Method and system for simulating interaction of electric propulsion wall debris with plasma

Abstract

This invention provides a method and system for simulating the interaction between electric propulsion wall debris and plasma, comprising: a charge deposition module to simulate the charge deposition effect of plasma flow field on debris; an electron energy deposition module to simulate the collision and energy absorption effect of debris on electrons; and an ion collision module to simulate the collision effect of debris on ions. This invention provides a simulation model tool for numerical simulation of discharge disturbances caused by electric propulsion debris, applicable to the simulation of the motion process of debris from electric thruster wall materials in a plasma flow field. It provides clear formulaic support for the formation of discharge disturbances related to wall debris, laying the foundation for establishing discharge disturbance suppression strategies and providing simulation basis for the influence of electric thruster wall debris on the plasma flow field and the discharge disturbance induction process.

Description

Technical Field

[0001] This invention belongs to the field of space propulsion technology, specifically relating to a method and system for simulating the interaction between electric propulsion wall debris and plasma. Background Technology

[0002] During normal operation of electric thrusters, the sputtering effect of the plasma working fluid on the wall material often causes the wall material to detach, forming spalling debris. Current theory has found that the formation and movement of this spalling debris can cause discharge disturbances to the electric thruster, resulting in instantaneous and drastic changes in the thruster current. This can cause a strong impact on the power system, leading to thruster instability, performance degradation, or even power outages, causing the satellite to lose power. In 2022 and 2023, two satellites using 300W Hall thrusters experienced on-orbit discharge disturbance events. Both events resulted in thruster shutdowns, and power was only restored after restarting ignition for more than ten minutes.

[0003] Currently, discharge disturbance events pose a significant threat to the safe flight of satellites in orbit. Therefore, the suppression strategy for electric propulsion discharge disturbances has become a key focus, and the simulation technology of the interaction between electric thruster wall debris and plasma has become one of the key technologies that urgently need to be mastered.

[0004] In the prior art, the literature "Typical transient phenomena of Hall Effect thrusters" (Komarov A, Pridannikov S, Lenguito G., The 36th International Electric Propulsion Conference. 2019) experimentally observed that the triggering time scale of the discharge disturbance is extremely short, on the order of milliseconds, accompanied by a large and violent surge in current and a "flashover" phenomenon in the discharge channel. Based on the traces on the discharge chamber wall after the experiment, it is inferred that the formation of the discharge disturbance may be related to the peeling off of the wall, but no direct evidence is given.

[0005] The paper "Accelerating 23,000 hours of ground test backsputtered carbon on a magnetically shielded Hall thruster" (Lobbia RB, Polk JE, Hofer RR, et al., AIAA Propulsion Energy. 2019) conducted accelerated carbon deposition tests by placing graphite plates near the thruster outlet. It found that the increase in sputtered deposits led to an increase in the "flashover" triggering frequency, indirectly proving that carbon deposition detachment is the cause of discharge disturbances. However, the paper only inferred that this phenomenon was related to carbon deposition detachment and did not provide direct supporting data.

[0006] The patent document "Adaptive and Efficient Simulation Method and System for Electric Propulsion Plasma Oscillation" (CN120706284A) discloses a high-precision numerical simulation model for electric propulsion plasma. It decomposes the computational task through parallel computing and a multi-grid method, and utilizes a neural network model to optimize and adjust parameters to achieve adaptive simulation. However, the subsequent computational optimization of this numerical simulation model is not related to the simulation modeling itself, and is irrelevant to the motion of the exfoliated material.

[0007] In summary, based on the current research status, focusing solely on the motion of the spalling material in the discharge disturbance problem fails to provide more microscopic experimental observations and further induction mechanisms. This poses a significant obstacle to the establishment of discharge disturbance suppression strategies. Therefore, it is necessary to establish a numerical model for the interaction between spalling material and plasma on electrically propelled wall surfaces. Summary of the Invention

[0008] In view of the deficiencies in the prior art, the purpose of this invention is to provide a method and system for simulating the interaction between electric propulsion wall debris and plasma.

[0009] A method for simulating the interaction between electric propulsion wall spallings and plasma, provided by the present invention, includes:

[0010] The spalling material refers to fragmented objects of material that have detached from the surface of electric thruster components due to plasma sputtering.

[0011] Charge deposition steps and the effect of simulated plasma flow field on charge deposition of exfoliated material; Electron energy deposition steps, simulating the collision and energy absorption of electrons by exfoliated material; Ion collision steps and simulation of the collision effect of exfoliated material on ions.

[0012] Integrate charge deposition, collision and energy absorption effects, and output simulation results.

[0013] Preferably, in the charge deposition step, the charge flux of electrons to the exfoliated material is:

[0014] in, Indicates the local electron number density; The 'e' represents the velocity of the electron; 'e' represents the electron. This represents the self-induced electromotive force of the exfoliated material; Indicates the affinity of the exfoliated material; This indicates the local electronic temperature.

[0015] The charge flux of ions to the exfoliated material is:

[0016] in, Indicates the local ion number density; This indicates the velocity of ion movement.

[0017] The self-induced potential at the location of the detached material at this moment is:

[0018] in, Indicates electron mass; Indicates the mass of the ion.

[0019] Preferably, the charge carried by the exfoliated material is:

[0020] in, Represents the vacuum permittivity; Indicates the surface area of ​​the exfoliated material; 'a' represents the local Debye length; 'a' represents the empirical coefficient.

[0021] Preferably, in the ion collision step, when the ions collide with the exfoliated material, they neutralize the electrons on the surface of the exfoliated material and leave the exfoliated material in the form of atoms. The velocity at the moment of departure is the thermal velocity corresponding to the temperature of the exfoliated material, and the direction follows a cosine distribution.

[0022] The thermal velocity corresponding to the temperature of the exfoliated material is much lower than the incident velocity of the ions, so the ions deposit both kinetic and ionization energy on the surface of the exfoliated material.

[0023] in, Indicates the incident kinetic energy of the ions; This represents the ionization energy of an ionic element.

[0024] In the electron energy deposition step, if the incident kinetic energy of the electrons on the exfoliated material satisfies Electrons are scattered at a thermal velocity corresponding to the temperature of the exfoliated material, following a cosine distribution. The energy deposited in the exfoliated material is as follows:

[0025] If the incident kinetic energy of the electron satisfies Then the electrons will cancel out the kinetic energy of the affinity and be deposited on the surface of the exfoliated material:

[0026] in, Indicates incident kinetic energy; Indicates the affinity of the exfoliated material; This indicates that the incident electron kinetic energy satisfies Under certain conditions, electron energy is deposited in the exfoliated material; This indicates that the incident electron kinetic energy satisfies Under certain conditions, electron energy is deposited on the exfoliated material.

[0027] Preferably, the kinetic energy absorbed by the exfoliated material from electrons is:

[0028] The initial temperature of the detached material after it detaches from the wall is taken as the wall temperature, and the temperature change of the detached material is:

[0029] in, This indicates the deposition energy of ions on the exfoliated material; This indicates the deposition energy of ions on the exfoliated material; Indicates the mass of the exfoliated material; Indicates the specific heat capacity of the exfoliated material; This indicates the temperature change value of the exfoliated material.

[0030] This invention provides a simulation system for the interaction between electric propulsion wall debris and plasma, comprising: Charge deposition module, simulating the charge deposition effect of plasma flow field on exfoliated material; Electron energy deposition module, simulating the collision and energy absorption of electrons by exfoliated material; Ion collision module, simulating the collision effect of exfoliated material on ions.

[0031] The module integrates charge deposition, collision and energy absorption, and outputs simulation results.

[0032] The spalling material refers to fragmented objects of material that have detached from the surface of electric thruster components due to plasma sputtering.

[0033] Preferably, in the charge deposition module, the charge flux of electrons to the exfoliated material is:

[0034] in, Indicates the local electron number density; The 'e' represents the velocity of the electron; 'e' represents the electron. This represents the self-induced electromotive force of the exfoliated material; Indicates the affinity of the exfoliated material; This indicates the local electronic temperature.

[0035] The charge flux of ions to the exfoliated material is:

[0036] in, Indicates the local ion number density; This indicates the velocity of ion movement.

[0037] The self-induced potential at the location of the detached material at this moment is:

[0038] in, Indicates electron mass; Indicates the mass of the ion.

[0039] In more preferred embodiments, the charge carried by the exfoliated material is:

[0040] in, Represents the vacuum permittivity; Indicates the surface area of ​​the exfoliated material; 'a' represents the local Debye length; 'a' represents the empirical coefficient.

[0041] Preferably, in the ion collision module, when ions collide with the exfoliated material, they neutralize the electrons on the surface of the exfoliated material and leave the exfoliated material in the form of atoms. The velocity at the moment of departure is the thermal velocity corresponding to the temperature of the exfoliated material, and the direction follows a cosine distribution.

[0042] The thermal velocity corresponding to the temperature of the exfoliated material is much lower than the incident velocity of the ions, so the ions deposit both kinetic and ionization energy on the surface of the exfoliated material.

[0043] in, Indicates the incident kinetic energy of the ions; This represents the ionization energy of an ionic element.

[0044] In the electron energy deposition module, if the incident kinetic energy of the electrons on the exfoliated material satisfies Electrons are scattered at a thermal velocity corresponding to the temperature of the exfoliated material, following a cosine distribution. The energy deposited in the exfoliated material is as follows:

[0045] If the incident kinetic energy of the electron satisfies Then the electrons will cancel out the kinetic energy of the affinity and be deposited on the surface of the exfoliated material:

[0046] in, Indicates incident kinetic energy; Indicates the affinity of the exfoliated material; This indicates that the incident electron kinetic energy satisfies Under certain conditions, electron energy is deposited in the exfoliated material; This indicates that the incident electron kinetic energy satisfies Under certain conditions, electron energy is deposited on the exfoliated material.

[0047] Preferably, the kinetic energy absorbed by the exfoliated material from electrons is:

[0048] The initial temperature of the detached material after it detaches from the wall is taken as the wall temperature, and the temperature change of the detached material is:

[0049] in, This indicates the deposition energy of ions on the exfoliated material; This indicates the deposition energy of ions on the exfoliated material; Indicates the mass of the exfoliated material; Indicates the specific heat capacity of the exfoliated material; This indicates the temperature change value of the exfoliated material.

[0050] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention provides a simulation model tool for numerical simulation of discharge disturbances caused by electric propulsion debris, providing technical support for the establishment of discharge disturbance suppression strategies.

[0051] 2. This invention captures the dynamic interaction process between exfoliated material and plasma at the microscopic level, the influence mechanism on space charge transport, the evolution mechanism of exfoliated material-triggered discharge disturbance, and which factors can suppress the degree and frequency of discharge disturbance.

[0052] 3. This invention provides clear formulaic support for the mechanism of discharge disturbance formation related to wall spalling, and provides simulation basis for the influence of wall spalling on plasma flow field and discharge disturbance induction process of electric thruster. Attached Figure Description

[0053] Other features, objects, and advantages of the invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of a simulation system for the interaction between electric propulsion wall debris and plasma. Detailed Implementation

[0054] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0055] The present invention provides a simulation method for the interaction between electric propulsion wall debris and plasma, which is applicable to the simulation of the motion process of electric thruster wall debris in plasma flow field. It can obtain the influence process of debris motion on flow field and the process of flow field forming discharge disturbance, providing simulation basis for the influence law of electric thruster wall debris on plasma flow field and the discharge disturbance induced process.

[0056] Specifically, the motion of wall spalling material in the plasma flow field can simultaneously induce changes in both the spalling material and the plasma. The spalling material will undergo charge deposition, while the plasma will undergo electron-sparing material collisions, ion-sparing material collisions, and related charge and energy exchanges. This is an unsteady numerical model in which multiple particles interact in motion, which is used to study the mechanism of how spalling material induces discharge disturbances and to explore the factors that affect discharge disturbances.

[0057] The interaction refers to charge exchange and mutual collision.

[0058] The numerical model describes the charge deposition effect of the exfoliated material itself, the collision and energy absorption effect of the exfoliated material on electrons, and the collision effect of the exfoliated material on ions. When the exfoliated material moves in the plasma flow field of the electric thruster, the above three physical processes will continuously occur. In this dynamic process, both the exfoliated material and the plasma will be continuously affected by each other.

[0059] Therefore, the simulation process specifically includes: Step S1: Simulate the charge deposition effect of plasma flow field on the exfoliated material.

[0060] The (wall) spalling material refers to fragmented objects of material that have detached from the surface of electric thruster components due to plasma sputtering.

[0061] The charge deposition process is a dynamic charge accumulation process formed by electrons and ions on the exfoliated material.

[0062] When the debris moves to a certain position in space, the charge flux of electrons to the debris is:

[0063] In the formula, For the local electron number density, For the speed of electron movement, The self-induced potential of the exfoliated material, For the affinity of exfoliated materials, This refers to the local electronic temperature.

[0064] The charge flux of ions to the exfoliated material is:

[0065] In the formula, The local ion number density, This represents the velocity of ions.

[0066] Solve for the self-induced potential at the location of the detached material at this moment:

[0067] In the formula, For electronic quality, The value represents the ionic mass. Calculations show that the exfoliated material typically carries a negative potential.

[0068] If we consider the detached material and the surrounding electrostatic shielding boundary as a set of capacitors, then the charge carried by the detached material is:

[0069] In the formula, The vacuum permittivity, The surface area of ​​the exfoliated material. denoted as the local Debye length, representing the spatial scale of the electrostatic shielding around the exfoliated material; 'a' is an empirical coefficient, taken as 1.47, which is an empirical parameter that has been calculated through extensive simulations and whose results are in good agreement with actual conditions.

[0070] The surrounding electrostatic shielding boundary characterizes the plasma's ability to shield against static electricity. When a charge in the plasma is moved away from it by a certain spatial dimension, the influence of the surrounding electrostatic field on it will decrease to a negligible level; the boundary of this range is the surrounding electrostatic shielding boundary.

[0071] Step S2: Simulate the collision effect of exfoliated material on ions.

[0072] The collision effect refers to the charge neutralization and energy deposition processes that occur when ions collide with the exfoliated material.

[0073] When ions collide with the exfoliated material, they neutralize electrons on the surface and leave the material as atoms. The velocity at the moment of departure is the thermal velocity corresponding to the temperature of the exfoliated material, and its direction follows a cosine distribution. Similarly, in this process, the thermal velocity corresponding to the temperature of the exfoliated material is much lower than the incident velocity of the ions. Therefore, the ions deposit almost all of their kinetic and ionization energy on the surface of the exfoliated material, resulting in:

[0074] In the formula, The incident kinetic energy of the ions. denoted as ionization energy.

[0075] Step S3: Simulate the collision and energy absorption of electrons by the exfoliated material.

[0076] Specifically, if electrons due to incident kinetic energy ( Insufficient affinity for exfoliated materials ( ) When an electron strikes the electron barrier on the surface of the exfoliated material, it can only leave after impacting the material's electron barrier; that is, when the incident kinetic energy of the electron on the exfoliated material satisfies... At that time, electrons will be scattered at a thermal velocity corresponding to the temperature of the exfoliated material, and the direction will follow a cosine distribution.

[0077] Since the thermal velocity corresponding to the temperature of the exfoliated material is much lower than the incident velocity of the electrons, it can be considered that the electrons lose almost all of their kinetic energy in this collision. During this process, the energy deposited in the exfoliated material is as follows:

[0078] If the incident kinetic energy of the electron satisfies During charge deposition collisions, electrons deposit kinetic energy that cancels out affinity onto the surface of the exfoliated material, i.e.:

[0079] Therefore, there are two scenarios in which the exfoliated material absorbs kinetic energy from electrons:

[0080] in, This indicates that the incident electron kinetic energy satisfies Under certain conditions, electron energy is deposited in the exfoliated material; This indicates that the incident electron kinetic energy satisfies Under certain conditions, electron energy is deposited on the exfoliated material.

[0081] The solution for the temperature of the exfoliated material specifically includes: The initial temperature of the detached material after it detaches from the wall is taken as the wall temperature. Its movement in the plasma flow field causes it to continuously absorb energy from the plasma, which is converted into the internal energy of the detached material, including all the energy obtained from electrons and ions. Therefore, the temperature change of the exfoliated material is:

[0082] In the formula, For the quality of the flaking material, The specific heat capacity of the exfoliated material, This represents the temperature change value of the exfoliated material. This represents the deposition energy of ions on exfoliated material. This represents the deposition energy of ions on exfoliated material.

[0083] The present invention also provides a simulation system for the interaction between electric propulsion wall debris and plasma. The simulation system can be implemented by executing the process steps of the simulation method for the interaction between electric propulsion wall debris and plasma. That is, those skilled in the art can understand the simulation method for the interaction between electric propulsion wall debris and plasma as a preferred embodiment of the simulation system for the interaction between electric propulsion wall debris and plasma.

[0084] This invention also provides a simulation system for the interaction between electric propulsion wall debris and plasma, providing a simulation method for the interaction between debris and plasma flow field and how to induce discharge disturbances, including: Charge deposition module, simulating the charge deposition effect of plasma flow field on exfoliated material; Non-depositional collision module, simulating the non-depositional collision effect of exfoliated material on electrons; The collision module simulates the collision effect of exfoliated material on ions.

[0085] The module integrates charge deposition, collision and energy absorption, and outputs simulation results.

[0086] The spalling material refers to fragmented objects of material that have detached from the surface of electric thruster components due to plasma sputtering.

[0087] In more preferred embodiments, the charge flux of electrons to the exfoliated material in the charge deposition module is:

[0088] in, Indicates the local electron number density; The 'e' represents the velocity of the electron; 'e' represents the electron. This represents the self-induced electromotive force of the exfoliated material; Indicates the affinity of the exfoliated material; This indicates the local electronic temperature.

[0089] The charge flux of ions to the exfoliated material is:

[0090] in, Indicates the local ion number density; This indicates the velocity of ion movement.

[0091] The self-induced potential at the location of the detached material at this moment is:

[0092] in, Indicates electron mass; Indicates the mass of the ion.

[0093] In more preferred embodiments, the charge carried by the exfoliated material is:

[0094] in, Represents the vacuum permittivity; Indicates the surface area of ​​the exfoliated material; 'a' represents the local Debye length; 'a' represents the empirical coefficient.

[0095] In more preferred embodiments, in the ion collision module, when ions collide with the exfoliated material, they neutralize the electrons on the surface of the exfoliated material and leave the exfoliated material in the form of atoms. The velocity at the moment of departure is the thermal velocity corresponding to the temperature of the exfoliated material, and the direction follows a cosine distribution.

[0096] The thermal velocity corresponding to the temperature of the exfoliated material is much lower than the incident velocity of the ions, so the ions deposit both kinetic and ionization energy on the surface of the exfoliated material.

[0097] in, Indicates the incident kinetic energy of the ions; This represents the ionization energy of an ionic element.

[0098] In the electron energy deposition module, if the incident kinetic energy of the electrons on the exfoliated material satisfies Electrons are scattered at a thermal velocity corresponding to the temperature of the exfoliated material, following a cosine distribution. The energy deposited in the exfoliated material is as follows:

[0099] If the incident kinetic energy of the electron satisfies Then the electrons will cancel out the kinetic energy of the affinity and be deposited on the surface of the exfoliated material:

[0100] in, Indicates incident kinetic energy; Indicates the affinity of the exfoliated material; This indicates that the incident electron kinetic energy satisfies Under certain conditions, electron energy is deposited in the exfoliated material; This indicates that the incident electron kinetic energy satisfies Under certain conditions, electron energy is deposited on the exfoliated material.

[0101] In more preferred embodiments, the kinetic energy absorbed by the exfoliated material from electrons is:

[0102] The initial temperature of the detached material after it detaches from the wall is taken as the wall temperature, and the temperature change of the detached material is:

[0103] in, This indicates the deposition energy of ions on the exfoliated material; This indicates the deposition energy of ions on the exfoliated material; Indicates the mass of the exfoliated material; Indicates the specific heat capacity of the exfoliated material; This indicates the temperature change value of the exfoliated material.

[0104] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function as logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0105] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for simulating the interaction between electric propulsion wall debris and plasma, characterized in that, include: Charge deposition steps and the effect of simulated plasma flow field on charge deposition of exfoliated material; Electron energy deposition steps, simulating the collision and energy absorption of electrons by exfoliated material; Ion collision steps, simulating the collision effect of exfoliated material on ions; Integrate charge deposition, collision and energy absorption effects, and output simulation results; The spalling material refers to fragmented objects of material that have detached from the surface of electric thruster components due to plasma sputtering.

2. The method for simulating the interaction between electric propulsion wall debris and plasma according to claim 1, characterized in that, In the charge deposition step, the charge flux of electrons to the exfoliated material is: in, Indicates the local electron number density; Indicates the speed of electron movement; e represents electron; This represents the self-induced electromotive force of the exfoliated material; Indicates the affinity of the exfoliated material; Indicates the local electronic temperature; The charge flux of ions to the exfoliated material is: in, Indicates the local ion number density; Indicates the velocity of ion movement; The self-induced potential at the location of the detached material at this moment is: in, Indicates electron mass; Indicates the mass of the ion.

3. The method for simulating the interaction between electric propulsion wall debris and plasma according to claim 2, characterized in that, The charge carried by the detached material is: in, Represents the vacuum permittivity; Indicates the surface area of ​​the exfoliated material; Indicates the local Debye length; 'a' represents the empirical coefficient.

4. The method for simulating the interaction between electric propulsion wall debris and plasma according to claim 1, characterized in that, In the ion collision step, when ions collide with the exfoliated material, they neutralize the electrons on the surface of the exfoliated material and leave the exfoliated material in the form of atoms. The velocity at the moment of departure is the thermal velocity corresponding to the temperature of the exfoliated material, and the direction follows a cosine distribution. The thermal velocity corresponding to the temperature of the exfoliated material is much lower than the incident velocity of the ions, so the ions deposit both kinetic and ionization energy on the surface of the exfoliated material. in, Indicates the incident kinetic energy of the ions; This represents the ionization energy corresponding to an ionic element; In the electron energy deposition step, if the incident kinetic energy of the electrons on the exfoliated material satisfies Electrons are scattered at a thermal velocity corresponding to the temperature of the exfoliated material, following a cosine distribution. The energy deposited in the exfoliated material is as follows: If the incident kinetic energy of the electron satisfies Then the electrons will cancel out the kinetic energy of the affinity and be deposited on the surface of the exfoliated material: in, Indicates incident kinetic energy; Indicates the affinity of the exfoliated material; This indicates that the incident electron kinetic energy satisfies Under certain conditions, electron energy is deposited on the exfoliated material; This indicates that the incident electron kinetic energy satisfies Under certain conditions, electron energy is deposited on the exfoliated material.

5. The method for simulating the interaction between electric propulsion wall debris and plasma according to claim 4, characterized in that, The kinetic energy absorbed by the exfoliated material from electrons is: The initial temperature of the detached material after it detaches from the wall is taken as the wall temperature, and the temperature change of the detached material is: in, This indicates the deposition energy of ions on the exfoliated material; This indicates the deposition energy of ions on the exfoliated material; Indicates the mass of the exfoliated material; Indicates the specific heat capacity of the exfoliated material; This indicates the temperature change value of the exfoliated material.

6. A simulation system for the interaction between electric propulsion wall debris and plasma, characterized in that, include: Charge deposition module, simulating the charge deposition effect of plasma flow field on exfoliated material; Electron energy deposition module, simulating the collision and energy absorption of electrons by exfoliated material; Ion collision module, simulating the collision effect of exfoliated material on ions; The module integrates charge deposition, collision and energy absorption, and outputs simulation results. The spalling material refers to fragmented objects of material that have detached from the surface of electric thruster components due to plasma sputtering.

7. The simulation system for the interaction between electric propulsion wall debris and plasma according to claim 6, characterized in that, In the charge deposition module, the charge flux of electrons to the exfoliated material is: in, Indicates the local electron number density; Indicates the speed of electron movement; e represents electron; This represents the self-induced electromotive force of the exfoliated material; Indicates the affinity of the exfoliated material; Indicates the local electronic temperature; The charge flux of ions to the exfoliated material is: in, Indicates the local ion number density; Indicates the velocity of ion movement; The self-induced potential at the location of the detached material at this moment is: in, Indicates electron mass; Indicates the mass of the ion.

8. The simulation system for the interaction between electric propulsion wall debris and plasma according to claim 7, characterized in that, The charge carried by the detached material is: in, Represents the vacuum permittivity; Indicates the surface area of ​​the exfoliated material; Indicates the local Debye length; 'a' represents the empirical coefficient.

9. The simulation system for the interaction between electric propulsion wall debris and plasma according to claim 6, characterized in that, In the ion collision module, when ions collide with the exfoliated material, they neutralize the electrons on the surface of the exfoliated material and leave the exfoliated material in the form of atoms. The velocity at the moment of departure is the thermal velocity corresponding to the temperature of the exfoliated material, and the direction follows a cosine distribution. The thermal velocity corresponding to the temperature of the exfoliated material is much lower than the incident velocity of the ions, so the ions deposit both kinetic and ionization energy on the surface of the exfoliated material. in, Indicates the incident kinetic energy of the ions; This represents the ionization energy corresponding to an ionic element; In the electron energy deposition module, if the incident kinetic energy of the electrons on the exfoliated material satisfies Electrons are scattered at a thermal velocity corresponding to the temperature of the exfoliated material, following a cosine distribution. The energy deposited in the exfoliated material is as follows: If the incident kinetic energy of the electron satisfies Then the electrons will cancel out the kinetic energy of the affinity and be deposited on the surface of the exfoliated material: in, Indicates incident kinetic energy; Indicates the affinity of the exfoliated material; This indicates that the incident electron kinetic energy satisfies Under certain conditions, electron energy is deposited on the exfoliated material; This indicates that the incident electron kinetic energy satisfies Under certain conditions, electron energy is deposited on the exfoliated material.

10. The simulation system for the interaction between electric propulsion wall debris and plasma according to claim 9, characterized in that, The kinetic energy absorbed by the exfoliated material from electrons is: The initial temperature of the detached material after it detaches from the wall is taken as the wall temperature, and the temperature change of the detached material is: in, This indicates the deposition energy of ions on the exfoliated material; This indicates the deposition energy of ions on the exfoliated material; Indicates the mass of the exfoliated material; Indicates the specific heat capacity of the exfoliated material; This indicates the temperature change value of the exfoliated material.

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