CN110851939A - Simulation calculation method for service life evaluation of cylindrical anode layer Hall thruster - Google Patents
Simulation calculation method for service life evaluation of cylindrical anode layer Hall thruster Download PDFInfo
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- 238000004088 simulation Methods 0.000 title claims abstract description 20
- 238000011156 evaluation Methods 0.000 title claims abstract description 16
- 238000004364 calculation method Methods 0.000 title claims abstract description 10
- 150000002500 ions Chemical class 0.000 claims abstract description 39
- 238000005530 etching Methods 0.000 claims abstract description 25
- 239000000463 material Substances 0.000 claims abstract description 24
- 238000004544 sputter deposition Methods 0.000 claims abstract description 20
- 238000000034 method Methods 0.000 claims description 14
- 238000000992 sputter etching Methods 0.000 claims description 4
- 239000002245 particle Substances 0.000 abstract description 3
- 230000005672 electromagnetic field Effects 0.000 description 3
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- 230000006399 behavior Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
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Abstract
The invention discloses a simulation calculation method for service life evaluation of a cylindrical anode layer Hall thruster. Firstly, establishing a three-dimensional geometric model, and obtaining the spatial distribution of a three-dimensional magnetic field through magnetic field simulation software; then, introducing the three-dimensional geometric model and the magnetic field data into a particle simulation solver VORPAL to obtain the position, energy and incident angle distribution of incident ions bombarded on the surface of the magnetic pole material; then, considering the characteristics of the cylindrical anode layer Hall thruster, and establishing a sputtering model; then from the incident ion energy E0And distribution of incident angle theta, and energy threshold E of magnetic pole materialdObtaining the atom number sputtered by an incident ion through a sputtering model; finally, the etching rate expression of the magnetic pole of the thruster can be deduced according to the etching depth h of the magnetic pole of the thruster and the conservation formula of the quantity of incident ionsThe service life of the thruster can be evaluated through the distribution of the etching rate.
Description
Technical Field
The invention belongs to a simulation method, and particularly relates to a simulation method for service life evaluation of a cylindrical anode layer Hall thruster.
Background
Hall thrusters applied in the aerospace field are mainly of two types: a steady State Plasma Thruster (SPT) and an anode layer plasma Thruster (TAL). The greatest difference between the two is the length of the acceleration channel and the material of the inner wall of the acceleration channel. The SPT accelerating channel is larger than TAL, and the inner wall of the accelerating channel is made of insulating materials such as boron nitride. The TAL accelerating channel is shorter and the inner wall of the accelerating channel adopts metal with conductive property, so that only few secondary electrons are emitted, and the secondary electron emission coefficient is much lower than that of SPT.
The cylindrical anode layer Hall thruster belongs to an anode layer Hall thruster and is a thruster type with great development potential in the aspects of high voltage and high efficiency. However, the self-sputtering phenomenon is a major problem restricting the development of the cylindrical anode layer hall thruster application. The self-sputtering is a phenomenon that some parts inside the device are bombarded by ions with higher energy in the operation process of the device, so that particles on the surfaces of the parts are sputtered. A great deal of related research shows that the ion self-sputtering is one of the key factors for limiting the service life of the propeller. For the electric thruster which runs in the outer space for a long time, the service life of the thruster is a key problem. Although the electric thruster can work for years with dozens of kilograms of propellant, if the service life of the electric thruster is not long enough, the electric thruster can not exert the advantages of the electric thruster. For the cylindrical anode layer Hall electric thruster, most of etching products in the thruster are metal particles, and a part of metal particles are retained in the thruster and can influence the efficiency and working parameters of the thruster; and a part of the solar energy moves out of the thruster to affect the solar cell and other optical components.
The etching of the magnetic poles of the hall thruster by ion sputtering is a rather lengthy process. Resulting in the electromagnetic field eventually distorting, which typically runs for thousands of hours at the end of the propeller's useful life. The traditional method for evaluating the service life of the Hall thruster is to simulate the actual working condition of the thruster in a large-scale ground vacuum chamber, and record the accumulated running time after the thruster runs for a long time until the thruster can not normally discharge. Since such long run tests incur a significant cost (one test costs over millions of dollars), it is of great advantage to analyze the etching process of the hall thruster through theoretical and simulation. The existing service life evaluation methods of the Hall plasma thruster are all aimed at a steady-state Hall thruster and are all ceramic surface etching rates obtained based on the sputtering coefficient Y (E, theta) of surface materials. The cylindrical anode layer Hall thruster has an electromagnetic field configuration which is greatly different from that of a steady-state Hall thruster and is a metal wall. The conventional life evaluation method is not suitable for the cylindrical anode layer hall thruster.
Disclosure of Invention
The invention aims to provide a simulation calculation method for service life evaluation of a cylindrical anode layer Hall thruster, which can solve the problems that the conventional thruster service life evaluation method is not suitable for the cylindrical anode layer Hall thruster and the service life evaluation is high in cost and long in time by using experiments.
The technical scheme of the invention is as follows: the simulation calculation method for service life evaluation of the Hall thruster of the cylindrical anode layer comprises the following steps:
(1) carrying out three-dimensional geometric structure modeling, and repairing the output gridding geometric model;
(2) performing magnetic field simulation to obtain the distribution of three-dimensional magnetic field data in the inner space of the cylindrical anode layer Hall thruster;
(3) compiling python program based on a Vorpal solver, importing the gridded geometric model and three-dimensional magnetic field data, and then solving to obtain ion energy E incident to the surfaces of the magnetic poles of the thruster at different times and different positions0And the distribution of the angle of incidence θ;
(4) according to the characteristics of the cylindrical anode layer Hall thruster, a collision sputtering model for bombarding the surface of the magnetic pole of the thruster to incident ions and magnetic pole materials is established;
(5) from incident ion energy E0And distribution of incident angle theta, and energy threshold E of magnetic pole materialdObtaining an atomic number n (E) of incident ion etching0，θ，Ed) I.e., the sputtering coefficient;
(6) the etching rate expression of the magnetic pole of the thruster can be deduced according to the etching depth h of the magnetic pole of the thruster and the conservation formula of the quantity of incident ions, and the service life of the thruster can be evaluated through the distribution of the etching rate.
Wherein, after the optimal gridding geometric model in the step (1) and the three-dimensional magnetic field data in the step (2) are obtained, a vorpal solver is introduced in the step (3) to obtain the energy E of the incident ions0And the distribution of the incident angle theta.
Wherein, in the step (5)
In the formula, m1Is the mass of the incident ion, m2Is the mass of the sputtered atom, θ is the angle of incidence of the ion, EdIs the energy threshold of the target atom, E0Is the energy of the incident ions.
Obtaining an expression of the etching rate Es in the step (6):
the invention has the beneficial effects that: the method can obtain the etching rate distribution of different positions on the surface of the magnetic pole of the thruster under different operating conditions. By comparison of etching rate distribution under different working conditions, comprehensive comparison of parameters such as thrust, specific impulse and discharge efficiency is combined. And further carrying out service life evaluation on the cylindrical anode layer Hall thruster.
Detailed Description
The present invention will be described in further detail with reference to specific examples.
A simulation calculation method for service life evaluation of a cylindrical anode layer Hall thruster comprises the following steps:
(1) and carrying out three-dimensional geometric structure modeling, and repairing the output gridding geometric model.
(2) And performing magnetic field simulation to obtain the distribution of the three-dimensional magnetic field data in the inner space of the cylindrical anode layer Hall thruster.
(3) Compiling python program based on a Vorpal solver, importing the gridded geometric model and three-dimensional magnetic field data, and then solving to obtain ion energy E incident to the surfaces of the magnetic poles of the thruster at different times and different positions0And the distribution of the incident angle theta.
(4) According to the characteristics of the cylindrical anode layer Hall thruster, a collision sputtering model for bombarding the surface of the magnetic pole of the thruster to incident ions and magnetic pole materials is established.
(5) From incident ion energy E0And the distribution of the incident angle theta and the energy threshold Ed of the magnetic pole material to obtain the atomic number n (E) of the incident ion etching0，θ，Ed) I.e. the sputtering coefficient.
(6) And deducing an etching rate expression of the magnetic pole of the thruster according to the etching depth h of the magnetic pole of the thruster and an incident ion quantity conservation formula. The service life of the thruster can be evaluated through the distribution of the etching rate.
Wherein, after the optimal gridding geometric model in the step (1) and the three-dimensional magnetic field data in the step (2) are obtained, a vorpal solver is introduced in the step (3) to obtain the energy E of the incident ions0And the distribution of the incident angle theta.
Wherein, in the step (5)
m1Is the mass of the incident ion, m2Is the mass of the sputtered atom, θ is the angle of incidence of the ion, EdIs the energy threshold of the target atom, E0Is the energy of the incident ions.
Obtaining an expression of the etching rate Es in the step (6):
the method adopts a numerical simulation method, and is based on VORPAL simulation software developed by the American Tech-X company to comprehensively and accurately model and analyze the electron and ion behaviors in the discharging process, so as to obtain the distribution of ion positions, energy and incident angles on the surface of the magnetic pole of the thruster, and further evaluate the service life of the thruster by utilizing a sputtering coefficient formula and an etching rate formula. The specific implementation mode comprises the following steps:
(1) and (3) carrying out three-dimensional geometric structure modeling by using three-dimensional drawing software AutoCAD or VariCAD to obtain a gridded geometric structure model, and storing the gridded geometric structure model into STP (Standard transfer template) and STL (Standard transfer template) formats for later use. And performing mesh repairing on the output gridded geometric model in the STL format.
(2) And (3) importing the STP format three-dimensional geometric model stored in the first step into an innovative Magnetic field simulation software for Magnetic field simulation, and acquiring three-dimensional Magnetic field data inside the cylindrical anode layer Hall thruster. And the acquired three-dimensional data is arranged according to the requirement of a python program written in the following Vorpal simulation.
(3) The python program is written based on a Vorpal solver, and comprises an electromagnetic field solving module program, a particle module program, a Monte Carlo collision module program and a data recording and storing module program. And leading in the STL-format gridding geometric model obtained in the first step and the three-dimensional magnetic field data obtained in the second step, and then solving to obtain the ion coordinate position (x, y, z) incident to the magnetic pole surface of the thruster and the corresponding ion energy E0And the distribution of the incident angle theta.
(4) According to the characteristics of the cylindrical anode layer Hall thruster, a collision sputtering model for bombarding incident ions on the surface of a magnetic pole of the thruster and magnetic pole materials is established: assuming mass m1At a velocity v in the direction of the incident angle theta1And mass m2The magnetic pole material atoms a elastically collide. Part of energy obtained after the atoms a are collided is used for overcoming the wall material of the Hall thruster of the anode layerEnergy threshold E of materialdThe excess energy is used to elastically collide with the next atom b, which gets a recoil momentum to detach from the material surface. And a part of the energy gained by the atoms b is used to overcome the energy threshold E of the materialdThe remaining energy will be used again for the next collision, and the process is repeated until the atoms of the wall material during the collision acquire insufficient energy to overcome the energy threshold E of the materiald。
(5) And obtaining the average energy obtained by sputtering atoms after one collision according to the magnetic pole sputtering model of the cylindrical anode layer Hall thruster established in the fourth step and the momentum and energy conservation law:
m1is the mass of the incident ion, m2Is the mass of the sputtered atom, θ is the angle of incidence of the ion, E1The energy of the incident ions before collision. This fraction of energy is used to overcome the energy threshold E of the material according to the sputtering modeldAnd escape, the remaining energyThe same collision process will occur with the next material atom, and so on until the energy obtained by the wall material atoms during the collision process is insufficient to overcome the energy threshold E of the materiald. The condition for the nth atom to be sputtered is that the energy value after overcoming the energy threshold of the material is greater than or equal to zero. Both is
In combination with the above formula, atoms having a sputtering atomic number of half or more are considered to be sputtered, and therefore, a coefficient of 0.5 is added thereto. Recombination ofThe energy E of the incident ion obtained in the fourth step0And distribution of incident angle theta, and energy threshold E of magnetic pole materialdThe number of sputtering atoms n that can be obtained by one incident ion is:
(6) assuming that the etching depth h of the magnetic pole of the thruster is m, the number of ions incident to the surface of the magnetic pole within t time is m, and obtaining the ion etching depth by combining an incident ion number conservation formula
Therefore, the expression Es of the etching speed of the magnetic pole of the thruster can be obtained, and the service life of the thruster can be evaluated through the distribution of the etching speed.
Claims (4)
1. The simulation calculation method for service life evaluation of the Hall thruster of the cylindrical anode layer is characterized by comprising the following steps of: the method comprises the following steps:
(1) carrying out three-dimensional geometric structure modeling, and repairing the output gridding geometric model;
(2) performing magnetic field simulation to obtain the distribution of three-dimensional magnetic field data in the inner space of the cylindrical anode layer Hall thruster;
(3) compiling python program based on a Vorpal solver, importing the gridded geometric model and three-dimensional magnetic field data, and then solving to obtain ion energy E incident to the surfaces of the magnetic poles of the thruster at different times and different positions0And the distribution of the angle of incidence θ;
(4) according to the characteristics of the cylindrical anode layer Hall thruster, a collision sputtering model for bombarding the surface of the magnetic pole of the thruster to incident ions and magnetic pole materials is established;
(5) from incident ion energy E0And distribution of incident angle theta, and magnetic poleEnergy threshold E of materialdObtaining an atomic number n (E) of incident ion etching0，θ，Ed) I.e., the sputtering coefficient;
(6) the etching rate expression of the magnetic pole of the thruster can be deduced according to the etching depth h of the magnetic pole of the thruster and the conservation formula of the quantity of incident ions, and the service life of the thruster can be evaluated through the distribution of the etching rate.
2. The simulation calculation method for lifetime evaluation of a hall thruster of a cylindrical anode layer according to claim 1, wherein: wherein, after the optimal gridding geometric model in the step (1) and the three-dimensional magnetic field data in the step (2) are obtained, a vorpal solver is introduced in the step (3) to obtain the energy E of the incident ions0And the distribution of the incident angle theta.
3. The simulation calculation method for lifetime evaluation of a hall thruster of a cylindrical anode layer according to claim 1, wherein: wherein, in the step (5)
In the formula, m1Is the mass of the incident ion, m2Is the mass of the sputtered atom, θ is the angle of incidence of the ion, EdIs the energy threshold of the target atom, E0Is the energy of the incident ions.
4. The simulation calculation method for lifetime evaluation of a hall thruster of a cylindrical anode layer according to claim 1, wherein: obtaining an expression of the etching rate Es in the step (6):
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112329247A (en) * | 2020-11-11 | 2021-02-05 | 成都理工大学工程技术学院 | Simulation method for discharge plasma and self-sputtering of Hall electric thruster |
| CN112347610A (en) * | 2020-09-30 | 2021-02-09 | 兰州空间技术物理研究所 | Hall thruster life evaluation method based on hollow cathode |
| CN112628098A (en) * | 2020-12-03 | 2021-04-09 | 核工业西南物理研究院 | Hall accelerator with sinking type hollow inner magnetic pole structure |
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Cited By (4)
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