CN111177910B - Numerical simulation method for inducing spacecraft to discharge by releasing neutral gas - Google Patents
Numerical simulation method for inducing spacecraft to discharge by releasing neutral gas Download PDFInfo
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Abstract
A numerical simulation method for inducing spacecraft discharge by releasing neutral gas includes the steps of giving out seed currents such as field current and thermal current under initial or specific conditions, considering initial states of surrounding plasmas and material outgassing, solving particle tracks and particle and gas collision reaction processes in space through a particle simulation method and a Monte Carlo method respectively, and researching changes of gas pressure and discharge intensity in the processes, so that influence degrees and rules of the spacecraft discharge induced by releasing neutral gas under different initial conditions are obtained. The method can assist in analyzing the influence mechanism of neutral gas released in the charging and discharging process of the spacecraft surface, can be used for analyzing the conversion threshold value of non-self-sustaining to self-sustaining and avalanche discharging possibly occurring in the charging and discharging process of spacecraft charged parts with different air pressures and different structures through calculation, and can be used as a basic method for researching the process of jointly inducing the charging and discharging of the spacecraft in various complex environments, so that the spacecraft can be scientifically and effectively designed and reinforced.
Description
Technical Field
The invention belongs to the technical field of spacecraft protection and reinforcement, and relates to a numerical simulation method for inducing spacecraft discharge by releasing neutral gas, which is used for analyzing and researching the influence of the neutral gas release on the spacecraft discharge, in particular to the law and mechanism of the induction influence.
Background
Electrostatic Discharge (ESD) caused by charge and Discharge effects is one of the main causes of a mission failure of a spacecraft. Through several decades of key researches, great amount of research achievements are obtained in aerospace countries such as Europe and America in aspects of spacecraft charging mechanism, charge-discharge effect evaluation, engineering protection and the like, and are successfully applied to various in-orbit spacecrafts. Despite of a relatively sufficient protection design, due to environmental factors such as geomagnetic substorm and the like, the abnormality caused by spacecraft discharge still frequently occurs, and people are difficult to clearly determine specific discharge reasons and discharge parts, not to mention the analysis of the possibly existing cooperative discharge phenomenon in the process. Neutral gases are considered to be a key analytical factor in this process.
In a space vacuum environment, neutral gas is released in many cases: neutral gases released during spacecraft propulsion, degassing of surface materials, and trim gases to adjust attitude, among others. Neutral gases themselves have no direct effect on the spacecraft charging, but when neutral gases are ionized on the spacecraft surface, the ionized gases can affect the spacecraft surroundings: 1) Due to the charge attraction effect, ions and electrons returned to the spacecraft can effectively reduce the phenomena of electrification and unequal charging of the spacecraft; 2) The charge adsorption can cause the surface pollution of the material, the temperature of the material is increased, and the characteristic parameters of the material are changed; 3) Gas ionization can improve plasma conductivity and induce surface discharge; 4) Short periods of insufficient ionization of the neutral gas can cause a momentary increase in pressure between the charged surfaces (or electrodes) and can provide environmental conditions for the interplay and synergy of low pressure and vacuum discharges. Under normal conditions, the surface air pressure of the in-orbit spacecraft is in a continuous and stable low state, and the influence on the spacecraft is not very serious. However, when the surface of the material is bombarded by debris, meteorons, high-energy particle beams and the like, or in the process of arc discharge (including surface discharge and medium deep discharge), the material has a short and violent outgassing phenomenon. The process is accompanied by a large amount of influences of surface pollution of the spacecraft, material characteristic change caused by temperature rise, radiation-induced conductivity change and the like, and can also induce gas breakdown to generate low-pressure discharge or cooperative discharge, and the series of influences are all likely to cause the actual charge and discharge conditions of the spacecraft to exceed the design consideration, so that the spacecraft is abnormal. The explanation for the more reliable neutral gas induced discharge is that the neutral gas will be ionized at the beginning of the discharge, the ionized electrons will further excite and ionize the background gas under the influence of the accelerating field, and once the avalanche effect is generated, a larger discharge current will be generated, thereby causing damage to the spacecraft electronics.
In order to meet the research requirements of the charge and discharge effect of the spacecraft and promote the technical research of the electrostatic protection and reinforcement of the spacecraft, a method is urgently needed to be provided for researching the process of jointly inducing the charge and discharge of the spacecraft in various complex environments so as to more scientifically and effectively design and reinforce the spacecraft.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the method can obtain the influence degree and rule of the discharge of the spacecraft induced by the release of the neutral gas under different initial conditions, and provides a foundation for designing and reinforcing the spacecraft.
The technical solution of the invention is as follows:
a numerical simulation method for inducing spacecraft discharge by releasing neutral gas comprises the following steps:
1) Carrying out calculation initialization;
2) Carrying out regional modeling aiming at a spacecraft structure to be researched, obtaining a spacecraft discharge model and a calculation region, dividing grids, placing the spacecraft discharge model on the grids, and redistributing grid attributes according to the shape and characteristics of a spacecraft material;
3) Setting related boundary conditions, and determining a calculated initial state by correcting the distribution of related initial particles and the sizes of an electric field and a magnetic field;
4) After the calculation is started, under each time step, considering the particle emission boundary, and generating new particles in a specific grid;
5) Calculating the current density and the charge density of each grid, and weighting the current density and the charge density to the corresponding positions of the particles;
6) Solving a Poisson equation to obtain the potential distribution and the electric field distribution of the calculation region;
7) Updating the momentum and position of the particles with the electric potential and electric field values;
8) Solving the processes of particle collision, excitation, reaction and deposition by using a Monte Carlo method according to a spacecraft discharge model, and correcting the momentum and the position of the collision or reaction particles;
9) Considering the extinction on the particle boundary and the generation of secondary electrons/ions on the conductor or medium, estimating the air pressure change based on the particle generation and extinction statistics and the air pressure diffusion factor, and entering the step 10);
10 Judging whether the calculation result reaches balance or whether the calculation reaches preset time, if not, increasing the time, repeating the steps from 4) to 9) at the next time step until the balance is reached or the calculation reaches the preset time, outputting the particle number, energy distribution and position in the whole calculation process, and finishing the numerical simulation of the neutral gas release induced spacecraft discharge under the current initial condition.
In the step 2), the grid properties include conductivity and dielectric constant.
In the step 3), the boundary conditions include field boundary conditions and particle boundary conditions.
In the step 3), the calculated initial state is obtained by fitting the initial particle environment on the surface of the spacecraft and the geomagnetic field environment.
In the step 9), when the generation of secondary electrons/ions on the conductor or the medium is considered, the electron or ion is considered to be static when the energy of the electron or ion is lower than a threshold value, and the threshold value is 30-50 eV without considering the movement of the electron or ion.
In the step 9), a stable or dynamic air pressure model is adopted to estimate the air pressure change, and the air pressure model is used for simulating the air pressure and energy distribution of neutral gas on the surface of the spacecraft discharge material when the spacecraft material is severely deflated.
In the step 4), a seed current model is applied to generate new particles, wherein the seed current model comprises a thermionic emission model and a field emission model, the field emission model is mainly used, and when the temperature of an emitter is higher, the thermionic emission model is used as a correction model of the field emission model to realize field emission or thermal field induced emission between adjacent conductors or media.
In the step 10), when the total number of electrons in the calculation region fluctuates by less than 5% within 100 time steps, the calculation process is considered to reach an equilibrium.
In the step 7), the method for updating the momentum and the position of the particles is as follows:
and calculating the electric field distribution according to the electric potential distribution of the calculation region, then weighting to the position of each particle to calculate the electric field force of the position of each particle, and pushing the particles with the current step length to move through Newton's law so as to realize the update of the positions and the momentum of the particles.
Compared with the prior art, the invention has the advantages that:
(1) The invention provides a numerical simulation method for inducing space spacecraft discharge based on neutral gas release, which can obtain the influence degree and rule of the neutral gas release to induce the spacecraft discharge under different initial conditions.
(2) The method can assist in analyzing an influence mechanism of neutral gas released in the charging and discharging process of the surface of the spacecraft, can calculate and analyze the conversion threshold value of non-self-sustaining to self-sustaining and avalanche discharging possibly occurring in the charging and discharging process of spacecraft charged parts with different air pressures and different structures, and can be used as a basic method for researching the process of jointly inducing the charging and discharging of the spacecraft in various complex environments, so that the design and the reinforcement of the spacecraft can be more scientifically and effectively carried out.
Drawings
FIG. 1 is a flow chart of the method of the present invention.
Detailed Description
In order to improve the safety and reliability of a spacecraft and strengthen the effective protection and reinforcement of the discharge hazard of the spacecraft, the mechanism research of the discharge process needs to be deepened urgently, and the detailed analysis is carried out on the key influence factors which are mutually restricted or mutually cooperated, the invention provides a numerical simulation method for inducing the discharge of the spacecraft by releasing neutral gas based on the charge-discharge effect of the spacecraft, which comprises the following steps: the method comprises the steps of firstly, providing seed currents such as field current and thermal current under initial or specific conditions, considering initial states of surrounding plasmas and material outgassing, then solving a particle track in a space and a particle and gas collision reaction process through a particle simulation method and a Monte Carlo method, and researching changes of gas pressure and discharge intensity in the process, so that the influence degree and law of the spacecraft discharge induced by neutral gas release under different initial conditions are obtained.
As shown in fig. 1, the steps of the present invention are as follows:
a numerical simulation method for inducing spacecraft discharge through neutral gas release comprises the following steps:
1) Carrying out calculation initialization;
2) Carrying out regional modeling aiming at a spacecraft structure to be researched, obtaining a spacecraft discharge model and a calculation region, dividing grids, placing the spacecraft discharge model on the grids, and redistributing grid properties including conductivity, dielectric constant and the like according to the shape and characteristics of a spacecraft material;
3) Setting related boundary conditions (field boundary conditions and particle boundary conditions), and determining a calculated initial state (obtained by fitting an initial particle environment on the surface of the spacecraft and a geomagnetic field environment) by correcting the distribution of related initial particles and the sizes of an electric field and a magnetic field;
4) After the calculation is started, under each time step, considering the particle emission boundary, and generating new particles in a specific grid;
and generating new particles by applying a seed current model, wherein the seed current model comprises a thermionic emission model and a field emission model, and the thermionic emission model is taken as a correction model of the field emission model when the temperature of the emitter is higher so as to realize (thermal) field emission between adjacent conductors or mediums.
5) Calculating the current density and the charge density of each grid, and weighting the current density and the charge density to the corresponding positions of the particles;
6) Solving a Poisson equation to obtain the potential distribution and the electric field distribution of the calculation region;
7) Updating the momentum and position of the particles with the electric potential and electric field values;
the method of updating the particle position is as follows:
and calculating the electric field distribution according to the electric potential distribution of the calculation region, then calculating the electric field force of the position of each particle by weighting the position of each particle, and pushing the particles with the current step length to move through Newton's law so as to realize the update of the positions and the momentum of the particles.
8) Solving the processes of particle collision, excitation, reaction and deposition by using a Monte Carlo method according to a spacecraft discharge model, and correcting the momentum and the position of the collision or reaction particles;
9) Considering the extinction on the particle boundary and the generation of secondary electrons/ions on the conductor or medium, estimating the air pressure change based on the particle generation and extinction statistics and the air pressure diffusion factor, and entering the step 10);
considering secondary electron/ion generation on a conductor or medium, electrons or ions are considered to be stationary when their energy is below a threshold, which is 30-50 eV, regardless of their motion.
Estimating the air pressure change by adopting a stable or dynamic air pressure model, wherein the air pressure model is used for simulating the air pressure and energy distribution of neutral gas on the surface of a spacecraft discharge material when the spacecraft material is violently deflated; the instantaneity is considered in the stable air pressure model, the dynamic air pressure model is relatively accurate, and slightly long discharge time is considered.
10 Judging whether the calculation result reaches balance or whether the calculation reaches preset time, if not, increasing the time, repeating the steps from 4) to 9) at the next time step until the balance is reached or the calculation reaches the preset time, outputting the particle number, energy distribution and position in the whole calculation process, and finishing the numerical simulation of the neutral gas release induced spacecraft discharge under the current initial condition.
The calculation process is considered to be in equilibrium when the total number of electrons in the calculation region fluctuates by less than 5% over 100 time steps.
The spacecraft discharge model adopts a particle impact ionization/reaction model, and researches self-sustaining/non-self-sustaining and avalanche discharge phenomena possibly generated by electron beam impact neutral gas or plasma on the basis of the physical process and impact cross section of neutral gas ionization of particle impact.
The invention provides a new research method for researching the spacecraft discharge phenomenon under the environment factors of the complex space, can analyze the discharge condition and threshold value problem of the spacecraft under the complex structure or material distribution, can simultaneously meet the analysis requirements of high precision and real-time performance, can calculate and analyze the discharge mechanism when different air pressures and structures are electrified, can carry out deep research on the multi-factor environmental influence of plasma, particle radiation, ultraviolet rays, surface pollution and the like under the background of neutral gas and the spacecraft discharge mechanism under the coordination, and lays a foundation for developing the analysis of the multi-effect and multi-environment factor comprehensive effect of the spacecraft.
The invention not only meets the research requirement of the charge and discharge effect of the spacecraft, but also can promote the research of the electrostatic protection and reinforcement technology of the spacecraft.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are not particularly limited to the specific examples described herein.
Claims (9)
1. A numerical simulation method for inducing spacecraft discharge by releasing neutral gas is characterized by comprising the following steps:
1) Carrying out calculation initialization;
2) Performing region modeling aiming at a spacecraft structure to be researched to obtain a spacecraft discharge model and a calculation region, dividing a grid, placing the spacecraft discharge model on the grid, and redistributing grid attributes according to the shape and characteristics of a spacecraft material;
3) Setting related boundary conditions, and determining a calculated initial state by correcting the distribution of related initial particles and the sizes of an electric field and a magnetic field;
4) After the calculation is started, under each time step, considering the particle emission boundary, and generating new particles in a specific grid;
5) Calculating the current density and the charge density of each grid, and weighting the current density and the charge density to the corresponding positions of the particles;
6) Solving a Poisson equation to obtain the potential distribution and the electric field distribution of the calculation region;
7) Updating the momentum and position of the particles with the electric potential and electric field values;
8) Solving the processes of particle collision, excitation, reaction and deposition by using a Monte Carlo method according to a spacecraft discharge model, and correcting the momentum and the position of the collision or reaction particles;
9) Considering the extinction on the particle boundary and the generation of secondary electrons/ions on the conductor or medium, estimating the air pressure change based on the particle generation and extinction statistics and the air pressure diffusion factor, and entering the step 10);
10 Judging whether the calculation result reaches balance or whether the calculation reaches preset time, if not, increasing the time, repeating the steps from 4) to 9) at the next time step until the balance is reached or the calculation reaches the preset time, outputting the particle number, energy distribution and position in the whole calculation process, and finishing the numerical simulation of the neutral gas release induced spacecraft discharge under the current initial condition.
2. A method of numerical simulation of neutral gas release induced spacecraft electrical discharge according to claim 1, wherein: in the step 2), the grid properties include conductivity and dielectric constant.
3. A method of numerical simulation of neutral gas release induced spacecraft electrical discharge according to claim 1, wherein: in the step 3), the boundary conditions include field boundary conditions and particle boundary conditions.
4. The method according to claim 1, wherein the method comprises the following steps: in the step 3), the calculated initial state is obtained by fitting the initial particle environment on the surface of the spacecraft and the geomagnetic field environment.
5. The method according to claim 1, wherein the method comprises the following steps: in the step 9), when secondary electrons/ions are generated on the conductor or the medium, the conductor or the medium is determined to be static when the energy of the electrons or the ions is lower than a threshold value, and the threshold value is 30-50 eV without considering the movement of the electrons or the ions.
6. A method of numerical simulation of neutral gas release induced spacecraft electrical discharge according to claim 1, wherein: in the step 9), a stable or dynamic air pressure model is adopted to estimate the air pressure change, and the air pressure model is used for simulating the air pressure and energy distribution of neutral gas on the surface of the spacecraft discharge material when the spacecraft material is severely deflated.
7. A method of numerical simulation of neutral gas release induced spacecraft electrical discharge according to claim 1, wherein: in the step 4), a seed current model is applied to generate new particles, wherein the seed current model comprises a thermal electron emission model and a field emission model, the field emission model is mainly used, and when the temperature of an emitter is higher, the thermal electron emission model is used as a correction model of the field emission model to realize field emission or thermal field-induced emission between adjacent conductors or media.
8. A method of numerical simulation of neutral gas release induced spacecraft electrical discharge according to claim 1, wherein: in the step 10), when the total number of electrons in the calculation region fluctuates by less than 5% within 100 time steps, the calculation process is considered to reach an equilibrium.
9. The method according to claim 1, wherein the method comprises the following steps: in the step 7), the method for updating the momentum and the position of the particles is as follows:
and calculating the electric field distribution according to the electric potential distribution of the calculation region, then calculating the electric field force of the position of each particle by weighting the position of each particle, and pushing the particles with the current step length to move through Newton's law so as to realize the update of the positions and the momentum of the particles.
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| JP2008031515A (en) * | 2006-07-28 | 2008-02-14 | National Institute Of Advanced Industrial & Technology | Microwave plasma analysis program |
| CN106697338A (en) * | 2015-07-15 | 2017-05-24 | 北京卫星环境工程研究所 | Spacecraft potential active control method based on neutral gas release |
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