CN102941930A - Surface electrification simulation test system and method for satellite tail regions - Google Patents
Surface electrification simulation test system and method for satellite tail regions Download PDFInfo
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- CN102941930A CN102941930A CN2012104848415A CN201210484841A CN102941930A CN 102941930 A CN102941930 A CN 102941930A CN 2012104848415 A CN2012104848415 A CN 2012104848415A CN 201210484841 A CN201210484841 A CN 201210484841A CN 102941930 A CN102941930 A CN 102941930A
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Abstract
The invention relates to a surface electrification simulation test system and a method for satellite tail regions, and belongs to the test field. The system comprises a medium and low energy electronic gun, a three-dimensional transmission mechanism, a surface potentiometer, lamp filaments, a plasma diagnostic system, a Kaufmann ion source, a vacuum-pumping system, a vacuum chamber and a personal computer (PC). The method comprises that a satellite component is placed in the vacuum chamber to vacuumize the vacuum chamber; the Kaufmann ion source and the medium and low energy electronic gun are opened, and grid accelerating voltages, ion beams and electronic beams of the Kaufmann ion source and beam density and energy of the medium and low energy electronic gun are set; the plasma diagnostic system is used for diagnosing produced plasma environments; and the three-dimensional transmission mechanism drives the surface potentiometer to measure surface charging potentials in the satellite tail region. By means of the surface electrification simulation test system and the method for satellite tail regions, plasma environment simulation can be performed on satellite tail region environments, and the charging simulation test of the satellite component tail region can be performed.
Description
Technical field
The present invention relates to a kind of satellite tail region surface charging simulation experiment system and method, particularly for the system and method for simulation Low Earth Orbit (LEO) plasma environment and aurora electronic environment Satellite tail region surface charging effect test, belong to field tests.
Background technology
When satellite transit is in low temperature high-density plasma environment, form one obvious " flight path " in its tail region, this is a unequal electronics and ion depletion region, since satellite orbit speed greater than the hot speed of ion less than Electron Heat speed, therefore thereby electronics can enter relatively easily this zone and form a negative potential potential barrier, Here it is so-called " tail region charged effect ", and its obvious effect to satellite is that the tail region dielectric surface will charge to a higher negative potential.Especially, when polar region aurora electronic injection was arranged, the tail region current potential of satellite can reach thousands of volts.Usually, the surface charging that forms because of " tail region effect " of satellite is to affect particularly one of the major issue of polar-orbiting satellite safe operation of low orbit.
Document " Wakes and differential charging of large bodies in low earth orbit " studies show that, the substantially proportional relations such as tail region charging potential and satellite velocities (Mach speed), satellite size.The size of the low orbit investigation satellite of present stage design has reached tens of rice, and simultaneously, polar region aurora sedimentation electronic beam current reaches as high as 100 times of geosynchronous orbit, and flux is about 30nA/cm
2, will produce at Large-scale satellite and parts afterbody thereof the current potential of thousands of volts, and because charging capacitor is large, and discharge energy is also large, the Induced by Space Electrostatic Discharges of generation with serious threat satellite electron system in rail safety.Therefore, be necessary to develop a kind of apparatus and method that are fit to carry out satellite tail region band electric analogy testing.
But, in satellite tail region charged effect analogue test, also there is following main difficulty at present:
(1) ground is difficult to real simulation tail region plasma band electrical environment;
(2) ground is difficult to carry out the charged analogue test in full-size(d) satellite tail region.
Therefore, setting up the charged simulation experiment method in a kind of actv. tail region studies significant to carrying out the low-orbit satellite surface charging.
Summary of the invention
For achieving the above object, technical scheme of the present invention is as follows.
A kind of satellite tail region surface charging simulation experiment system, described system comprises: middle low-energy electron rifle, three dimensional transmission mechanism, surface potential meter, filament, plasma diagnostics system, Kaufman ion source, pumped vacuum system, vacuum chamber, PC.
Wherein, at internal vacuum chamber, the filament symmetry is installed on the upper lower wall surface of vacuum chamber; Satellite component vertically is suspended on the center of vacuum chamber by metal filament; Kaufman ion source is installed in respectively on two relative sidewalls of vacuum chamber with middle low-energy electron rifle, and wherein Kaufman ion source is positioned at the satellite component left side, and middle low-energy electron rifle is positioned at the satellite component right side; Being centered close on the straight line of Kaufman ion source, satellite component, middle low-energy electron rifle; Plasma diagnostics system and three dimensional transmission mechanism are positioned at internal vacuum chamber, at three dimensional transmission mechanism the surface potential meter are installed;
Outside at vacuum chamber, PC is connected with the plasma diagnostics system; Pumped vacuum system is connected with vacuum chamber;
Preferred described plasma diagnostics system is the Langmuir probe.
Preferred described filament is tungsten filament.
Distance between preferred described satellite component and the Kaufman ion source is 30 ~ 40cm.
A kind of satellite tail region surface charging simulation experiment method, described method step is as follows:
Step 3, drive the surface potential meter by three dimensional transmission mechanism and move on the satellite component right side, measure the surface charging current potential in the satellite component tail region;
Behind the end of test, shutdown system, size or the Kaufman ion source grid accelerated voltage of transposing satellite component structure, repeating step one～three obtains the scantling of structure of satellite component and the relation of satellite motion speed and tail region charging potential.
Preferably in step 2, Kaufman ion source grid accelerated voltage is that 100V, ion beam current are that 32mA, electronic beam current are 35mA; The energy of middle low-energy electron rifle is 1.0 ~ 100keV, and beam current density is 1 ~ 10nA/cm
2The density of the plasma in the vacuum chamber is 10
9/ m
3～10
12/ m
3
Beneficial effect
1. the invention provides a kind of satellite tail region surface charging simulation experiment system, described system can carry out the environment plasma environment simulation of satellite tail region, can carry out satellite component tail region charging analogue test.
2. the invention provides the test method of described satellite tail region surface charging simulation experiment system, can carry out the environment plasma environment simulation of satellite tail region, be specially: utilize Kaufman ion source to produce high density low-power plasma body, simultaneously, relative motion effect for analog satellite, ion accelerating grid electrode at Kaufman ion source applies accelerated voltage to ion current, produced the plasma flow of directed flow, therefore, the afterbody at the object of directional plasma stream can produce the tail region effect.
3. described method can be carried out the simulation of aurora electronic environment, is specially on the opposite of Kaufman ion source and places a middle low-energy electron rifle, and its electron energy is 1.0 ~ 100keV, and beam current density is 1 ~ 10nA/cm
2
Description of drawings
Fig. 1 is satellite of the present invention tail region surface charging simulation experiment system structural representation.
Among the figure: 1 is satellite component, and 2 is middle low-energy electron rifle, and 3 is three dimensional transmission mechanism, and 4 is the surface potential meter, and 5 is filament, and 6 is the plasma diagnostics system, and 7 is Kaufman ion source, and 8 is pumped vacuum system, and 9 is vacuum chamber, and 10 is PC.
The specific embodiment
Below the invention will be further described.
Embodiment
A kind of satellite tail region surface charging simulation experiment system as shown in Figure 1, described system comprises: middle low-energy electron rifle 2, three dimensional transmission mechanism 3, surface potential meter 4, filament 5, plasma diagnostics system 6, Kaufman ion source 7, pumped vacuum system 8, vacuum chamber 9, PC 10.
Wherein, in vacuum chamber 9 inside, filament 5 symmetries are installed on the upper lower wall surface of vacuum chamber; Satellite component 1 vertically is suspended on the center of vacuum chamber 9 by metal filament; Kaufman ion source 7 is installed in respectively on 9 two relative sidewalls of vacuum chamber with middle low-energy electron rifle 2, and wherein Kaufman ion source 7 is positioned at satellite component 1 left side, and middle low-energy electron rifle 2 is positioned at satellite component 1 right side; Being centered close on the straight line of Kaufman ion source 7, satellite component 1, middle low-energy electron rifle 2; Plasma diagnostics system 6 and three dimensional transmission mechanism 3 are positioned at vacuum chamber 9 inside, at three dimensional transmission mechanism 3 surface potential meter 4 are installed;
Have through hole at vacuum chamber 9 walls, the PC 10 of vacuum chamber 9 outsides is connected with plasma diagnostics system 6 by wire; Pumped vacuum system 8 is connected with vacuum chamber 9;
Wherein, described plasma diagnostics system 6 is the Langmuir probe.Described filament 5 is tungsten filament.Distance between described satellite component 1 and the Kaufman ion source 7 is 30cm.The electron energy of middle low-energy electron rifle is 1.0 ~ 100keV, and beam current density is 1 ~ 10nA/cm
2
A kind of satellite tail region surface charging simulation experiment method, described method step is as follows:
Step 3, drive surface potential meters 4 by three dimensional transmission mechanism 3 and move on satellite component 1 right side, measure the surface charging current potential in satellite component 1 tail region;
Behind the end of test, shutdown system, regulating Kaufman ion source 7 grid accelerated voltages is 120V, repeating step one～three, the relation of acquisition satellite motion speed and tail region charging potential.Then change the size of satellite component 1, repeating step one～three obtains the size of satellite component 1 and the relation of tail region charging potential.
In sum, more than be preferred embodiment of the present invention only, be not for limiting protection scope of the present invention.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (6)
1. satellite tail region surface charging simulation experiment system, it is characterized in that: described system comprises: middle low-energy electron rifle (2), three dimensional transmission mechanism (3), surface potential meter (4), filament (5), plasma diagnostics system (6), Kaufman ion source (7), pumped vacuum system (8), vacuum chamber (9), PC (10);
Wherein, in vacuum chamber (9) inside, filament (5) symmetry is installed on the upper lower wall surface of vacuum chamber; Satellite component (1) vertically is suspended on the center of vacuum chamber (9) by metal filament; Kaufman ion source (7) is installed in respectively on (9) two relative sidewalls of vacuum chamber with middle low-energy electron rifle (2), and wherein Kaufman ion source (7) is positioned at satellite component (1) left side, and middle low-energy electron rifle (2) is positioned at satellite component (1) right side; Being centered close on the straight line of Kaufman ion source (7), satellite component (1), middle low-energy electron rifle (2); Plasma diagnostics system (6) and three dimensional transmission mechanism (3) are positioned at vacuum chamber (9) inside, at three dimensional transmission mechanism (3) surface potential meter (4) are installed;
In vacuum chamber (9) outside, PC (10) is connected with plasma diagnostics system (6); Pumped vacuum system (8) is connected with vacuum chamber (9).
2. a kind of satellite according to claim 1 tail region surface charging simulation experiment system, it is characterized in that: described plasma diagnostics system (6) is the Langmuir probe.
3. a kind of satellite according to claim 1 tail region surface charging simulation experiment system, it is characterized in that: described filament (5) is tungsten filament.
4. a kind of satellite according to claim 1 tail region surface charging simulation experiment system, it is characterized in that: the distance between described satellite component (1) and the Kaufman ion source (7) is 30 ~ 40cm.
5. satellite tail region surface charging simulation experiment method, it is characterized in that: described method is being carried out such as each described system of claim 1 to 4, and described method step is as follows:
Step 1, in vacuum chamber (9), put into satellite component (1), open pumped vacuum system (8) vacuum chamber (9) is vacuumized, make degree of vacuum in the vacuum chamber (9)≤10
-3Pa;
Step 2, open Kaufman plasma source (7) and middle low-energy electron rifle (2), set grid accelerated voltage, ion beam current, the electronic beam current of Kaufman ion source (7), and beam current density and the energy of middle low-energy electron rifle (2); Utilize plasma diagnostics system (6) that the plasma environment that produces is diagnosed;
Step 3, drive surface potential meter (4) by three dimensional transmission mechanism (3) and move on satellite component (1) right side, measure the surface charging current potential in satellite component (1) tail region;
Behind the end of test, shutdown system, size or Kaufman ion source (7) the grid accelerated voltage of transposing satellite component (1), repeating step one～three obtains the size of satellite component (1) and the relation of satellite motion speed and tail region charging potential.
6. a kind of satellite according to claim 5 tail region surface charging simulation experiment method, it is characterized in that: in step 2, Kaufman ion source (7) grid accelerated voltage is that 100V, ion beam current are that 32mA, electronic beam current are 35mA; The energy of middle low-energy electron rifle (2) is 1.0 ~ 100keV, and beam current density is 1 ~ 10nA/cm
2The density of the plasma in the vacuum chamber (9) is 10
9/ m
3~ 10
12/ m
3
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103245858A (en) * | 2013-04-24 | 2013-08-14 | 兰州空间技术物理研究所 | Device and method for ground-based simulation experimentation of charging effect of high altitude satellite material |
| CN103698589A (en) * | 2013-11-28 | 2014-04-02 | 兰州空间技术物理研究所 | Satellite surface potential monitoring device |
| CN104239620A (en) * | 2014-09-03 | 2014-12-24 | 兰州空间技术物理研究所 | Charging effect simulation method at tail region of spacecraft |
| CN104260906A (en) * | 2014-09-03 | 2015-01-07 | 兰州空间技术物理研究所 | Spacecraft tail area ion atmosphere ground-based simulation method |
| CN104340381A (en) * | 2014-10-24 | 2015-02-11 | 兰州空间技术物理研究所 | Experiment system for space lower earth orbit plasma environment simulation |
| CN105000202A (en) * | 2015-07-16 | 2015-10-28 | 兰州空间技术物理研究所 | Vacuum pumping system of test equipment of ion thrusters |
| CN105785153A (en) * | 2014-12-19 | 2016-07-20 | 中国科学院空间科学与应用研究中心 | Simulation device of satellite surface charge and discharge phenomena |
| CN110006776A (en) * | 2019-04-12 | 2019-07-12 | 哈尔滨工业大学 | A kind of evaluation method for the anti-sputtering performance of Hall electric propulsion device channel material |
| CN112146905A (en) * | 2020-09-04 | 2020-12-29 | 兰州空间技术物理研究所 | Space high-speed charged particle simulation device and simulation method |
| CN114560109A (en) * | 2022-03-17 | 2022-05-31 | 中国科学院国家空间科学中心 | Space proton deep charging ground simulation device and method |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103245858A (en) * | 2013-04-24 | 2013-08-14 | 兰州空间技术物理研究所 | Device and method for ground-based simulation experimentation of charging effect of high altitude satellite material |
| CN103698589A (en) * | 2013-11-28 | 2014-04-02 | 兰州空间技术物理研究所 | Satellite surface potential monitoring device |
| CN104239620B (en) * | 2014-09-03 | 2017-04-05 | 兰州空间技术物理研究所 | A kind of spacecraft tail region charged effect emulation mode |
| CN104260906A (en) * | 2014-09-03 | 2015-01-07 | 兰州空间技术物理研究所 | Spacecraft tail area ion atmosphere ground-based simulation method |
| CN104260906B (en) * | 2014-09-03 | 2016-05-04 | 兰州空间技术物理研究所 | A kind of spacecraft tail region ionic environment ground simulation method |
| CN104239620A (en) * | 2014-09-03 | 2014-12-24 | 兰州空间技术物理研究所 | Charging effect simulation method at tail region of spacecraft |
| CN104340381A (en) * | 2014-10-24 | 2015-02-11 | 兰州空间技术物理研究所 | Experiment system for space lower earth orbit plasma environment simulation |
| CN104340381B (en) * | 2014-10-24 | 2016-04-06 | 兰州空间技术物理研究所 | A kind of space Low Earth Orbit plasma environment experimental system for simulating |
| CN105785153A (en) * | 2014-12-19 | 2016-07-20 | 中国科学院空间科学与应用研究中心 | Simulation device of satellite surface charge and discharge phenomena |
| CN105785153B (en) * | 2014-12-19 | 2019-02-26 | 中国科学院空间科学与应用研究中心 | A kind of simulator of satellite surface charge and discharge phenomena |
| CN105000202A (en) * | 2015-07-16 | 2015-10-28 | 兰州空间技术物理研究所 | Vacuum pumping system of test equipment of ion thrusters |
| CN110006776A (en) * | 2019-04-12 | 2019-07-12 | 哈尔滨工业大学 | A kind of evaluation method for the anti-sputtering performance of Hall electric propulsion device channel material |
| CN110006776B (en) * | 2019-04-12 | 2021-08-24 | 哈尔滨工业大学 | Method for evaluating anti-sputtering performance of Hall electric propeller channel material |
| CN112146905A (en) * | 2020-09-04 | 2020-12-29 | 兰州空间技术物理研究所 | Space high-speed charged particle simulation device and simulation method |
| CN114560109A (en) * | 2022-03-17 | 2022-05-31 | 中国科学院国家空间科学中心 | Space proton deep charging ground simulation device and method |
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Application publication date: 20130227 |