CN109726458A - A kind of geostationary orbit material inequality electrification emulation mode - Google Patents
A kind of geostationary orbit material inequality electrification emulation mode Download PDFInfo
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- CN109726458A CN109726458A CN201811555475.1A CN201811555475A CN109726458A CN 109726458 A CN109726458 A CN 109726458A CN 201811555475 A CN201811555475 A CN 201811555475A CN 109726458 A CN109726458 A CN 109726458A
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Abstract
The invention discloses a kind of geostationary orbit material inequalities to charge emulation mode.It being capable of the effectively inequality charge process of simulation analysis spacecraft different surfaces structure, different materials on geostationary orbit using the present invention.The present invention constructs spacecraft surface material structure equivalent model, geo-stationary orbit magnetic storm plasma distribution profile is fitted using the bi-Maxwellian distribution of electronics and ion, it is composed then in conjunction with material secondary electronic emission spectrum and photoelectron emissions, utilize the effective simulation analysis geo-stationary orbit Spacecraft Material inequality charged effect process of PIC (Particle-In-Cell) method, it is clear with simulation process, the advantages that analog result and actual monitoring electrification situation relatively meet, important references are provided for the antistatic protection design of spacecraft representative region material structure and surface potential active control.
Description
Technical field
The present invention relates to space environment simulation technical fields, are suitable for geostationary orbit (Geosynchronous
Earth Orbit) spacecraft surface adjacent materials inequality charge (Differential Charging) process simulation, tool
Body is related to the spacecraft surface inequality charged effect emulation point when a kind of GEO substorm occurs under magnetic storm plasma environment
Analysis method.
Background technique
Geostationary orbit ground level is about 36000km, it is generally the case that entire track comes from the sun through sunny slope
The high energy electron ion cloud (Chang Yinqi GEO substorm) of wind, outer Van Allen belt and the low energy in earth's shadow area are highdensity
Plasma environment.Since the perforative region of geo-stationary orbit is different, without same district area plasma energy and temperature, there are huge
Difference, so as to form the charging environment that geo-stationary orbit spacecraft is extremely harsh.
Spacecraft in orbit when with the factor interactions such as ambient space plasma, solar radiation and magnetic field environment,
It will lead to space charge to accumulate to form surface electrification on spacecraft surface.Since the characteristic of spacecraft surface different materials is different,
Lead to the differentiation of surface potential, and then forms inequality electrification.The inequality electrification of material surface depends not only on spacecraft
The plasmoid of surrounding, it is also related to the secondary electron of surfacing, backscattered electron, photoelectron emissions characteristic, simultaneously
Body Leakage Current by material is influenced.Inequality charges the surface contamination in addition to that can aggravate spacecraft, reduces surfacing
Hot property, and influence outside Space environment detection, it is mainly shown as static discharge.Serious inequality electrification occurs mainly in earth magnetism
Geostationary orbit when substorm injects and there are the auroral region of aurora electron precipitation, but the electrification of geo-stationary orbit inequality occurs
Frequency and charge level it is higher than polar region.
Since the dielectric property of spacecraft outer surface material, illumination condition, geometry are different, inequality electrification
Specific manifestation are as follows: generate potential difference between spacecraft adjacent external surfaces, between surface and spacecraft " ground ".It studies in space environment
Interaction between the different materials of spacecraft surface is a complicated job, and difficulty is mainly manifested in when a surface
When current potential changes, adjacent all surface current potential also has to change therewith.Correspondingly, the change of other surface potentials
Change the current potential that can also influence first surface and other more surfaces in turn.Also, inequality electrification can be in adjacent difference
Material surface is formed about local potential well and potential barrier, and the formation of potential well will affect photoelectron, the backscattered electron of material surface again
With the transmitting of secondary electron, and then influence material surface Potential distribution.
The surface inequality electrification formed by environment magnetic storm is to influence the important original of geo-stationary orbit spacecraft safe operation
One of because.After inequality electrification in spacecraft surface meets or exceeds Spacecraft Material breakdown threshold, static discharge will be generated,
It may induce Spacecraft anomaly, or even failure.
Have some analysis methods that can be used for the electrification emulation of geo-stationary orbit material inequality, such as the U.S. in the world at present
The geo-stationary orbit spacecraft charging effect emulation mode of NASA and geo-stationary orbit spacecraft-magnetic storm plasma phase interaction of ESA
With analogy method, but these analogy methods all concentrate on the group effect emulation charged to spacecraft surface.The country is in this respect
Research be in the starting stage, had no in document geo-stationary orbit Spacecraft Material inequality charge emulation mode.
Summary of the invention
In view of this, the present invention provides a kind of geostationary orbit material inequalities to charge emulation mode, it can be effective
Ground simulation analysis spacecraft different surfaces structure, inequality charge process of the different materials on geostationary orbit.
Geostationary orbit material inequality of the invention charges emulation mode, includes the following steps:
Step 1, the characteristic parameter data library of the used material in space is established；
Step 2, the plasma point of the bi-Maxwellian distribution fitting geostationary orbit of electronics and ion is respectively adopted
Cloth state；
Step 3, according to spacecraft surface material structure, material area and earthing mode to be emulated, equivalent model is constructed；
Wherein, the structure of equivalent model are as follows: dielectric-dielectric structure and/or dielectric-metal structure；The connection side of material in equivalent model
Formula are as follows: flush and/or overlap；
Step 4, the equivalent model to simulating area that steps for importing three constructs in PIC, and assign step 1 database
In respective material characterisitic parameter；The electronics bi-Maxwellian distribution and ion bi-Maxwellian distribution constructed according to step 2
Construct simulated environment；Then it calculates to obtain using PIC method and charges simulation result to the material inequality of simulating area.
Further, the characterisitic parameter of the material includes: secondary electron emission characteristic parameter, the photoelectron emissions of material
The charge leakage characterisitic parameter of characterisitic parameter and material；And the density of material, relative dielectric constant, surface resistivity, body electricity
Conductance and thickness.
Further, the photoelectron emissions characterisitic parameter of material is obtained by testing experiment, wherein when test, using light
Spectral limit is the deuterium lamp simulated solar ultraviolet light of 115~400nm.
Further, it in the PIC method of the step 4, simulates macro number of particles in each grid in space and is greater than 5, protecting
Shorten while demonstrate,proving simulation accuracy and calculates the time.
The utility model has the advantages that
(1) present invention building spacecraft surface material structure equivalent model, utilizes double Maxwells of electronics and ion point
Cloth is fitted geo-stationary orbit magnetic storm plasma distribution profile, composes then in conjunction with material secondary electronic emission spectrum and photoelectron emissions, benefit
It being capable of effectively simulation analysis geo-stationary orbit material inequality charge process with PIC method.
(2) superposition that the electronics in the present invention in geo-stationary orbit magnetic storm plasma and ion are distributed by two kinds is come table
Show, realize the fitting of the most harsh charging environment of geo-stationary orbit, fitting result more meets real space conductive environment, is beneficial to multiple
Miscellaneous structural material inequality electrification situation is emulated.
(3) polyimides, polytetrafluoroethylene (PTFE) and quartz glass etc. are chosen in the embodiment of the present invention be used as typical space medium
Material；Aluminium, copper and silver etc. are chosen as Typical Metals and carries out sample preparation, sample test covers spacecraft and often uses material
Material.In spacecraft labyrinth material modeling corresponding material type and parameter can be chosen according to real material structure.
(4) present invention establishes equivalent model to spacecraft surface labyrinth material, according to practical spacecraft surfacing
Layout carries out structural modeling, determines equivalent earthing mode, guarantees that simulation model is consistent with practical spacecraft structure.
(5) have can corrective and expansible for space of embodiment of the present invention common used material and new material characteristic parameter data library
Property.The setting of spacecraft surfacing is called directly using database mode, with space common used material parameter measurement accuracy
The discovery and preparation with space new material are improved, the measurement data of existing material may be updated in database and space green wood can be added
Expect parameter.
Detailed description of the invention
Fig. 1 is flow chart of the present invention.
Fig. 2 is the double Maxwell's fitting results of geo-stationary orbit magnetic storm plasma.Wherein, figure (a) and figure (b) are respectively same
Walk the fitting result of orbital electron and ion.
Fig. 3 is space material structure equivalent model.
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
The present invention provides a kind of geostationary orbit material inequalities to charge emulation mode, in conjunction with double Maxwellian electrons
With the charge leakage characteristic of ion distribution spectrum, the secondary electron emission characteristic of material, photoelectron emissions characteristic and material, utilize
PIC (Particle-In-Cell) method being capable of effective simulation analysis geo-stationary orbit Spacecraft Material inequality charged effect mistake
Journey has many advantages, such as that simulation process is clear, and it is spacecraft representative region material that analog result and actual monitoring electrification situation, which relatively meet,
Expect that the antistatic protection design of structure and surface potential active control provide important references.
The method specifically includes following steps:
Step 1: establishing space common used material and new material characteristic parameter data library
The electricity of secondary electron emission characteristic parameter, photoelectron emissions characterisitic parameter and material in database including material
Lotus reveals characterisitic parameter etc.；Meanwhile also comprising density, relative dielectric constant, surface resistivity and the bulk conductivity of material, material
The parameters such as thickness.
Wherein, the secondary electron of material and photoelectronic emission characteristics and the charge leakage characteristic of material can pass through examination
Test examination obtains, and can be by being further ensured that the accuracys of data with external comparing.
Step 2: the bi-Maxwellian distribution of magnetic storm plasma is fitted
Bi-Maxwellian distribution fitting is carried out to the most harsh charging environmental observation data of geo-stationary orbit, obtains most harsh environment
Under magnetic storm plasma distribution；In order to preferably reflect plasma distribution that space monitoring arrives, present invention difference
It is fitted the distribution of magnetic storm plasma using the bi-Maxwellian distribution of electronics and ion, i.e., is in thermal equilibrium state by two kinds
Under Maxwell distribution be overlapped.The distribution is distributed closer to actual measurement plasma under geostationary orbit most rigor condition
Spectrum, it is more identical with Bimodal Spectra structure.As shown in Figure 2.
Double Maxwells of electronics and ion energy distribution in the environment are superimposed fitting are as follows:
Wherein, f is energy；Subscript i and e respectively indicate electronics and ion；M is the matter of charged particle (electronics or ion)
Amount, n are the density of charged particle, and subscript 1,2 respectively indicates the 1st and the 2nd peak value of double Maxwell's curves, and kT is band electrochondria
The energy of son, v are the speed of charged particle.
Step 3: spacecraft surface representative region material with complex structural modeling
Material structure, material area and the earthing mode of simulating area are waited for for spacecraft surface, construct equivalent model；Its
In, equivalent model includes dielectric-dielectric structure and dielectric-metal structure, and material connection type includes flushing and overlapping two kinds.
Typical surface texture such as multilayer insulation material, OSR second surface mirror, ITO conductive film, parabola antenna, bus
Cable, solar panel and driving mechanism etc. equivalent can charge equivalent model at inequality as shown in Figure 3.Wherein, Fig. 3
It (a) is flushing by two dielectric materials；Fig. 3 (b) is the overlap joint of two dielectric materials；Fig. 3 (c) is taking for two dielectric materials
It connects and dielectric material and metal material flushes；Fig. 3 (d) is flushing for two kinds of circular metal materials and dielectric material.
Step 4: PIC method process simulation
PIC method process simulation, including spacecraft surface representative region material structure mode input, spacecraft surfacing
Database calls in, the injection of simulated domain plasma and grid dividing around spacecraft；
Using the ion bi-Maxwellian distribution and electronics bi-Maxwellian distribution being fitted in step 2, in entire simulation region
The electronics number of each energy section is distributed in the calculating grid that domain is divided, then the equivalent macro particle at certain amount.Inequality
With the spacecraft representative region material structure that electric model uses step 3 to establish, distinguishing feature is by a variety of space medium materials
It is formed with metal material.Simulated domain grid dividing can simplify programmed algorithm using uniform grid division around spacecraft.Its
In, it simulates macro number of particles in each grid in space and is greater than 5, both can guarantee that simulation process was not take up largely.
PIC method includes following basic step: after the position and speed for obtaining ion and electronics, by the charge of their institute's bands
It is assigned on grid node with electric current, acquires the charge density and current density at grid node, then solve Maxwell equation
Electromagnetic field value on mesh point can be obtained in group, then obtains the electromagnetic field at ion and electronics by interpolation, and particle is in Lorentz power
Under the action of move.Pass through loop iteration process self-consistent solution plasma physics problem so.
Step 5: analog result output and analysis
Simulation result, fine multiple material inequality are charged using the labyrinth material inequality that step 4 provides
Charged data will provide important ginseng for the antistatic protection design of spacecraft representative region material structure and surface potential active control
It examines.
Wherein, when carrying out the surface photoelectron emissions characteristic test of material, using solar simulation ultraviolet source (spectrum model
Enclose the deuterium lamp for 115~400nm) it is tested, the light source is closer to illumination condition true in space.
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (4)
1. a kind of geostationary orbit material inequality charges emulation mode, which comprises the steps of:
Step 1, the characteristic parameter data library of the used material in space is established；
Step 2, the plasma distribution shape of the bi-Maxwellian distribution fitting geostationary orbit of electronics and ion is respectively adopted
State；
Step 3, according to spacecraft surface material structure, material area and earthing mode to be emulated, equivalent model is constructed；Its
In, the structure of equivalent model are as follows: dielectric-dielectric structure and/or dielectric-metal structure；The connection type of material in equivalent model
Are as follows: it flushes and/or overlaps；
Step 4, the equivalent model to simulating area that steps for importing 3 constructs in PIC, and assign pair in step 1 database
Answer the characterisitic parameter of material；Electronics bi-Maxwellian distribution and ion the bi-Maxwellian distribution building constructed according to step 2 is imitative
True environment；Then it calculates to obtain using PIC method and charges simulation result to the material inequality of simulating area.
2. geostationary orbit material inequality as described in claim 1 charges emulation mode, which is characterized in that the material
Characterisitic parameter include: the secondary electron emission characteristic parameter of material, the charge leakage of photoelectron emissions characterisitic parameter and material
Characterisitic parameter；And density, relative dielectric constant, surface resistivity, bulk conductivity and the thickness of material.
3. geostationary orbit material inequality as claimed in claim 2 charges emulation mode, which is characterized in that the light of material
Electron emission characteristic parameter is obtained by testing experiment, wherein when test, uses spectral region for the deuterium lamp mould of 115~400nm
Quasi- solar ultraviolet light.
4. geostationary orbit material inequality as described in claim 1 charges emulation mode, which is characterized in that the step
In 4 PIC method, simulates macro number of particles in each grid in space and be greater than 5.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111913083A (en) * | 2020-08-07 | 2020-11-10 | 许昌学院 | Simulation test method for space charge-discharge effect of multilayer thin film material |
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Application publication date: 20190507 |