CN103761359A - Simulated analysis method for suspended potential of low earth orbit satellite - Google Patents
Simulated analysis method for suspended potential of low earth orbit satellite Download PDFInfo
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Abstract
The invention discloses a simulated analysis method for suspended potential of a low earth orbit satellite. The simulated analysis method includes: acquiring environment parameters of a low earth orbit space, state parameters of a solar array and material information of the satellite; building a dynamic simulation model according to the environment parameters, the state parameters and the material information; carrying out number analog computation on the dynamic simulation model to obtain the suspended potential of the satellite model; calculating the suspended potential of the satellite based on the dynamic simulation model through particle simulation number analyzing method. The simulated analysis method for the suspended potential of the low earth orbit satellite is capable of effectively improving the calculation accuracy.
Description
Technical field
The present invention relates to spationautics field, relate in particular to a kind of low orbit satellite floating potential simulating analysis.
Background technology
Solar battery array power-supply system is as one of most important useful load of satellite, because it is exposed in space plasma environment completely, easily be subject to the impact of spatial charging environment and electric current in collection space plasma environment causes satellite structure potential change.The structure potential change of satellite will cause electric discharge event and affect the normal work of load on satellite, as caused, space environment surveys the detection data error of load, causes burning of high pressure sun array etc.In the design of satellites stage, need to carry out for the space environment of its operation the analysis of floating potential, thereby take effective method to control.
Aspect satellite and the interactional analytical calculation of space plasma, two kinds of methods of magnetic fluid and particle simulation have generally been adopted at present.And particle simulation (PIC) numerical analysis method is a kind ofly to take dynamic plasma model and be the powerful numerical computation method on basis, it can carry out analytical calculation to the interaction between satellite and space plasma more accurately.As ESA/TOS-EMA has developed LEO/PEO(Polar Earth Orbit) processing satellite Plasma Interaction and the galvanomagnetic effect software of track, wherein numerical evaluation adopts two-dimentional PIC method.PicUp3D/Spis satellite and Plasma Interaction simulation softward by European IRF-K, CNRS-UVSQ/CETP and the development of ESA/TOS-EMA joint development, all adopted the PIC method that precision is higher.But, for satellite floating potential, analyze, the methods of approximate analysis that adopt are carried out analytical calculation more at present, and the method for parsing is calculated lower aspect precision.And scientific exploration load is often very high for the accuracy requirement of floating potential.Therefore setting up a kind of high-precision floating potential computing method has great importance.
Summary of the invention
Provide hereinafter about brief overview of the present invention, to the basic comprehension about some aspect of the present invention is provided.Should be appreciated that this general introduction is not about exhaustive general introduction of the present invention.It is not that intention is determined key of the present invention or pith, and nor is it intended to limit the scope of the present invention.Its object is only that the form of simplifying provides some concept, usings this as the preorder in greater detail of discussing after a while.
The invention provides a kind of low orbit satellite floating potential simulating analysis, comprising:
Obtain environmental parameter, the state parameter of sun battle array and the material information of satellite in low rail space;
According to described environmental parameter, state parameter and material information, set up Dynamic Simulation Model;
Described Dynamic Simulation Model is carried out to numerical simulation calculation to draw the floating potential of dummy satellite in Preset Time.
Track satellite floating potential simulating analysis provided by the invention, take Dynamic Simulation Model as basis, calculates the floating potential of satellite by particle simulation numerical analysis method, can effectively improve the precision of calculating.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present invention or technical scheme of the prior art, to the accompanying drawing of required use in embodiment or description of the Prior Art be briefly described below, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skills, do not paying under the prerequisite of creative work, can also obtain according to these accompanying drawings other accompanying drawing.
Fig. 1 is the process flow diagram of a kind of embodiment of low orbit satellite floating potential simulating analysis provided by the invention.
Fig. 2 is the schematic diagram that in low orbit satellite floating potential simulating analysis provided by the invention, grid cell is divided.
Embodiment
For making object, technical scheme and the advantage of the embodiment of the present invention clearer, below in conjunction with the accompanying drawing in the embodiment of the present invention, technical scheme in the embodiment of the present invention is clearly and completely described, obviously, described embodiment is the present invention's part embodiment, rather than whole embodiment.The element of describing in an accompanying drawing of the present invention or a kind of embodiment and feature can combine with element and feature shown in one or more other accompanying drawing or embodiment.It should be noted that for purposes of clarity, in accompanying drawing and explanation, omitted expression and the description of unrelated to the invention, parts known to persons of ordinary skill in the art and processing.Embodiment based in the present invention, the every other embodiment that those of ordinary skills obtain under the prerequisite of not paying creative work, belongs to the scope of protection of the invention.
With reference to figure 1, the present embodiment provides, and a kind of low orbit satellite floating potential simulating analysis, comprising:
Step S101, obtains environmental parameter, the state parameter of sun battle array and the material information of satellite in low rail space;
Step S102, sets up Dynamic Simulation Model according to described environmental parameter, state parameter and material information;
Step S103, carries out numerical simulation calculation to draw the floating potential of dummy satellite in Preset Time to described Dynamic Simulation Model.
Particularly, the environmental parameter in low rail space comprises: electron density, electron temperature, ion concentration, ion temperature; The state parameter of sun battle array comprises: sun battle array is with respect to interconnected position and the connected mode of operating voltage, sun battle array bare metal on satellite structure ground; The material information of satellite comprises the material information of satellite surface.
Wherein, environmental parameter adopts typical low orbit environmental parameter, and wherein electron temperature is 0.3eV, and electron density is 10
9/ m
3, ion temperature is 01eV, ion concentration is 10
9/ m
3.
Sun battle array comprises into a plurality of solar cells that matrix is arranged, and the surface coverage of solar cell has cover glass, adopts the ITO film of electrostatic prevention coated on cover glass, using the electrostatic prevention film ITO ground connection of satellite and as satellite structurally; Between each solar cell, by exposed metal interconnection, the solar cell of series connection provides operating voltage, then parallel connection provides working current.
Potential difference (PD) between interconnected bare metal that in the present embodiment, the floating potential of calculative satellite is satellite structurally and in sun battle array.
According to the feature of low orbit, plasma and satellite interact and adopt PIC(particle model) analyze, according to described space environment parameter, state parameter and material information, set up Dynamic Simulation Model, comprising:
According to described electron density, electron temperature, ion concentration, ion temperature, set up corresponding plasma environment model, according to the interconnect location of described operating voltage, bare metal and connected mode, set up sun battle array model, according to the material information of described satellite surface, set up dummy satellite; Described dummy satellite and sun battle array model are in described plasma environment model.
Described Dynamic Simulation Model is carried out to numerical simulation calculation to draw the floating potential in Preset Time of described dummy satellite, comprising:
Preset Time and time step are set;
Calculate the floating potential of the dummy satellite in each time step until reach Preset Time;
The floating potential obtaining in set potential by sun battle array model and dummy satellite between structurally and each time step superposes to obtain the floating potential of described dummy satellite in Preset Time.
Further, the floating potential of the satellite in each time step of described calculating, comprising:
By plasma environment model partition, be a plurality of grid cells;
According to the plasma ambient Changing Pattern of each grid cell, determine quantity and the speed of the charged particle in grid cell in a time step, and according to the quantity of described charged particle and speed, determine the electric current of each grid cell;
According to the floating potential of dummy satellite in time step of Current calculation of each grid cell.
In described plasma ambient model, comprise plasma region, dummy satellite and sun battle array model, during grid division unit, need article on plasma body region, dummy satellite and sun battle array model to divide.
Particularly, for the division in plasma region, be the Debye length according to plasma, be generally 0.7 λ
d, for the grid of sun battle array model, divide, need to be according to concrete details, grid needs meticulousr, may be than 0.7 λ
dless, for example in the sun battle array solar cell between gap conventionally only have 1mm, need grid to be divided into 1mm.
In actual conditions, can to grid, divide according to concrete design feature.
Further, according to the plasma ambient Changing Pattern of each grid cell, determine quantity and the speed of the charged particle in grid cell in a time step, and according to the quantity of described charged particle and speed, determine the electric current of each grid cell, comprising:
Determine initial position and the initial velocity of described charged particle;
By Poisson equation and Maxwell equation group, draw the Electric and magnetic fields of each grid cell, and utilize Lorentz force formula and newtonian motion formula to calculate respectively Lorentz force and the moving situation of charged particle in each grid cell;
According to Lorentz force and the moving situation of the charged particle in described each grid cell, obtain speed and the quantity of charged particle;
According to the speed of the charged particle in grid cell and quantity, calculate the electric current of described grid cell in a time step.
Above-mentioned steps is in a time step, so the initial position of charged particle and initial velocity are position and the speed of upper time step charged particle while finishing.When starting most, when charged particle is initial, in the space of plasma environment model, be uniformly distributed, its density meets the density that environmental parameter provides; Electron temperature and ion temperature are the energy of charged particle, meeting Maxwell distributes, during simulation, according to the electron temperature in environment, ion temperature, charged particle in model is carried out to Maxwell's initialization that distributes, with reference to figure 2, conventional method for being decomposed into the speed of charged particle the component velocity of X, Y, tri-directions of Z in virtual space, and component velocity meets Maxwell and distributes.
By model partition, it is a limited number of grid cell, the quantity of electric charge of the electronics in space and ion is assigned in each grid cell by area weight, as shown in Figure 2, to obtain the electric density of each grid cell, take electric density as basis, by Poisson equation and Maxwell equation batch total, calculate the Electric and magnetic fields of grid cell, take this Electric and magnetic fields as basis, utilize Lorentz force formula and newtonian motion formula, calculate the stressed and motion of charged particle in each grid cell, and then obtaining speed and the quantity of charged particle.
Maxwell equation group is one group of partial differential equation of describing relation between electric field, magnetic field, electric density, current density, take electric density as basis, the method of calculating Electric and magnetic fields by Maxwell equation batch total is known to the skilled person, and at this, is not repeating.
After obtaining the speed and quantity of the charged particle in grid cell, according to the computing formula of strength of current, calculate the electric current of grid cell.
Above-mentioned steps is the process in a Preset Time step-length, position and the speed of the charged particle in an above Preset Time step-length are initial, carry out the calculating in next time step, carry out cycle calculations, thereby obtain quantity and the speed of the charged particle in the time of wanting.
Further, the floating potential according to dummy satellite in time step of Current calculation of each grid cell, comprising:
By the electric weight in each grid cell of the Current calculation in each grid cell;
According to described electric weight, calculate the current potential in described each grid cell;
Each grid cell is calculated to the current potential obtaining and superpose, to obtain the floating potential value of described dummy satellite in a time step.
Electric weight in grid cell adopts following formula to calculate:
Qi=IT；
Wherein Q is electric weight, and I is electric current, and T is Preset Time step-length.
The current potential of each grid cell adopts following formula to calculate:
Vi=Qi/Ci；
The current potential that wherein Vi is each grid cell, Qi is electric weight, Ci is each grid cell ground capacitance.
Obtaining the floating potential value of described dummy satellite in Preset Time step-length adopts following formula to calculate:
V=ΣQ
i/C；
Wherein V is the floating potential value of dummy satellite in Preset Time, and C is the ground capacitance of dummy satellite total.
After obtaining the floating potential value in time step of described satellite, the floating potential obtaining in each time step is superposeed to obtain the floating potential of described satellite in Preset Time.
Owing to there is a set potential V0 structurally in sun battle array model and dummy satellite, when calculating all the time by satellite structure and sun battle array between be set to set potential V0, so floating potential Vs=V0+V, Vs is as the initial value of next Preset Time step-length.
Low orbit satellite floating potential simulating analysis provided by the invention, by PIC particle simulation method, can effectively improve the precision that satellite floating potential calculates.
In the various embodiments described above of the present invention, the sequence number of embodiment is only convenient to describe, and does not represent the quality of embodiment.Description to each embodiment all emphasizes particularly on different fields, and there is no the part of detailed description in certain embodiment, can be referring to the associated description of other embodiment.
One of ordinary skill in the art will appreciate that: all or part of step that realizes said method embodiment can complete by the relevant hardware of programmed instruction, aforesaid program can be stored in a computer read/write memory medium, this program, when carrying out, is carried out the step that comprises said method embodiment; And aforesaid storage medium comprises: various media that can be program code stored such as ROM (read-only memory) (Read-Only Memory is called for short ROM), random access memory (Random Access Memory is called for short RAM), magnetic disc or CDs.
In the embodiment such as apparatus and method of the present invention, obviously, each parts or each step reconfigure after can decomposing, combine and/or decomposing.These decomposition and/or reconfigure and should be considered as equivalents of the present invention.Simultaneously, in the above in the description of the specific embodiment of the invention, the feature of describing and/or illustrating for a kind of embodiment can be used in same or similar mode in one or more other embodiment, combined with the feature in other embodiment, or substitute the feature in other embodiment.
Should emphasize, term " comprises/comprises " existence that refers to feature, key element, step or assembly while using herein, but does not get rid of the existence of one or more further feature, key element, step or assembly or add.
Finally it should be noted that: although described above the present invention and advantage thereof in detail, be to be understood that in the situation that do not exceed the spirit and scope of the present invention that limited by appended claim and can carry out various changes, alternative and conversion.And scope of the present invention is not limited only to the specific embodiment of the described process of instructions, equipment, means, method and step.One of ordinary skilled in the art will readily appreciate that from disclosure of the present invention, can use carry out with the essentially identical function of corresponding embodiment described herein or obtain process, equipment, means, method or step result essentially identical with it, that existing and will be developed future according to the present invention.Therefore, appended claim is intended to comprise such process, equipment, means, method or step in their scope.
Claims (9)
1. the anti-true analytical approach of low orbit satellite floating potential, is characterized in that, comprising:
Obtain environmental parameter, the state parameter of sun battle array and the material information of satellite in low rail space;
According to described environmental parameter, state parameter and material information, set up Dynamic Simulation Model;
Described Dynamic Simulation Model is carried out to numerical simulation calculation to draw the floating potential of dummy satellite in Preset Time.
2. low orbit satellite floating potential simulating analysis according to claim 1, is characterized in that, described environmental parameter comprises: electron density, electron temperature, ion concentration, ion temperature;
The state parameter of described sun battle array comprises:
Sun battle array is with respect to the set potential between satellite structure ground, interconnected position and the connected mode of sun battle array bare metal;
The material information of described satellite comprises the material information of satellite surface.
3. low orbit satellite floating potential simulating analysis according to claim 2, is characterized in that, according to described space environment parameter, state parameter and material information, sets up Dynamic Simulation Model, comprising:
According to described electron density, electron temperature, ion concentration, ion temperature, set up corresponding plasma environment model, according to the interconnect location of described operating voltage, bare metal and connected mode, set up sun battle array model, according to the material information of described satellite surface, set up dummy satellite; Described dummy satellite and sun battle array model are in described plasma environment model.
4. low orbit satellite floating potential simulating analysis according to claim 3, is characterized in that, described Dynamic Simulation Model is carried out to numerical simulation calculation to draw the floating potential in Preset Time of described dummy satellite, comprising:
Preset Time and time step are set;
Calculate the floating potential of the dummy satellite in each time step until reach Preset Time;
The floating potential obtaining in set potential by sun battle array model and dummy satellite between structurally and each time step superposes, to obtain the floating potential of described dummy satellite in Preset Time.
5. low orbit satellite floating potential simulating analysis according to claim 4, is characterized in that, the floating potential of the dummy satellite in each time step of described calculating, comprising:
By plasma environment model partition, be a plurality of grid cells;
According to the plasma ambient Changing Pattern of each grid cell, determine quantity and the speed of the charged particle in grid cell in a time step, and according to the quantity of described charged particle and speed, determine the electric current of each grid cell;
According to the floating potential of dummy satellite in time step of Current calculation of each grid cell.
6. low orbit satellite floating potential simulating analysis according to claim 5, is characterized in that, according to the Debye length of plasma, described plasma environment model is decomposed into a plurality of grid cells.
7. low orbit satellite floating potential simulating analysis according to claim 5, it is characterized in that, according to the plasma ambient Changing Pattern of each grid cell, determine quantity and the speed of the charged particle in grid cell in a time step, and according to the quantity of described charged particle and speed, determine and comprise the electric current of each grid cell:
Determine initial position and the initial velocity of described charged particle;
By Poisson equation and Maxwell equation group, draw the Electric and magnetic fields of each grid cell, and utilize Lorentz force formula and newtonian motion formula, calculate respectively Lorentz force and the moving situation of charged particle in each grid cell;
According to Lorentz force and the moving situation of the charged particle in described each grid cell, obtain speed and the quantity of charged particle;
According to the speed of the charged particle in grid cell and quantity, calculate the electric current of described grid cell in a time step.
8. low orbit satellite floating potential simulating analysis according to claim 7, is characterized in that, the floating potential according to dummy satellite in time step of Current calculation of each grid cell, comprising:
By the electric weight in each grid cell of the Current calculation in each grid cell;
According to described electric weight, calculate the current potential in described each grid cell;
Each grid cell is calculated to the current potential obtaining and superpose, to obtain the floating potential of described dummy satellite in a time step.
9. low orbit satellite floating potential simulating analysis according to claim 7, is characterized in that,
The initial position of described charged particle and initial velocity, be respectively position and the speed of time step charged particle while finishing.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104239623A (en) * | 2014-09-05 | 2014-12-24 | 兰州空间技术物理研究所 | Method for obtaining satellite surface potential based on multi-time-scale particle push |
| CN104281740A (en) * | 2014-09-05 | 2015-01-14 | 兰州空间技术物理研究所 | Method for acquiring satellite surface potential on basis of non-uniform grid division |
| CN104614583A (en) * | 2015-02-11 | 2015-05-13 | 中国科学院空间科学与应用研究中心 | Suspension potential monitoring system |
| CN107679274A (en) * | 2017-08-30 | 2018-02-09 | 西安空间无线电技术研究所 | A kind of spacecraft discharge and recharge comprehensive analysis method |
| CN115510729A (en) * | 2022-09-27 | 2022-12-23 | 兰州空间技术物理研究所 | Acceleration method for simulating and calculating satellite surface potential by adopting PIC (peripheral interface controller) method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101276378A (en) * | 2007-03-26 | 2008-10-01 | 中国航天科技集团公司第五研究院第五一○研究所 | Method of satellite sun array surface charging numerical simulation prediction |
| CN102117345A (en) * | 2009-12-31 | 2011-07-06 | 北京卫星环境工程研究所 | Method for surface charging analysis of satellite |
| CN103226638A (en) * | 2013-04-24 | 2013-07-31 | 兰州空间技术物理研究所 | Estimation method for numerical simulation of distribution character of plasma generated by electric propulsor |
-
2013
- 2013-12-24 CN CN201310722549.7A patent/CN103761359A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101276378A (en) * | 2007-03-26 | 2008-10-01 | 中国航天科技集团公司第五研究院第五一○研究所 | Method of satellite sun array surface charging numerical simulation prediction |
| CN102117345A (en) * | 2009-12-31 | 2011-07-06 | 北京卫星环境工程研究所 | Method for surface charging analysis of satellite |
| CN103226638A (en) * | 2013-04-24 | 2013-07-31 | 兰州空间技术物理研究所 | Estimation method for numerical simulation of distribution character of plasma generated by electric propulsor |
Non-Patent Citations (2)
| Title |
|---|
| 师立勤: "低轨道航空器辐射环境和表面充电效应研究", 《中国博士学位论文全文数据库 工程科技Ⅱ辑》 * |
| 杨集等: "低轨道卫星表面充电模拟", 《微纳电子技术》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104239623A (en) * | 2014-09-05 | 2014-12-24 | 兰州空间技术物理研究所 | Method for obtaining satellite surface potential based on multi-time-scale particle push |
| CN104281740A (en) * | 2014-09-05 | 2015-01-14 | 兰州空间技术物理研究所 | Method for acquiring satellite surface potential on basis of non-uniform grid division |
| CN104614583A (en) * | 2015-02-11 | 2015-05-13 | 中国科学院空间科学与应用研究中心 | Suspension potential monitoring system |
| CN107679274A (en) * | 2017-08-30 | 2018-02-09 | 西安空间无线电技术研究所 | A kind of spacecraft discharge and recharge comprehensive analysis method |
| CN107679274B (en) * | 2017-08-30 | 2021-06-11 | 西安空间无线电技术研究所 | Spacecraft charging and discharging comprehensive analysis method |
| CN115510729A (en) * | 2022-09-27 | 2022-12-23 | 兰州空间技术物理研究所 | Acceleration method for simulating and calculating satellite surface potential by adopting PIC (peripheral interface controller) method |
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Inventor after: Li Detian Inventor after: Tang Daotan Inventor after: Yang Shengsheng Inventor after: Qin Xiaogang Inventor after: Liu Qing Inventor after: Wang Jun Inventor before: Tang Daotan Inventor before: Yang Shengsheng Inventor before: Li Detian Inventor before: Qin Xiaogang Inventor before: Liu Qing Inventor before: Wang Jun |
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Application publication date: 20140430 |