreases, atmospheric drag increases dramatically, resulting in insufficient lift and excessive residual drag during ultra-low Earth orbit (ULE) spaceflight. This makes it a no-go zone for both aircraft and spacecraft, hindering their long-term operation. To date, among the propulsion schemes proposed by international researchers for ULE drag compensation, air-breathing electric propulsion is the most prominent and popular candidate. This scheme eliminates the need for a propellant, utilizing the thin atmosphere of the orbital environment as the propellant source. Thrust is generated through processes such as intake, compression, heating, ionization, and acceleration, thereby significantly mitigating the limitations imposed by the propellant on the spacecraft's on-orbit lifespan.

[0004] Satellites employing air-breathing electric propulsion systems can, under ideal conditions, turn adversity into advantage, continuously converting drag into thrust and achieving an ultra-long on-orbit lifespan. However, air-breathing electric propulsion systems operating in very low Earth orbit still face stringent limitations due to the following environmental factors:

[0005] 1. The atmospheric working fluid is difficult to ionize and exhibits complex physicochemical reactions. According to existing research, the main components of the VLEO atmosphere are oxygen atoms, nitrogen molecules, oxygen molecules, and nitrogen atoms. Its first ionization energy is higher than that of xenon working fluid used in conventional electric propulsion. Furthermore, under different energy excitation states, more than 120 physicochemical reactions, including dissociation, recombination, and combination, occur between the two elements. Therefore, the performance of the atmospheric working fluid is poor, and its ionization rate needs to be significantly improved.

[0006] 2. The atmospheric properties in ultra-low Earth orbit (ULEO) are highly variable. Solar activity, geomagnetic storms, and other factors can cause periodic and dramatic changes in atmospheric density in ULEO. Non-spherical perturbations can also cause satellites to cross multiple atmospheric isodense surfaces while flying in the same orbit. Whether the atmospheric molecular density or pressure is high or low, it can make it difficult for air-breathing electric propulsion satellites to propel themselves normally. In cases of low atmospheric density, problems such as poor gas collection, failure to ignite, failure to discharge properly, and a large thrust deficit may occur. In cases of high atmospheric density, problems such as excessive drag and overheating of the propulsion system under prolonged high-pressure operation may occur.

[0007] 3. The working fluid in the atmosphere has strong oxidizing properties. Atomic oxygen, which constitutes the majority of the composition of the ultra-low orbit atmosphere, will corrode propulsion system components that come into direct contact with it, such as the grid ion thruster, potentially leading to grid corrosion failure.

[0008] In addition, satellites using air-breathing electric propulsion systems have certain shortcomings because the ultra-low orbit atmospheric working fluid collection device 12 cannot pressurize and store excess atmospheric working fluid when operating at high atmospheric density, and the single passive collection structure cannot control the flow rate or adjust the thrust.

[0009] Although previous studies have proposed an active collection scheme using molecular pumps, the limited power provided by the solar cell array module 7 would further reduce the available power of the satellite payload, impacting satellite performance. In addition, this scheme is costly and complex, and has significant drawbacks. Summary of the Invention

[0010] This invention aims to address the problems of unstable thrust in air-breathing electric propulsion caused by the variable atmospheric properties in ultra-low Earth orbit (ULE), insufficient thrust during emergency maneuvers, and difficulties in ignition under low-density atmosphere, which limit the operational duration of spacecraft in ULE. Therefore, this invention proposes an air-breathing tangential field electric propulsion system with multiple propellant supply modes and a multi-mode supply method. Furthermore, in addition to ULE air-breathing electric propulsion missions, this invention also maintains the capability for conventional electric propulsion using xenon propellant in higher orbits.

[0011] This invention provides the following technical solutions:

[0012] A multi-propellant supply mode air-breathing field-cutting electric propulsion system, the system comprising:

[0013] Electric thruster and collection device module, microwave cathode module, xenon gas storage and supply module, and control and energy supply module;

[0014] The electric thruster and collection device module includes a microwave-DC hybrid ionization field-cutting thruster and an ultra-low orbit atmospheric working fluid collection device connected to the discharge channel inlet of the microwave-DC hybrid ionization field-cutting thruster; the microwave cathode module is used to neutralize the high-speed ion plume ejected by the microwave-DC hybrid ionization field-cutting thruster.

[0015] The control and energy supply module includes a DC power source module, a microwave power source module, and a power supply processor module that are electrically connected to the onboard control system via a communication and power supply bus.

[0016] The DC power source module is electrically connected to the microwave-DC hybrid ionization field thruster and microwave cathode module, and provides electrical energy; the microwave power source module is electrically connected to the microwave-DC hybrid ionization field thruster and microwave cathode module, and provides the microwave power required for working fluid ionization; the supply processor module and xenon gas storage and supply module are electrically connected, and are used to control the xenon gas flow rate supplied by the xenon gas storage and supply module.

[0017] The xenon gas storage and supply module is connected to the gas input terminals of the microwave-DC hybrid ionization field thruster and the microwave cathode module, respectively.

[0018] Preferably, the microwave-DC hybrid ionization field-cutting thruster includes a thruster housing with a cylindrical main body, a microwave feed interface reserved on the housing, three permanent magnets arranged along the central axis inside the housing, a cylindrical discharge channel installed on the central axis inside the thruster housing, a cylindrical monopole antenna inserted into the channel through the microwave feed interface between the three permanent magnets, a high transparency anode installed at the upstream entrance of the channel on the central axis, an insulating ceramic installed upstream of the high transparency anode on the central axis, and an annular gas homogenizer installed upstream of the insulating ceramic on the central axis.

[0019] The anode is electrically connected to the positive terminal of the DC power source module, the cylindrical monopole antenna is electrically connected to the microwave power source module, and the annular gas homogenizer is connected to the ultra-low orbit atmospheric working fluid collection device and the xenon gas storage and supply module.

[0020] Preferably, the ultra-low orbit atmospheric propellant collection device includes a parabolic-shaped outer shell and a rectification grid set in the windward direction of satellite flight, and the ultra-low orbit atmospheric propellant collection device is connected to the thruster shell.

[0021] Preferably, the microwave cathode module includes a cylindrical shell, an outlet plate installed at the front end of the cylindrical shell, a ring-shaped permanent magnet coaxially installed inside the cylindrical shell, a base plate installed at the rear end of the cylindrical shell, a substrate coaxially installed inside the ring-shaped permanent magnet and having a reserved gas inlet, and a cathode antenna installed at the axis of the substrate.

[0022] The substrate is connected to the xenon gas storage and supply module; the cylindrical shell is electrically connected to the negative terminal of the DC power source module, and the cathode antenna is electrically connected to the microwave power source module.

[0023] Preferably, the discharge channel and the insulating ceramic material are hexagonal boron nitride ceramics, and the materials of the three-stage permanent magnet and the annular permanent magnet are samarium cobalt 2:17 permanent magnets;

[0024] The cross-sectional shape of the rectifier grid is square, circular, fan-shaped, equilateral triangular, or regular hexagonal.

[0025] The cathode antenna is a disk-shaped, L-shaped, F-shaped, cylindrical monopole or a double-arm dipole;

[0026] The discharge channel is shaped as a cylinder, a partially expanding cylinder, a fully expanding platform, or a stepped expanding cylinder.

[0027] A method for supplying a multi-propellant supply mode air-breathing electric propulsion system, the method comprising the following steps:

[0028] Step 1: Obtain three environmental parameters, namely the spacecraft orbital altitude H, atmospheric density ρ, and solar radiation intensity T, as well as four system state parameters, namely the intake flow rate A of the ultra-low orbit atmospheric propellant collection device, the pressure B of the xenon storage and supply system, the anode voltage V, and the microwave power P, through the spaceborne sensor, and select the core operating condition parameters as the neural network input;

[0029] Step 2: Normalize the above parameters, map them to the 0-1 interval, and eliminate the influence of dimensional differences on neural network training;

[0030] Step 3: Adopt an improved BP neural network as the core decision-making model;

[0031] Step 4: Obtain training data through ground simulation and experiments, and divide them into a training set and a validation set according to the ratio of 8:2;

[0032] Step 5: Initialize the network weights using the Xavier initialization method;

[0033] Step 6: Online allocate the execution process;

[0034] Step 7: Feedback correction. During on-orbit operation, set the frequency of collecting thrust values according to the required accuracy of the mission. The ground monitoring center regularly receives the actual operating conditions and thrust data transmitted back by the satellite, retrains the model using the new data, and updates the model parameters in the satellite system through telemetry commands to achieve on-orbit update.

[0035] Preferably, real-time acquisition: Obtain the operating condition parameters in real time through the sensor, and perform normalization processing according to the method in Step 2;

[0036] Ratio prediction: Input the normalized parameters into the trained neural network, and output the xenon supply ratio K_pred;

[0037] Execution adjustment:

[0038] When K_pred = 1, the supply processor module fully opens the xenon storage and supply module, and uses full-flow xenon supply;

[0039] When K_pred = 0, the supply processor module fully closes the xenon storage and supply module, and uses pure atmosphere supply;

[0040] If 0 < K_pred < 1, the supply processor module opens the xenon storage and supply module according to the ratio, where the xenon flow rate = K_pred * the maximum xenon flow rate M1.

[0041] Preferably, Step 2 is specifically:

[0042] Eliminate the influence of dimensional differences on neural network training. The formula is:

[0043]

[0044] Where X is the original parameter value, X min and X max These are the minimum and maximum values ​​of the parameter within the design range, respectively.

[0045] A computer-readable storage medium having a computer program stored thereon, the program being executed by a processor for implementing a supply method for an air-breathing, cross-field electric propulsion system with a multi-propellant supply mode.

[0046] A computer device includes a memory and a processor, the memory storing a computer program, and the processor executing the computer program to implement a supply method for an air-breathing, cross-field electric propulsion system with a multi-propellant supply mode.

[0047] The present invention has the following beneficial effects:

[0048] The multi-propellant supply mode air-breathing tangential field electric propulsion system provided by this invention, in addition to making full use of the thin atmosphere of the VLEO (Ultra-Low Earth Orbit), enhances the adaptability of the electric thruster under complex operating conditions by utilizing its own xenon propellant. Compared to air-breathing electric propulsion systems with a single propellant source, the multi-propellant supply mode air-breathing tangential field electric propulsion system designed in this invention has stronger adaptability to various complex propulsion situations, especially sudden changes in atmospheric density and emergency maneuvers. Furthermore, in addition to VLEO air-breathing electric propulsion missions, the xenon propellant it carries enables it to cover a wider orbital range, encompassing the orbital range of traditional xenon electric propulsion and VLEO space above 150 km.

[0049] The microwave-DC hybrid ionization field-cutting thruster provided by this invention possesses the wide-range adjustable discharge power characteristic of traditional field-cutting thrusters, while also taking into account the low-pressure discharge characteristics of the microwave electron cyclotron resonance ionization method. The discharge pressure range spans three orders of magnitude, matching the variable characteristics of the ultra-low orbit atmosphere. Furthermore, due to the strong confinement effect of the strong magnetic field on electrons, the microwave-DC hybrid ionization field-cutting thruster can provide a higher anode voltage compared to Hall thrusters, achieving a higher specific impulse while maintaining a high thrust-to-power ratio.

[0050] The microwave-DC hybrid ionization field thruster and microwave cathode provided by this invention both employ microwave electron cyclotron resonance ionization. This method selects a frequency of 4.2 GHz, which, compared to frequencies of 2.45 GHz and lower, can generate plasma with higher density. At the same time, the higher electron temperature is more advantageous for dissociating high-bond-energy molecules such as N2 and O2 in atmospheric working fluids.

[0051] The present invention provides a multi-propellant supply mode air-breathing tangential electric propulsion system. Under the control of the supply processor module, the xenon gas storage and supply module supplies gas to both the thruster and the microwave cathode. A gas homogenizer is present on the thruster side to avoid local density inhomogeneity of the xenon gas, improve the uniformity of the microwave discharge plasma, and thus enhance the symmetry of the thrust distribution of the system.

[0052] The multi-propellant supply mode air-breathing field electric propulsion system provided by this invention uses hexagonal boron nitride ceramic structure for all non-metallic components that are in direct contact with the atmospheric propellant. These components are chemically stable and not easily corroded. Metallic components that are in direct contact with the atmospheric propellant, such as the ultra-low orbit atmospheric propellant collection device and the anode, are made of corrosion-resistant alloy materials to improve their service life in atomic oxygen environments.

[0053] This invention utilizes the nonlinear fitting capability of neural networks to respond in real time to dynamic changes in complex operating conditions such as orbital altitude and atmospheric density. It achieves higher thrust accuracy than traditional fixed threshold control methods. The model is lightweight with only 21 neurons, reducing the time required for a single inference. It can operate efficiently on the limited onboard computing resources of spacecraft without relying on real-time ground control, thus enhancing the autonomy of mission execution.

[0054] This invention provides a multi-mode power supply method for an air-breathing, field-cutting electric propulsion system with multiple working propellant supply modes. The preset control scheme includes auxiliary ignition mode, low-thrust-shortage mode, high-thrust-shortage mode, emergency maneuver mode, and a custom mode. It fully considers various fault scenarios, further enhancing system reliability based on neural network methods. The custom mode allows for manual takeover at any time, providing a reliable power source and safety guarantee for ultra-low Earth orbit satellite missions. Attached Figure Description

[0055] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0056] Figure 1 The diagram shown is a schematic representation of an embodiment of the air-breathing, field-cutting electric propulsion system with a multi-propellant supply mode according to the present invention.

[0057] Among them, 81-Ultra-low orbit atmospheric working fluid flow, 11-Microwave-DC hybrid ionization field thruster, 12-Ultra-low orbit atmospheric working fluid collection device, 2-Microwave cathode module, 3-Xenon gas storage and supply module, 4-Control and energy supply module, 41-DC power source module, 42-Microwave power source module, 43-Supply processor module, 5-Communication and power supply bus.

[0058] Figure 2 The diagram shown is a schematic diagram of the principle of the air-breathing electric propulsion satellite of the present invention.

[0059] Among them, 81-ultra-low orbit atmospheric working fluid flow, 12-ultra-low orbit atmospheric working fluid collection device, 11-electric thruster, 6-satellite main module, 7-solar cell array module, 82-plunge;

[0060] Figure 3 The diagram shows a schematic representation of the structure of the microwave cathode in an embodiment of the air-breathing, field-cutting electric propulsion system with multi-working-propellant supply mode of the present invention.

[0061] Among them, 21-cylindrical shell, 22-lead-outlet plate, 23-ring-shaped permanent magnet, 24-bottom plate, 25-substrate, 26-cathode antenna;

[0062] Figure 4 The diagram shows a structural schematic of an ultra-low orbit atmospheric working fluid collection device in an embodiment of the multi-working fluid supply mode of the present invention's air-breathing, field-cutting electric propulsion system.

[0063] Figure 5 The diagram shows a microwave-DC hybrid ionization thruster in an embodiment of the multi-propellant supply mode air-breathing tangential electric propulsion system of the present invention.

[0064] Among them, 11-microwave-DC hybrid ionization field-cutting thruster, 111-thruster housing, 112-microwave feed interface, 113-three-stage permanent magnet, 114-cylindrical discharge channel, 115-cylindrical monopole antenna, 116-high transparency anode, 117-insulating ceramic, 118-gas homogenizer, 121-parabolic housing, 112-rectifier grid;

[0065] Figure 6 This is a schematic diagram showing the shape of the cathode antenna in the microwave cathode in an embodiment of the air-breathing, field-cutting electric propulsion system with multi-propellant supply mode of the present invention.

[0066] Figure 7 The diagram shows the shape of the rectifier grid in an embodiment of the air-breathing, field-cutting electric propulsion system with multi-propellant supply mode of the present invention.

[0067] Figure 8 The diagram shows the cross-sectional shape of the discharge channel of the microwave-DC hybrid ionization field thruster in this invention. Detailed Implementation

[0068] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0069] The present invention will be described in detail below with reference to specific embodiments. Specific Implementation Example 1:

[0071] according to Figures 1 to 8 As shown, the specific optimized technical solution adopted by the present invention to solve the above-mentioned technical problems is: The present invention relates to an air-breathing field electric propulsion system and supply method with multiple working fluid supply modes.

[0072] This invention provides an air-breathing, field-cutting electric propulsion system with multiple working propellant supply modes, the system comprising:

[0073] Includes electric thruster and collection device module 1, microwave cathode module 2, xenon gas storage and supply module 3, and control and energy supply module 4;

[0074] The electric thruster and collection device module 1 includes a microwave-DC hybrid ionization field-cutting thruster 11 and an ultra-low orbit atmospheric working fluid collection device 12 connected to the discharge channel inlet of the microwave-DC hybrid ionization field-cutting thruster 11; the microwave cathode module 2 is used to neutralize the high-speed ion plume ejected by the microwave-DC hybrid ionization field-cutting thruster 11.

[0075] The control and energy supply module 4 includes a DC power source module 41, a microwave power source module 42, and a power supply processor module 43, which are electrically connected to the onboard control system via a communication and power supply bus 5.

[0076] The DC power source module 41 is electrically connected to the microwave-DC hybrid ionization field thruster 11 and the microwave cathode module 2, and provides electrical energy; the microwave power source module 42 is electrically connected to the microwave-DC hybrid ionization field thruster 11 and the microwave cathode module 2, and provides the microwave power required for working fluid ionization; the supply processor module 43 is electrically connected to the xenon gas storage and supply module 3, and is used to control the xenon gas flow rate supplied by the xenon gas storage and supply module 3;

[0077] The xenon gas storage and supply module 3 is connected to the gas input terminal of the microwave-DC hybrid ionization field thruster 11 and the microwave cathode module 2.

[0078] like Figure 2As shown, the air-breathing electric propulsion system, as a key structure of the satellite, mainly consists of the satellite main body module 6, the solar cell array module 7, and the electric thruster and collection device module 1.

[0079] The working principle of the air-breathing electric propulsion system is as follows: When the satellite is running at orbital speed in a very low orbit, a very low orbit atmospheric working fluid flow 81 is formed on the windward side. The very low orbit atmospheric working fluid flow 81 passes through the very low orbit atmospheric working fluid collection device 12 and is transmitted into the electric thruster through compression, heating and other processes. After ionization and acceleration processes, a high-speed ion plume 82 is formed, thereby generating thrust. Finally, the neutralizer module 2 neutralizes the electrical properties of the plume. Specific Implementation Example 2:

[0081] The only difference between Embodiment 2 and Embodiment 1 of this application is that:

[0082] The microwave-DC hybrid ionization field-cutting thruster 11 includes a thruster housing 111 with a cylindrical main body, a microwave feed interface 112 reserved on the housing, three permanent magnets 113 arranged along the central axis inside the housing, a cylindrical discharge channel 114 installed on the central axis inside the thruster housing 111, a cylindrical monopole antenna 115 inserted into the channel through the microwave feed interface 112 in the gap between the three permanent magnets 113, a high transparency anode 116 installed at the upstream entrance of the channel on the central axis, an insulating ceramic 117 installed upstream of the high transparency anode 116 on the central axis, and an annular gas homogenizer 118 installed upstream of the insulating ceramic 117 on the central axis.

[0083] The anode 116 is electrically connected to the positive terminal of the DC power source module 41, the cylindrical monopole antenna 115 is electrically connected to the microwave power source module 42, and the annular gas homogenizer 118 is connected to the ultra-low orbit atmospheric working fluid collection device 12 and the xenon gas storage and supply module 3. Specific Implementation Example 3:

[0085] The only difference between Embodiment 3 and Embodiment 2 of this application is that:

[0086] The ultra-low orbit atmospheric working fluid collection device 12 includes a parabolic-shaped outer shell 121 and a rectifier grid 122 set in the windward direction of satellite flight. The ultra-low orbit atmospheric working fluid collection device 12 is connected to the thruster outer shell 111. Specific Implementation Example 4:

[0088] The only difference between Embodiment 4 and Embodiment 3 of this application is that:

[0089] The microwave cathode module 2 includes a cylindrical shell 21, an outlet plate 22 installed at the front end of the cylindrical shell 21, a ring-shaped permanent magnet 23 coaxially installed inside the cylindrical shell 21, a base plate 24 installed at the rear end of the cylindrical shell 21, a substrate 25 coaxially installed inside the ring-shaped permanent magnet 23 and with a reserved gas inlet end, and a cathode antenna 26 installed at the axis of the substrate.

[0090] The substrate 25 is connected to the xenon gas storage and supply module 3; the cylindrical shell 21 is electrically connected to the negative terminal of the DC power source module 41, and the cathode antenna 26 is electrically connected to the microwave power source module 42. Specific Implementation Example 5:

[0092] The difference between Embodiment 5 and Embodiment 4 of the present invention lies only in:

[0093] The discharge channel 114 and the insulating ceramic 117 are made of hexagonal boron nitride ceramic, and the three-stage permanent magnet 113 and the annular permanent magnet 23 are made of samarium cobalt 2:17 permanent magnet.

[0094] The cross-sectional shape of the rectifier grid 122 is square, circular, fan-shaped, equilateral triangular, or regular hexagonal.

[0095] The cathode antenna 26 is a disk-shaped, L-shaped, F-shaped, cylindrical monopole or a double-arm dipole;

[0096] The discharge channel 114 is cylindrical, partially expanding cylindrical, fully expanding truncated platform, or stepped expanding cylindrical. Specific Implementation Example Six:

[0098] The difference between Embodiment Six and Embodiment Five of the present invention lies only in:

[0099] This invention provides a supply method for an air-breathing, field-cutting electric propulsion system with multiple working propellant supply modes, the method comprising the following steps:

[0100] Step 1: Obtain three environmental parameters—spacecraft orbital altitude H, atmospheric density ρ, and solar radiation intensity T—and four system state parameters—airflow rate A of the ultra-low orbit atmospheric working fluid collection device, pressure B of the xenon storage and supply system, anode voltage V, and microwave power P—through onboard sensors, and select core operating condition parameters as neural network inputs;

[0101] Step 2: Normalize the above parameters and map them to the 0-1 interval to eliminate the influence of dimensional differences on neural network training;

[0102] Step 3: Use an improved BP neural network as the core decision-making model;

[0103] Step 4: Obtain training data through ground simulation and experiments, and divide it into a training set and a validation set according to a ratio of 8:2;

[0104] Step 5: Initialize the network weights using the Xavier initialization method;

[0105] Step 6: Online allocate and execute the process;

[0106] Step 7: Feedback correction. During the on-orbit period, set the acquisition frequency of the thrust value according to the required accuracy of the task. The ground monitoring center regularly receives the actual working conditions and thrust data transmitted back by the satellite, retrains the model using the new data, and updates the model parameters in the satellite system through telemetry commands to achieve on-orbit update. Specific Embodiment Seven:

[0108] The difference between Embodiment Seven and Embodiment Six of the present invention is only that:

[0109] Real-time acquisition: Obtain the working condition parameters in real time through sensors and perform normalization processing according to the method in Step 2;

[0110] Ratio prediction: Input the normalized parameters into the trained neural network and output the xenon supply ratio K_pred;

[0111] Execution adjustment:

[0112] When K_pred = 1, the supply processor module fully opens the xenon storage and supply module, and uses full-flow xenon supply;

[0113] When K_pred = 0, the supply processor module fully closes the xenon storage and supply module, and uses pure atmosphere supply;

[0114] If 0 < K_pred < 1, the supply processor module opens the xenon storage and supply module according to the ratio, where the xenon flow rate = K_pred * maximum xenon flow rate M1.

[0115] Based on the above scheme, the satellite system has a built-in preset supply program for use as a backup plan in case of emergencies and when the method for training the neural network model in Scheme 1 fails. The process of the preset supply program is as follows:

[0116] Process 1: The satellite determines the current working condition through sensors. The on-board system outputs a working instruction to the control and energy supply module 4 through the communication and power supply bus 5. The anode voltage V is adjusted by the DC power source module 41 of the control and energy supply module 4, the microwave power P1 of the microwave-DC hybrid ionization cusp thruster 11 is adjusted by the microwave power source module 42, and the xenon flow rate M of the xenon storage and supply module 3 is adjusted by the supply processor module 43 to meet the requirements of various on-orbit working conditions;

[0117] The ratio of xenon gas supplied by the processor module 43 to the microwave-DC hybrid ionization field thruster 11 and the microwave cathode module 2 is 9:1.

[0118] Process 2:

[0119] Based on the typical operating conditions of the air-breathing electric propulsion system with multiple working fluid supply modes, the standard anode voltage V0, maximum anode voltage V1, standard microwave power P0, maximum microwave power P1, standard xenon flow rate M0, maximum xenon flow rate M1, and atmospheric stable discharge lower limit pressure P01 are clearly defined.

[0120] The requirements are V1≥2V0, P1≥5P0, and M1≥10M0.

[0121] If the current operating condition is auxiliary ignition, proceed to step A;

[0122] If the current operating condition is a low thrust gap condition, proceed to step B;

[0123] If the current operating condition is a high thrust gap condition, proceed to step C;

[0124] If the current operating condition is an emergency maneuver condition, proceed to step D;

[0125] Step A: The satellite sensor determines the ambient air pressure value. If it is less than or equal to the lower limit of atmospheric stable discharge pressure P01, the processor module 43 sets the xenon flow rate to M0, the microwave power source module 42 sets the microwave power to P0, and the DC power source module 41 sets the anode voltage to V0. This process is continued for 10 seconds, waiting for the satellite sensor to return data. If ignition is successful and thrust is generated, the operating condition is determined and subsequent steps B, C, or D are executed. If ignition is still unsuccessful, with the xenon flow rate at M0 and the microwave power at P0, the anode voltage is kept constant, and each increase of 5%M0 and 5%P0 is performed, continuing for 10 seconds while waiting for the satellite sensor to return data until successful ignition.

[0126] Step B: The DC power source module 41 sets the anode voltage to V0~150%V0, and the microwave power source module 42 sets the microwave power to P0~150%P0. If the satellite computer determines that the resistance balance requirement can be met, the xenon supply to the processor module 43 is turned off. If the satellite computer determines that the resistance balance requirement is still not met, the xenon supply to the processor module 43 is set to M0~3M0.

[0127] Step C: The DC power source module 41 sets the anode voltage to V0~150%V0, the microwave power source module 42 sets the microwave power to P0~150%P0, and the processor module 43 sets the xenon supply to 3M0~5M0. If the satellite computer determines that the resistance balance requirement can be met, the xenon supply to the processor module 43 remains unchanged. If the satellite computer determines that the resistance balance requirement is still not met, the xenon supply to the processor module 43 is set to 5M0~M1 until the resistance balance requirement is met.

[0128] Step D: After receiving the emergency maneuver signal from the satellite sensor, the DC power source module 41 sets the anode voltage to 150%V0~V1, the microwave power source module 42 sets the microwave power to 150%P0~P1, and the processor module 43 sets the xenon flow rate to M1 unchanged until the emergency maneuver command is lifted.

[0129] In addition to steps A, B, C, and D, it also includes a custom operating condition E;

[0130] Step E: After receiving the satellite command, the air-breathing electric propulsion system with multi-propellant supply mode prioritizes the execution of the custom operating conditions. The DC power source module 41 and microwave power source module 42 supply the processor module 43 with custom values ​​according to the satellite command. Specific Implementation Example 8:

[0132] The difference between Embodiment 8 and Embodiment 7 of the present invention lies only in:

[0133] Step 2 specifically involves:

[0134] The formula to eliminate the influence of dimensional differences on neural network training is:

[0135]

[0136] Where X is the original parameter value, X min and X max These are the minimum and maximum values ​​of the parameter within the design range, respectively. Specific Implementation Example Nine:

[0138] The difference between Embodiment Nine and Embodiment Eight of the present invention lies only in:

[0139] The present invention provides a computer-readable storage medium having a computer program stored thereon, which is executed by a processor to implement a supply method for an air-breathing, cross-field electric propulsion system with a multi-propellant supply mode. Specific Implementation Example 10:

[0141] The only difference between Embodiment 10 and Embodiment 9 of the present invention is that:

[0142] The present invention provides a computer device, including a memory and a processor. The memory stores a computer program, and the processor executes the computer program to implement a supply method for an air-breathing, cross-field electric propulsion system with a multi-propellant supply mode. Specific Implementation Example Eleven:

[0144] The only difference between Embodiment Eleven and Embodiment Nine of the present invention is that:

[0145] A schematic diagram of an air-breathing, field-cutting electric propulsion system with multiple working fluid supply modes is shown below. Figure 1 As shown, a mixture of rarefied atmospheric working fluid and xenon working fluid is used for propulsion under multiple supply modes. Xenon was chosen as the auxiliary working fluid because xenon atoms have low ionization energy, large collision cross-section, and good ionization performance, and it has been widely used in the field of electric propulsion with mature application experience.

[0146] The multi-propellant supply mode air-breathing tangential field electric propulsion system includes an electric thruster and collection device module 1, a microwave cathode module 2, a xenon storage and supply module 3, and a control and energy supply module 4. The electric thruster and collection device module 1 includes a microwave-DC hybrid ionization tangential field thruster 11 and an ultra-low orbit atmospheric propellant collection device 12 connected to the inlet end of the discharge channel of the microwave-DC hybrid ionization tangential field thruster 11. The microwave cathode module 2 is used to neutralize the high-speed ion plume ejected by the microwave-DC hybrid ionization tangential field thruster 11. The control and energy supply module 4 includes a DC power supply module electrically connected to the onboard control system via a communication and power supply bus 5. The system includes a source module 41, a microwave power source module 42, and a supply processor module 43. The DC power source module 41 is electrically connected to the microwave-DC hybrid ionization field-cutting thruster 11 and the microwave cathode module 2, and provides electrical energy. The microwave power source module 42 is electrically connected to the microwave-DC hybrid ionization field-cutting thruster 11 and the microwave cathode module 2, and provides the microwave power required for working fluid ionization. The supply processor module 43 is electrically connected to the xenon gas storage and supply module 3, and is used to control the xenon gas flow rate supplied by the xenon gas storage and supply module 3. The xenon gas storage and supply module 3 is connected to the gas path input terminals of the microwave-DC hybrid ionization field-cutting thruster 11 and the microwave cathode module 2, respectively.

[0147] Detailed explanations of each module and submodule:

[0148] like Figure 4 and Figure 5As shown, the microwave-DC hybrid ionization field-cutting thruster 11 includes a thruster housing 111 with a cylindrical main body, a microwave feed interface 112 reserved on the housing, three-stage permanent magnets 113 arranged along the central axis inside the housing, a cylindrical discharge channel 114 installed on the central axis inside the thruster housing 111, a cylindrical monopole antenna 115 inserted into the channel through the microwave feed interface 112 between the three-stage permanent magnets 113, a high-transparency anode 116 installed at the upstream entrance of the channel on the central axis, an insulating ceramic 117 installed upstream of the high-transparency anode 116 on the central axis, and an annular gas homogenizer 118 installed upstream of the insulating ceramic 117 on the central axis. The anode 116 is electrically connected to the positive terminal of the DC power source module 41, the cylindrical monopole antenna 115 is electrically connected to the microwave power source module 42, and the annular gas homogenizer 118 is connected to the ultra-low orbit atmospheric working fluid collection device 12 and the xenon gas storage and supply module 3. The microwave-DC hybrid ionization thruster 11 utilizes microwave and DC power to ionize and accelerate a mixture of rarefied atmosphere and xenon gas, generating thrust. The plume is then neutralized by the microwave cathode module 2. When a satellite operates in a very low Earth orbit, the air-breathing electric propulsion system will continuously face the challenges of a low-pressure environment. The high electron temperature characteristics of microwave electron cyclotron resonance technology can specifically achieve stable discharge of the working fluid in low-pressure atmospheres. At a microwave frequency of 4.2 GHz, the strong magnetic field causes a higher electron cyclotron frequency and a higher local electron temperature, which is more conducive to the stable ionization of the atmospheric working fluid.

[0149] The microwave-DC hybrid ionization tangential thruster 11, developed based on the tangential thruster, possesses the wide-range adjustable discharge power characteristic of traditional tangential thrusters, while also incorporating the low-pressure discharge characteristics of microwave electron cyclotron resonance ionization. Its discharge pressure range spans three orders of magnitude, matching the variable characteristics of the ultra-low Earth orbit atmosphere. Furthermore, because the magnetic field lines are mostly parallel to the discharge channel wall, the tangential thruster experiences less wall loss and has a longer lifespan compared to traditional Hall thrusters. In addition, after long-term optimization, the tangential thruster has been put into engineering applications and possesses a high degree of technological maturity. Therefore, the microwave-DC hybrid ionization tangential thruster 11, combining the low-pressure characteristics of microwave electron cyclotron resonance ionization with the long lifespan, high specific impulse, and high thrust-to-power ratio of the tangential thruster, is highly compatible with the mission objectives of ultra-low Earth orbit air-breathing electric propulsion.

[0150] like Figure 4 As shown, the ultra-low orbit atmospheric working fluid collection device 12 includes a parabolic-shaped outer shell 121 and a rectifier grid 122 set in the windward direction of satellite flight. The ultra-low orbit atmospheric working fluid collection device 12 is connected to the thruster shell 111.

[0151] like Figure 3As shown, the microwave cathode module 2 includes a cylindrical shell 21, an outlet plate 22 installed at the front end of the cylindrical shell 21, a ring-shaped permanent magnet 23 coaxially installed inside the cylindrical shell 21, a base plate 24 installed at the rear end of the cylindrical shell 21, a substrate 25 coaxially installed inside the ring-shaped permanent magnet 23 with a reserved gas input end, and a cathode antenna 26 installed at the axis of the substrate; the substrate 25 is connected to the xenon gas storage and supply module 3, the cylindrical shell 21 is electrically connected to the negative terminal of the DC power source module 41, and the cathode antenna 26 is electrically connected to the microwave power source module 42.

[0152] The working principle of microwave cathode module 2 is as follows: atmospheric working fluid or multi-mode supplied atmospheric and xenon working fluid enter the microwave cathode through the gas path port reserved on the substrate 25. After being excited by the cathode antenna 26, microwave electron cyclotron resonance is generated and ionized into plasma. Electrons are subjected to DC electric field and enter the plume region through the lead-out plate 22 to neutralize the positive charge of the plume and avoid charge accumulation that may interfere with the key electronic components on the satellite.

[0153] like Figure 6 As shown, the cathode antenna 26 can be in the shape of a disc, L, F, cylindrical monopole, or double-arm dipole.

[0154] like Figure 7 As shown, the cross-sectional shape of the rectifier grid 122 is square, circular, fan-shaped, equilateral triangular, or regular hexagonal, which is used to regulate the gas to enter the ultra-low orbit atmospheric working fluid collection device 12 axially, thereby improving the collection efficiency.

[0155] like Figure 8 As shown in the cross-sectional view, the discharge channel 114 is in the shape of a cylinder, a partially expanding cylinder, a fully expanding platform, or a stepped expanding cylinder.

[0156] Considering the harsh environmental constraints of the ultra-low orbit, this embodiment provides a multi-mode supply method for an air-breathing field-cutting electric propulsion system with multiple working propellant supply modes. This method adjusts the anode voltage V through the DC power source module 41 of the control and energy supply module 4, adjusts the microwave power P01 and P02 of the microwave-DC hybrid ionized field-cutting thruster and microwave cathode module through the microwave power source module 42, and adjusts the xenon flow rate M of the xenon storage and supply module through the supply processor module 43 to meet the needs of various on-orbit operating conditions.

[0157] The specific supply methods are divided into the following two schemes, with Scheme 1 as the primary scheme and Scheme 2 as a supplementary scheme in case of emergency or failure of Scheme 1.

[0158] Option 1:

[0159] The satellite obtains the following parameters through on-board sensors, including but not limited to three environmental parameters such as the spacecraft orbital altitude H, atmospheric density ρ, and solar radiation intensity T, and four system state parameters such as the intake flow rate A of the ultra-low orbit atmospheric working fluid collection device, the pressure B of the xenon storage and supply system, the anode voltage V, and the microwave power P, and selects the above core operating parameters as the input of the neural network;

[0160] Process 1: Normalize the above parameters and map them to the 0-1 interval to eliminate the influence of dimensional differences on neural network training. The formula is:

[0161]

[0162] where X is the original parameter value, X min and X max are the minimum and maximum values of the parameter within the design range, respectively;

[0163] Process 2: Adopt an improved BP neural network as the core decision model, and its structure is as follows:

[0164] Input layer: Ensure that the number of neurons is consistent with the dimension of the operating parameters. For example, 7 parameters correspond to 7 input neurons;

[0165] Hidden layer: Set two hidden layers. The first layer has 14 neurons and adopts the ReLU activation function; the second layer has 7 neurons and adopts the LeakyReLU activation function;

[0166] Output layer: 1 neuron, and the output value is the xenon supply ratio K, where 0 ≤ K ≤ 1. K = 1 represents pure xenon supply, K = 0 represents pure atmospheric supply, and 0 < K < 1 represents multi-mode supply;

[0167] Process 3: Obtain training data through ground simulation and experiments, covering the full operating range of 150 - 1000 km, and calculate the optimal xenon ratio K_opt with a thrust error ≤ 3% and the minimum xenon consumption for each scenario through simulation software under the premise of meeting drag compensation; a total of 100,000 groups of samples are generated and divided into a training set and a validation set according to the ratio of 8:2;

[0168] Process 4: Use the Xavier initialization method to initialize the network weights; the loss function adopts the mean square error MSE, and the formula is:

[0169]

[0170] Use the Adam optimizer with an initial learning rate of 0.001, which decays by 10% every 50 epochs; terminate the training when the validation set loss does not decrease for 20 consecutive epochs or when the number of training epochs reaches 500; after training is completed, use the test set to verify the model accuracy, requiring a prediction error of more than 95% of the samples. The calculation formula is:

[0171]

[0172] Process 5: Online dispensing execution process;

[0173] Real-time acquisition: Obtain the working condition parameters in real time through sensors and perform normalization processing according to the method in Process 1;

[0174] Proportion prediction: Input the normalized parameters into the trained neural network and output the xenon supply ratio K_pred;

[0175] Execution adjustment:

[0176] When K_pred = 1, the supply processor module 43 fully opens the xenon storage and supply module 3, and uses full-flow xenon supply;

[0177] When K_pred = 0, the supply processor module 43 fully closes the xenon storage and supply module 3, and uses pure atmospheric supply;

[0178] If 0 < K_pred < 1, the supply processor module opens the xenon storage and supply module in proportion, where the xenon flow rate = K_pred * maximum xenon flow rate M1;

[0179] Process 6: Feedback correction. During on-orbit operation, set the frequency of collecting thrust values according to the required accuracy of the mission. The ground monitoring center regularly receives the actual working conditions and thrust data transmitted back by the satellite. When the average error of 100 consecutive adjustments exceeds 5%, retrain the model with new data and update the model parameters in the satellite system through telemetry commands to achieve on-orbit update;

[0180] Scheme ②: Based on Scheme ①, the satellite system has a built-in preset supply program, which is used as a backup plan for emergency situations and when the method of training the neural network model in Scheme ① fails. The process of the preset supply program is as follows:

[0181] Process 1: The satellite determines the current working condition through sensors. The on-board system outputs working instructions to the control and energy supply module 4 through the communication and power supply bus 5. The anode voltage V is adjusted by the DC power source module 41 of the control and energy supply module 4, the microwave power P of the microwave-DC hybrid ionization cusp field thruster 11 is adjusted by the microwave power source module 42, and the xenon flow rate M of the xenon storage and supply module 3 is adjusted by the supply processor module 43 to meet the requirements of various on-orbit working conditions;

[0182] The processor module 43 controls the xenon ratio of the first gas path to the second gas path to be 9:1;

[0183] Process 2:

[0184] Based on the typical operating conditions of the air-breathing electric propulsion system with multiple working fluid supply modes, the standard anode voltage V0, maximum anode voltage V1, standard microwave power P0, maximum microwave power P1, standard xenon flow rate M0, maximum xenon flow rate M1, and atmospheric stable discharge lower limit pressure P01 are clearly defined.

[0185] The requirements are V1≥2V0, P1≥5P0, and M1≥10M0.

[0186] If the current operating condition is auxiliary ignition, proceed to step A;

[0187] If the current operating condition is a low thrust gap condition, proceed to step B;

[0188] If the current operating condition is a high thrust gap condition, proceed to step C;

[0189] If the current operating condition is an emergency maneuver condition, proceed to step D;

[0190] Step A: The satellite sensor determines the ambient air pressure value. If it is less than or equal to the lower limit of atmospheric stable discharge pressure P01, the processor module 43 sets the xenon flow rate to M0, the microwave power source module 42 sets the microwave power to P0, and the DC power source module 41 sets the anode voltage to V0. This process is continued for 10 seconds, waiting for the satellite sensor to return data. If ignition is successful and thrust is generated, the operating condition is determined and subsequent steps B, C, or D are executed. If ignition is still unsuccessful, with the xenon flow rate at M0 and the microwave power at P0, the anode voltage is kept constant, and each increase of 5%M0 and 5%P0 is performed, continuing for 10 seconds while waiting for the satellite sensor to return data until successful ignition.

[0191] Step B: The DC power source module 41 sets the anode voltage to V0~150%V0, and the microwave power source module 42 sets the microwave power to P0~150%P0. If the satellite computer determines that the resistance balance requirement can be met, the xenon supply to the processor module 43 is turned off. If the satellite computer determines that the resistance balance requirement is still not met, the xenon supply to the processor module 43 is set to M0~3M0.

[0192] Step C: The DC power source module 41 sets the anode voltage to V0~150%V0, the microwave power source module 42 sets the microwave power to P0~150%P0, and the processor module 43 sets the xenon supply to 3M0~5M0. If the satellite computer determines that the resistance balance requirement can be met, the xenon supply to the processor module 43 remains unchanged. If the satellite computer determines that the resistance balance requirement is still not met, the xenon supply to the processor module 43 is set to 5M0~M1 until the resistance balance requirement is met.

[0193] Step D: After receiving the emergency maneuver signal from the satellite sensor, the DC power source module 41 sets the anode voltage to 150%V0~V1, the microwave power source module 42 sets the microwave power to 150%P0~P1, and the processor module 43 sets the xenon flow rate to M1 unchanged until the emergency maneuver command is lifted.

[0194] Step E: After receiving satellite commands, the air-breathing, field-switching electric propulsion system with multi-propellant supply mode prioritizes executing custom operating conditions. The DC power source module 41 and microwave power source module 42 supply processor module 43, both set to custom values ​​according to satellite commands. Table 1 summarizes the various supply modes:

[0195] Table 1. Parameters of Multi-mode Propulsion Methods for Air-breathing Field-Cut Electric Propulsion Systems with Multiple Propellant Supply Modes

[0196]

[0197] Detailed explanation:

[0198] The parameters in the table represent the design concept of the multi-mode supply method. The values ​​of the specific parameters can be adjusted according to the specific task requirements, and all such adjustments should be included within the protection scope of this invention.

[0199] The above description is merely a preferred embodiment of an air-breathing, tangential-field electric propulsion system and its supply method with multiple working propellant supply modes. The scope of protection for such a system and method is not limited to the above embodiments; all technical solutions falling within this conceptual framework are within the scope of protection of this invention. It should be noted that for those skilled in the art, any improvements and variations made without departing from the principles of this invention should also be considered within the scope of protection of this invention.

Claims

1. A supply method for an air-breathing, field-cutting electric propulsion system with multiple working propellant supply modes, the system comprising: An electric thruster, a collection device module, a microwave cathode module, a xenon storage and supply module, and a control and energy supply module, characterized in that: the method includes the following steps: Step 1: Obtain three environmental parameters of the spacecraft orbit altitude H, atmospheric density ρ, and solar radiation intensity T, as well as four system state parameters of the intake flow rate A of the ultra-low orbit atmospheric working medium collection device, the pressure B of the xenon storage and supply module, the anode voltage V, and the microwave power P through on-board sensors, and select the above core operating condition parameters as the input of the neural network; Step 2: Normalize the above parameters, map them to the 0-1 interval, and eliminate the influence of dimensional differences on neural network training; Step 3: Adopt an improved BP neural network as the core decision-making model; Step 4: Obtain training data through ground simulation and experiments, and divide them into a training set and a verification set according to a ratio of 8:2; Step 5: Use the Xavier initialization method to initialize the network weights; Step 6: Online allocate the execution process; Step 7: Feedback correction, during on-orbit operation, set the acquisition thrust value frequency according to the required accuracy of the mission. The ground monitoring center regularly receives the actual operating conditions and thrust data transmitted back by the satellite, retrains the model with the new data, and updates the model parameters in the satellite system through telemetry commands to achieve on-orbit update; Among them, real-time acquisition: Obtain operating condition parameters in real time through on-board sensors, and perform normalization processing according to the method in Step 2; Ratio prediction: Input the normalized parameters into the trained neural network, and output the xenon supply ratio K_pred; Execution adjustment: When K_pred = 1, the supply processor module fully opens the xenon storage and supply module, and uses full-flow xenon supply; When K_pred = 0, the supply processor module fully closes the xenon storage and supply module, and uses pure atmosphere supply; If 0 < K_pred < 1, the supply processor module opens the xenon storage and supply module according to the ratio, where the xenon flow rate = K_pred * maximum xenon flow rate M1.

2. The method according to claim 1, characterized in that: The specific content of Step 2 is: Eliminate the influence of dimensional differences on neural network training, and the formula is: where X is the original parameter value, X min and X max are the minimum and maximum values of the corresponding parameter within the design range, respectively.

3. A multi-propellant supply mode air-breathing tangential field electric propulsion system, wherein the system employs the supply method of the multi-propellant supply mode air-breathing tangential field electric propulsion system as described in claim 1, characterized in that: The system includes: An electric thruster, a collection device module, a microwave cathode module, a xenon storage and supply module, and a control and energy supply module; The electric thruster and collection device module includes a cusp field thruster with microwave-dc hybrid ionization, and an ultra-low orbit atmospheric working medium collection device connected to the discharge channel inlet end of the cusp field thruster with microwave-dc hybrid ionization; the microwave cathode module is used to neutralize the high-speed ion plume ejected by the cusp field thruster with microwave-dc hybrid ionization; The control and energy supply module includes a dc power source module, a microwave power source module, and a supply processor module electrically connected to the on-board control system through a communication and power supply bus; The dc power source module is electrically connected to the cusp field thruster with microwave-dc hybrid ionization and the microwave cathode module, and provides electrical energy; the microwave power source module is electrically connected to the cusp field thruster with microwave-dc hybrid ionization and the microwave cathode module, and provides the microwave power required for working medium ionization; the supply processor module is electrically connected to the xenon storage and supply module, and is used to control the xenon flow rate supplied by the xenon storage and supply module; The xenon gas storage and supply module is connected to the gas input terminals of the microwave-DC hybrid ionization field thruster and the microwave cathode module, respectively.

4. The system according to claim 3, characterized in that: microwave - The DC hybrid ionization field-cutting thruster includes a thruster housing with a cylindrical main body, a microwave feed interface reserved on the housing, three permanent magnets arranged along the central axis inside the housing, a cylindrical discharge channel installed on the central axis inside the thruster housing, a cylindrical monopole antenna inserted into the channel through the microwave feed interface between the three permanent magnets, a high transparency anode installed at the upstream entrance of the channel on the central axis, an insulating ceramic installed upstream of the high transparency anode on the central axis, and an annular gas homogenizer installed upstream of the insulating ceramic on the central axis. The high-transparency anode is electrically connected to the positive terminal of the DC power source module, the cylindrical monopole antenna is electrically connected to the microwave power source module, and the annular gas homogenizer is connected to the ultra-low orbit atmospheric working fluid collection device and the xenon gas storage and supply module.

5. The system according to claim 4, characterized in that: The ultra-low orbit atmospheric propellant collection device includes a parabolic outer shell and a rectification grid set in the windward direction of the satellite's flight. The ultra-low orbit atmospheric propellant collection device is connected to the thruster shell.

6. The system according to claim 5, characterized in that: The microwave cathode module includes a cylindrical shell, an outlet plate installed at the front end of the cylindrical shell, a ring-shaped permanent magnet coaxially installed inside the cylindrical shell, a base plate installed at the rear end of the cylindrical shell, a substrate coaxially installed inside the ring-shaped permanent magnet with a reserved gas inlet, and a cathode antenna installed at the axis of the substrate. The substrate is connected to the xenon gas storage and supply module; the cylindrical shell is electrically connected to the negative terminal of the DC power source module, and the cathode antenna is electrically connected to the microwave power source module.

7. The system according to claim 6, characterized in that: The discharge channel and insulating ceramic material are hexagonal boron nitride ceramics, and the materials for the three-stage permanent magnet and the ring-shaped permanent magnet are samarium cobalt 2:17 permanent magnets; The cross-sectional shape of the rectifier grid is square, circular, fan-shaped, equilateral triangular, or regular hexagonal. The cathode antenna can be a disc-shaped, L-shaped, F-shaped, cylindrical monopole or a double-armed dipole; The discharge channel shape can be a cylinder, a partially expanding cylinder, a fully expanding platform, or a stepped expanding cylinder.

8. A computer-readable storage medium having a computer program stored thereon, characterized in that, The program is executed by the processor to implement the method as claimed in any one of claims 1-2.

9. 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 1-2.

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