CN103245858A - Device and method for ground-based simulation experimentation of charging effect of high altitude satellite material - Google Patents
Device and method for ground-based simulation experimentation of charging effect of high altitude satellite material Download PDFInfo
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- CN103245858A CN103245858A CN2013101453517A CN201310145351A CN103245858A CN 103245858 A CN103245858 A CN 103245858A CN 2013101453517 A CN2013101453517 A CN 2013101453517A CN 201310145351 A CN201310145351 A CN 201310145351A CN 103245858 A CN103245858 A CN 103245858A
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Abstract
The invention relates to a device and method for ground-based simulation experimentation of charging effect of a high altitude satellite material and belongs to the field of measurement. The device comprises a shielded chamber, a vacuum chamber, an electron accelerator, a shielding case, a plasma source, a sample table, an insulation washer, a vacuum pumping system, a three-dimensional transmission mechanism, an oscilloscope, an impulse current probe, a non-contact potentiometer, a camera and an adjustable power source. The method comprises the following steps: starting the vacuum pumping system to vacuumize the vacuum chamber; starting the plasma source to simulate a GEO track plasma charging environment; starting the electron accelerator to simulate a GEO track high-energy electron charging environment; and utilizing the impulse current probe and the oscilloscope to monitor the transient discharge impulse of a material sample, utilizing the non-contact potentiometer to monitor the surface electric potential of the material specimen sample, and utilizing the camera to record the secondary discharge phenomenon. Through the adoption of the electron accelerator and the plasma source, the charging environment of a high track in a magnetic substorm can be simulated well; and the device and the method are suitable for measuring the charging effect of various satellite materials.
Description
Technical field
The present invention relates to a kind of high rail star with material charged effect ground simulation test device and method, belong to fields of measurement.
Background technology
The spatial charging environment of GEO is made up of two parts.At first be ground magnetic substorm plasma, when solar flare took place, solar wind and magnetic field of the earth interaction can produce ground magnetic substorm phenomenon, and this moment, at 1～50keV, density was 10 in geostationary orbit meeting produce power
5～10
6m
-3Big flux plasma in the scope can make GEO satellite surface charge to more than ten thousand volts; Secondly, GEO is in the edge of extraterrestrial radiation band, and the high energy electron energy is at 0.1～10MeV, and flux is 10
7E/cm
2About the scope of s, big flux high energy electron makes the GEO satellite produce interior charged effect easily.When the accumulation rate of electric charge in the material is higher than the rate of releasing of electric charge, the electric field of these charge generation constantly strengthens, when surpassing the breakdown threshold of material, will cause the puncture of material, cause the static discharge of material, the electromagnetic pulse of generation can cause satellite damage in various degree, causes the data upset, disturb even destroy the operate as normal of electronic system, can cause spacecraft complete failure when serious.Therefore, surface charging and the interior charged discharge that produces are to communicate by letter and earth high orbit satellite such as meteorology produces cause faults.
Along with the continuous development of Chinese Space application technology, the quantity of the Navsat of GEO track, telstar, weather satellite etc. is more and more, is imperative to GEO track star with the research of material charged effect.At present, China is deep not enough with the understanding of material charged effect to star, lacks effective means of defence and design means, can't guarantee fully the GEO orbiter in rail stable operation.Therefore, need the research of carrying out High Earth Orbit star usefulness material charged effect ground simulation test badly.
Summary of the invention
The technical matters that the present invention solves is: at the spatial charging environment that has plasma and high energy electron in the High Earth Orbit simultaneously, a kind of high rail star material charged effect ground simulation test device and method are provided, utilize electron accelerator and plasma source to simulate high energy electron and the plasma of high rail, carry out star material charged effect ground simulation test.
Technical scheme of the present invention is as follows:
A kind of high rail star material charged effect ground simulation test device, described device comprises screened room, vacuum chamber, electron accelerator, shielding case, plasma source, sample platform, insulating mat, vacuum-pumping system, three-dimensional gear train, oscillograph, pulse current probe, noncontact pot, camera, and regulated power supply.
At internal vacuum chamber, electron accelerator and camera are installed in the vacuum chamber top; Plasma source is installed in the vacuum chamber sidewall, is provided with shielding case in the periphery of plasma source, prevents that electronics from damaging plasma source;
The sample platform is installed on the vacuum chamber bottom surface, on the sample platform insulating mat is set; Material sample is placed on the insulating mat upper surface, is provided with metal back electrode at the material sample lower surface; Described material sample is connected with vacuum chamber regulated power supply outward.Three-dimensional gear train is positioned at vacuum chamber, and three-dimensional gear train is provided with contactless surface potential meter probe; Outside vacuum chamber, vacuum-pumping system is connected with vacuum chamber;
Oscillograph, pulse current probe, noncontact pot are positioned at screened room, noncontact pot one end ground connection, the other end with pass screened room and vacuum chamber and be connected with contactless surface potential meter probe; The lead that connects the material sample metal back electrode passes behind vacuum chamber and the screened room ground connection in screened room, is provided with the pulse current probe at lead, and described pulse current probe is connected with oscillograph.
Wherein, preferred described metal back electrode is the conducting metal adhesive tape.
A kind of high rail star material charged effect ground simulation experiment method may further comprise the steps:
Step 1, unlatching vacuum-pumping system vacuumize to vacuum chamber;
Step 2, the charged environment of unlatching plasma source simulation GEO track plasma;
Step 3, the charged environment of unlocking electronic accelerator simulation GEO track high energy electron;
Step 4, utilize pulse current probe and oscillograph monitoring material sample discharge transient pulse, utilize the surface potential of contactless pot monitoring material sample, utilize camera record secondary discharge phenomenon.
Wherein, vacuum environment vacuum tightness requires to be lower than 3.0 * 10 in the preferred described step 1
-4Pa.
The plasma temperature scope that preferred described step 2 ionic medium body source produces is that 1～50KeV is adjustable, and density range is 1 * 10
5～1 * 10
6/ m
3Adjustable.
It is adjustable in 0.8～2.3MeV that electron accelerator provides the energy range of high energy electron in the preferred described step 3, and the beam current density scope is at 1～25nA/cm
2Interior adjustable.
Adopt the pulse of CT-2 pulse current probe monitoring material sample spark in the preferred described step 4, adopt the contactless pot monitoring of Trek341A material sample surface potential.
Preferred described material sample is the high pressure sun battery.
The present invention's beneficial effect compared with prior art is:
(1) adopts electron accelerator and plasma source, can simulate the charged environment of high orbit when the ground magnetic substorm preferably;
(2) high rail star is workable with material charged effect ground simulation test device and method, and the test unit working stability is applicable to and measures the charged effect that various stars are used material.
Description of drawings
Fig. 1 is high rail star of the present invention material charged effect ground simulation test device structural drawing.
Among the figure: 1-screened room, 2-vacuum chamber, 3-electron accelerator, 4-shielding case, 5-plasma source, 6-sample platform, 7-insulating mat, 8-material sample, 9-vacuum-pumping system, the three-dimensional gear train of 10-, 11-oscillograph, 12-pulse current probe, 13-noncontact pot, 14-camera.
Embodiment
As shown in Figure 1, be high rail star of the present invention material charged effect ground simulation test device, described device comprises screened room 1, vacuum chamber 2, electron accelerator 3, shielding case 4, plasma source 5, sample platform 6, insulating mat 7, vacuum-pumping system 9, three-dimensional gear train 10, oscillograph 11, pulse current probe 12, noncontact pot 13, camera 14, and regulated power supply;
In vacuum chamber 2 inside, electron accelerator 3 and camera 14 are installed in vacuum chamber 2 tops; Plasma source 5 is installed in vacuum chamber 2 sidewalls, is provided with shielding case 4 in the periphery of plasma source 5, prevents that electronics from damaging plasma source 5;
Sample platform 6 is installed on vacuum chamber 2 bottom surfaces, and insulating mat 7 is set on the sample platform 6; Material sample 8 is placed on insulating mat 7 upper surfaces, is provided with metal back electrode at material sample 8 lower surfaces, and described metal back electrode is the conducting metal adhesive tape; Described material sample 8 is connected with vacuum chamber 2 regulated power supply outward.Three-dimensional gear train 10 is positioned at vacuum chamber 2, and three-dimensional gear train 10 is provided with contactless surface potential meter probe; Outside vacuum chamber 2, vacuum-pumping system 9 is connected with vacuum chamber 2;
Oscillograph 11, pulse current probe 12, noncontact pot 13 are positioned at screened room 1, noncontact pot 13 1 end ground connection, the other end with pass screened room 1 and vacuum chamber 2 and be connected with contactless surface potential meter probe; The lead that connects material sample 3 metal back electrodes passes vacuum chamber 2 and screened room 1 back ground connection in screened room 1, is provided with pulse current probe 12 at lead, and described pulse current probe 12 is connected with oscillograph 11.
A kind of high rail star material charged effect ground simulation experiment method may further comprise the steps:
Step 1, unlatching vacuum-pumping system 9 vacuumize for vacuum chamber 2, make vacuum tightness be lower than 3.0 * 10
-4Pa;
Step 2, the charged environment of unlatching plasma source 5 simulation GEO track plasmas, plasma temperature is 10KeV, density is 1 * 10
6/ m
3
Step 3, the charged environment of unlocking electronic accelerator 3 simulation GEO track high energy electrons, the high energy electron energy is 1Mev, beam intensity is 5nA/cm
2
Step 4, utilize the 8 discharge transient pulses of pulse current probe 12 and oscillograph 11 monitoring material samples, utilize the surface potential of contactless pot 13 monitoring material samples 8, utilize camera 14 record secondary discharge phenomenons.Described pulse current probe 12 is CT-2 pulse current probe, and described contactless pot 13 is the contactless pot of Trek341A.
Described material sample 8 is the high pressure sun battery.
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 (8)
1. one kind high rail star is with material charged effect ground simulation test device, it is characterized in that: described device comprises screened room (1), vacuum chamber (2), electron accelerator (3), shielding case (4), plasma source (5), sample platform (6), insulating mat (7), vacuum-pumping system (9), three-dimensional gear train (10), oscillograph (11), pulse current probe (12), noncontact pot (13), camera (14), and regulated power supply;
In vacuum chamber (2) inside, electron accelerator (3) and camera (14) are installed in vacuum chamber (2) top; Plasma source (5) is installed in vacuum chamber (2) sidewall, is provided with shielding case (4) in the periphery of plasma source (5);
Sample platform (6) is installed on vacuum chamber (2) bottom surface, and insulating mat (7) is set on the sample platform (6); Material sample (8) is placed on insulating mat (7) upper surface, is provided with metal back electrode at material sample (8) lower surface; Described material sample (8) is connected with vacuum chamber (2) regulated power supply outward; Three-dimensional gear train (10) is positioned at vacuum chamber (2), and three-dimensional gear train (10) is provided with contactless surface potential meter probe; Outside vacuum chamber (2), vacuum-pumping system (9) is connected with vacuum chamber (2);
Oscillograph (11), pulse current probe (12), noncontact pot (13) are positioned at screened room (1), noncontact pot (13) one end ground connection, the other end with pass screened room (1) and vacuum chamber (2) and be connected with contactless surface potential meter probe; The lead that connects material sample 3 metal back electrodes passes vacuum chamber (2) and screened room (1) back ground connection in screened room (1), is provided with pulse current probe (12) at lead, described pulse current probe 12) be connected with oscillograph (11).
2. high rail star according to claim 1 is with material charged effect ground simulation test device, and it is characterized in that: described metal back electrode is the conducting metal adhesive tape.
3. one kind high rail star is with material charged effect ground simulation experiment method, and described method uses high rail star as claimed in claim 1 with material charged effect ground simulation test device, it is characterized in that: may further comprise the steps:
Step 1, unlatching vacuum-pumping system (9) vacuumize for vacuum chamber (2);
Step 2, the charged environment of unlatching plasma source (5) simulation GEO track plasma;
Step 3, the charged environment of unlocking electronic accelerator (3) simulation GEO track high energy electron;
Step 4, utilize pulse current probe (12) and oscillograph (11) monitoring material sample (8) discharge transient pulse, utilize the surface potential of contactless pot (13) monitoring material sample (8), utilize camera (14) record secondary discharge phenomenon.
4. high rail star according to claim 3 is with material charged effect ground simulation experiment method, and it is characterized in that: vacuum environment vacuum tightness is lower than 3.0 * 10 in the described step 1
-4Pa.
5. high rail star according to claim 3 is with material charged effect ground simulation experiment method, and it is characterized in that: the plasma temperature scope that described step 2 ionic medium body source (5) produces is that 1～50KeV is adjustable, and density range is 1 * 10
5～1 * 10
6/ m
3Adjustable.
6. high rail star according to claim 3 is with material charged effect ground simulation experiment method, it is characterized in that: electron accelerator in the described step 3 (3) provides the energy range of high energy electron adjustable in 0.8～2.3MeV, and the beam current density scope is at 1～25nA/cm
2Interior adjustable.
7. high rail star according to claim 3 is with material charged effect ground simulation experiment method, it is characterized in that: adopt the spark pulse of CT-2 pulse current probe monitoring material sample (8) in the described step 4, adopt the contactless pot monitoring of Trek341A material sample (8) surface potential.
8. high rail star according to claim 3 is with material charged effect ground simulation experiment method, and it is characterized in that: described material sample (8) is the high pressure sun battery.
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|---|---|---|---|
| CN2013101453517A CN103245858A (en) | 2013-04-24 | 2013-04-24 | Device and method for ground-based simulation experimentation of charging effect of high altitude satellite material |
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| CN103760432A (en) * | 2013-12-20 | 2014-04-30 | 兰州空间技术物理研究所 | Polar orbit satellite bus power cable secondary discharge ground simulation test system and method |
| CN104267064A (en) * | 2014-09-04 | 2015-01-07 | 兰州空间技术物理研究所 | Sensor for in-orbit monitoring of spacecraft surface potential |
| CN105761588A (en) * | 2014-12-19 | 2016-07-13 | 中国科学院空间科学与应用研究中心 | Simulation device of satellite deep charging and discharging phenomenon |
| 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 |
| CN107765047A (en) * | 2016-08-15 | 2018-03-06 | 特克特朗尼克公司 | High frequency time-domain reflectometry investigation system |
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| CN109813974A (en) * | 2018-12-18 | 2019-05-28 | 兰州空间技术物理研究所 | A kind of geostationary orbit material inequality charging test device |
| CN110275070A (en) * | 2019-06-26 | 2019-09-24 | 西安交通大学 | Surface potential self-operated measuring unit and method under a kind of particle bombardment |
| CN110412441A (en) * | 2019-06-24 | 2019-11-05 | 深圳市森美协尔科技有限公司 | Vacuum high/low temperature semiconducter device testing probe station and semiconducter device testing method |
| CN113009242A (en) * | 2021-02-25 | 2021-06-22 | 西安理工大学 | Device and method for measuring surface potential distribution and attenuation of array fluxgate |
| CN114018436A (en) * | 2021-11-08 | 2022-02-08 | 北京卫星环境工程研究所 | Spacecraft material space strong electromagnetic environment effect test system |
| 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 |
| CN114671055A (en) * | 2022-03-24 | 2022-06-28 | 中国科学院国家空间科学中心 | Ground simulation experiment device and method for triboelectrification in lunar surface comprehensive environment |
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| CN103760432B (en) * | 2013-12-20 | 2016-09-28 | 兰州空间技术物理研究所 | Polar-orbiting satellite bus feed cable secondary discharge injection ground simulation test system and method |
| CN103760432A (en) * | 2013-12-20 | 2014-04-30 | 兰州空间技术物理研究所 | Polar orbit satellite bus power cable secondary discharge ground simulation test system and method |
| CN104267064A (en) * | 2014-09-04 | 2015-01-07 | 兰州空间技术物理研究所 | Sensor for in-orbit monitoring of spacecraft surface potential |
| CN105761588A (en) * | 2014-12-19 | 2016-07-13 | 中国科学院空间科学与应用研究中心 | Simulation device of satellite deep charging and discharging phenomenon |
| 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 |
| CN107765047A (en) * | 2016-08-15 | 2018-03-06 | 特克特朗尼克公司 | High frequency time-domain reflectometry investigation system |
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| CN109813974A (en) * | 2018-12-18 | 2019-05-28 | 兰州空间技术物理研究所 | A kind of geostationary orbit material inequality charging test device |
| CN110412441A (en) * | 2019-06-24 | 2019-11-05 | 深圳市森美协尔科技有限公司 | Vacuum high/low temperature semiconducter device testing probe station and semiconducter device testing method |
| CN110275070A (en) * | 2019-06-26 | 2019-09-24 | 西安交通大学 | Surface potential self-operated measuring unit and method under a kind of particle bombardment |
| CN113009242A (en) * | 2021-02-25 | 2021-06-22 | 西安理工大学 | Device and method for measuring surface potential distribution and attenuation of array fluxgate |
| CN113009242B (en) * | 2021-02-25 | 2022-10-04 | 西安理工大学 | Device and method for measuring surface potential distribution and attenuation of array fluxgate |
| CN114018436A (en) * | 2021-11-08 | 2022-02-08 | 北京卫星环境工程研究所 | Spacecraft material space strong electromagnetic environment effect test system |
| CN114018436B (en) * | 2021-11-08 | 2023-11-10 | 北京卫星环境工程研究所 | Spacecraft material space strong electromagnetic environment effect test system |
| 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 |
| CN114671055A (en) * | 2022-03-24 | 2022-06-28 | 中国科学院国家空间科学中心 | Ground simulation experiment device and method for triboelectrification in lunar surface comprehensive environment |
| CN114671055B (en) * | 2022-03-24 | 2023-02-07 | 中国科学院国家空间科学中心 | Ground simulation experiment device and method for frictional electrification in lunar surface comprehensive environment |
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Application publication date: 20130814 |