CN102937697A - LEO (low earth orbit) high-voltage solar cell secondary discharge test device and method - Google Patents

LEO (low earth orbit) high-voltage solar cell secondary discharge test device and method Download PDF

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Publication number
CN102937697A
CN102937697A CN201210484715XA CN201210484715A CN102937697A CN 102937697 A CN102937697 A CN 102937697A CN 201210484715X A CN201210484715X A CN 201210484715XA CN 201210484715 A CN201210484715 A CN 201210484715A CN 102937697 A CN102937697 A CN 102937697A
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battery group
voltage
solar battery
secondary discharge
solar
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王俊
李得天
柳青
杨生胜
秦晓刚
汤道坦
史亮
陈益峰
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510 Research Institute of 5th Academy of CASC
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Abstract

The invention relates to an LEO (low earth orbit) high-voltage solar cell secondary discharge test device and method, belonging to the field of measurement. The device comprises a vacuum chamber, an Ar plasma source, a camera, a three-dimensional driving mechanism, a vacuum-pumping system, a test bench, an insulating mat, a high-voltage solar cell work simulation system, a solar cell array, a non-contact potentiometer and a potential test system. The method comprises the following steps: vacuumizing the vacuum chamber, starting the Ar plasma source to emit plasma, starting the high-voltage solar cell work simulation system to induce the solar cell array to perform surface static discharge, and monitoring the surface potential charge process of the solar cell array by means of the potential test system and the non-contact potentiometer. Thus, the device and the method can well simulate the LEO plasma environment, can work stably and are applicable to various LEO satellite high-power high-voltage solar cell secondary discharge ground simulation tests.

Description

A kind of Low Earth Orbit High-Voltage Solar Array secondary discharge test unit and method
Technical field
The present invention relates to a kind of Low Earth Orbit High-Voltage Solar Array secondary discharge test unit and method, be particularly related to the low earth to LEO() in the orbit space band electrical environment, the High-Voltage Solar Array secondary discharge ground simulation test device and the method that adopt artificial plasma device to carry out.Belong to fields of measurement.
Background technology
Along with continuing to bring out of satellite new technology and new demand, also more and more higher to the requirement of satellite energy resource system, so satellite sun energy battery power supply system will be towards high-power, high-tension trend development.Yet the raising of operating voltage has also increased the coupling machine meeting of solar cell and spatial charging environment, has occurred because the new failure mode that Induced by Space Electrostatic Discharges causes.In view of anomalous event and the fault of electrostatic discharge problem to the low earth-orbit satellite generation, and the situation that causes solar cell output power heavy losses, the research institutions such as U.S. NASA, European ESA and Japanese JAXA all drop into a large amount of human and material resources and carry out research work for High-Voltage Solar Array injuring rule and guard technology.
Development along with the Chinese Space application technology, the high-power high voltage sun of LEO track will be widely adopted, and the LEO track High-Voltage Solar Array power loss problem that is therefore caused by the electrostatic breakdown event will become the new problem that Chinese Space Power Management Design person must face and solve.At present, China is deep not enough to the understanding of high-power satellite High-Voltage Solar Array electrostatic breakdown effect, therefore lacks effective means of defence and design means, has restricted the widespread use of high-power high voltage solar cell in space plasma band electrical environment.Ground is carried out High-Voltage Solar Array secondary discharge simulation test and is also had following main difficulty:
(1) ground can not real simulation space plasma band electrical environment;
(2) ground is difficult to carry out the simulation test of full-size(d) space high-voltage solar cell;
(3) High-Voltage Solar Array static secondary discharge effect is a kind of quick, random process.
Therefore, need badly by selecting correct effectively test method to carry out the research of low earth-orbit satellite High-Voltage Solar Array secondary discharge ground simulation test.
Summary of the invention
The technical matters that the present invention solves is: in conjunction with space high-voltage solar battery structure characteristics, utilize Ar plasma source simulation experiment method to carry out the research of High-Voltage Solar Array secondary discharge.
For achieving the above object, technical scheme of the present invention is as follows.
A kind of Low Earth Orbit High-Voltage Solar Array secondary discharge experimental provision, described device comprises: vacuum chamber, Ar plasma source, camera, three-dimensional driving mechanism, vacuum-pumping system, testing table, insulating mat, High-Voltage Solar Array work simulation system, solar battery group, contactless pot, potential test system;
Wherein, at internal vacuum chamber, testing table is installed on the vacuum chamber bottom surface, and solar battery group is positioned on the testing table and with testing table and insulate; Three-dimensional driving mechanism is positioned at internal vacuum chamber, and contactless pot is positioned at the solar battery group top and is fixedly connected with three-dimensional driving mechanism, realizes that by three-dimensional driving mechanism contactless pot is in the motion on solar battery group surface; Camera is installed in the vacuum chamber top;
Outside at vacuum chamber, the potential test system is connected with contactless pot by wire; High-Voltage Solar Array work simulation system is connected with solar battery group; Vacuum-pumping system is connected with vacuum chamber,
Contactless pot and potential test system act as, the charging potential on test solar battery group surface;
High-Voltage Solar Array work simulation system act as, and for solar battery group provides operating voltage and working current, is used for the analog satellite actual working state;
Preferred described solar cell working simulation system comprises pull-up resistor, high-voltage power supply, building-out capacitor, regulated power supply, oscillograph, the first pulse current probe, the second pulse current probe, substrate; Described solar battery group is installed in the substrate, comprises the first solar battery group and the second solar battery group; First, second solar battery group is one or an above solar cell series connection, and the type of described solar cell, size and number are identical;
Described solar cell working simulation system and solar battery group consist of the solar battery group operating circuit, and its annexation is as follows:
Wherein, high-voltage power supply one end ground connection, the other end is connected with substrate; Successively with after the first solar battery group, pull-up resistor, the second solar battery group are connected, the wire that is connected with the other end of regulated power supply is combined into one the tunnel to one end of regulated power supply by wire, then is connected afterwards ground connection with building-out capacitor; Between high-voltage power supply and substrate, be provided with the first pulse current probe, between regulated power supply and the first solar battery group, be provided with the second pulse current probe; Described the first pulse current probe, the second pulse current probe are connected with oscillograph respectively;
The actual working state of the operating circuit of described solar battery group is: by high-voltage power supply to substrate add negative high voltage (scope 0～-10kV), simultaneously with Ar plasma source simulation LEO track plasma band electrical environment, be subject to the effect of substrate negative high voltage when the Ar plasma of emission, so that the Ions Bombardment of positively charged accumulates the formation positive potential on solar battery group; When the positive potential of accumulation surpasses the breakdown threshold of solar battery group once discharge occuring, is the solar battery group power supply by regulated power supply afterwards again, after surpassing the secondary discharge threshold value, and solar battery group generation secondary discharge phenomenon.
A kind of Low Earth Orbit High-Voltage Solar Array secondary discharge test method, described method step is as follows:
Step 1, unlatching vacuum-pumping system vacuumize vacuum chamber, to vacuum tightness≤3.0 * 10 -4Pa;
Step 2, unlatching Ar plasma source transmitting plasma, the plasma environment of simulation LEO track;
Step 3, unlatching High-Voltage Solar Array work simulation system bring out the discharge of solar battery group surface electrostatic;
Step 4, unlatching potential test system realize that by three-dimensional driving mechanism contactless pot is in the movement on solar battery group surface; Monitor solar battery group surface charging current potential by potential test system and contactless pot, and take the secondary discharge process of solar battery group by camera.
When test finishes, close successively High-Voltage Solar Array work simulation system, Ar plasma source, close at last vacuum-pumping system.
In the preferred steps two, the energy range of the plasma that the Ar plasma source produces is 0.1～0.3eV, and density range is 1 * 10 9～1 * 10 12/ m 3
In the preferred steps three, described unlatching High-Voltage Solar Array work simulation system is to open high-voltage power supply and regulated power supply; Wherein the voltage range that provides for substrate of high-voltage power supply is-10 4V～0V, the operating voltage range that regulated power supply provides for solar battery group is 0V～200V; Current margin is direct current 0A～4.0A.
In the preferred steps four, by the secondary discharge transient pulse waveform of oscillograph monitoring solar battery group.
In the preferred steps four, adopt contactless pot monitoring solar battery group surface potential level, the potentiometer measurement scope be 0V～± 20000V; Adopt first, second pulse current probe and oscillograph monitoring solar battery group surface electrostatic sparking voltage and secondary discharge transient pulse waveform;
Building-out capacitor C=0.033 μ F in the preferred operating circuit.
Beneficial effect
(1) adopts the Ar plasma source, can better simulate LEO track plasma environment;
(2) theoretical according to High-Voltage Solar Array principle of work and space charge, designed external compensation capacity test circuit, solved the big or small problem that affects analog reslt of ground simulation test sample area;
(3) High-Voltage Solar Array secondary discharge ground simulation experiment method is workable, and this pilot system working stability is applicable to various low earth-orbit satellite high-power high voltage solar cell secondary discharge ground simulation tests.
Description of drawings
Fig. 1 is the structural representation of Low Earth Orbit High-Voltage Solar Array secondary discharge test unit of the present invention.
Fig. 2 is the operating circuit schematic diagram of solar battery group of the present invention.
Among the figure: 1-vacuum chamber, 2-camera, 3-Ar plasma source, 4-solar battery group, 5-vacuum-pumping system, 6-insulating mat, 7-testing table, 8-High-Voltage Solar Array work simulation system, the contactless pot of 9-, the three-dimensional driving mechanism of 10-, 11-pull-up resistor, 12-high-voltage power supply, 13-building-out capacitor, 14-regulated power supply, 15-oscillograph, 16-the first pulse current probe, 17-the second pulse current probe, 18-substrate.
Embodiment
As shown in Figure 1, a kind of Low Earth Orbit High-Voltage Solar Array secondary discharge experimental provision, described device comprises: vacuum chamber 1, Ar plasma source 3, camera 2, three-dimensional driving mechanism 10, vacuum-pumping system 5, testing table 7, insulating mat 6, High-Voltage Solar Array work simulation system 8, solar battery group 4, contactless pot 9, potential test system;
Wherein, in vacuum chamber 1 inside, testing table 7 is installed on the vacuum chamber bottom surface, is provided with insulating mat 6 at testing table 7, and solar battery group 4 is placed on the insulating mat 6; Three-dimensional driving mechanism 10 is positioned at testing table 7 one sides; Contactless pot 9 is positioned at solar battery group 4 tops, and is fixedly connected with three-dimensional driving mechanism 10, realizes its motion on solar battery group 4 surfaces by three-dimensional driving mechanism 10; Camera 2 is installed in vacuum chamber 1 top;
Have the through hole that wire is passed through at vacuum chamber 1; The through hole of wire by having on the vacuum chamber 1 will be positioned at vacuum chamber 1 outer potential test system and be connected with contactless pot 9; In like manner, the through hole of wire by having on the vacuum chamber will be positioned at vacuum chamber 1 outer High-Voltage Solar Array work simulation system 8 and be connected with solar battery group 4; Vacuum-pumping system 5 is connected with vacuum chamber 1;
Described solar cell working simulation system 8 comprises pull-up resistor 11, high-voltage power supply 12, building-out capacitor 13, regulated power supply 14, oscillograph 15, the first pulse current probe 16, the second pulse current probe 17, substrate 18; Described solar battery group 4 is installed in the substrate 18, comprises the first solar battery group and the second solar battery group; First, second solar battery group is one or an above solar cell series connection, and the type of described solar cell, size and number are identical; The numerical value of the building-out capacitor 13 in the operating circuit is C=0.033 μ F.Described the first pulse current probe 16, the second pulse current probe 17 are CT-2 pulse current probe.Described substrate 18 materials are honeycomb aluminum.
The annexation of described solar battery group operating circuit is as follows:
Wherein, high-voltage power supply 12 1 end ground connection, the other end is connected with substrate 18; Successively with after the first solar battery group, pull-up resistor 11, the second solar battery group are connected, the wire that is connected with the other end of regulated power supply 14 is combined into one the tunnel to one end of regulated power supply 14 by wire, then is connected afterwards ground connection with building-out capacitor 13; Between high-voltage power supply 12 and substrate 18, be provided with the first pulse current probe 16, between regulated power supply 14 and the first solar battery group, be provided with the second pulse current probe 17; Described the first pulse current probe 16, the second pulse current probe 17 are connected with oscillograph 15 respectively;
The actual working state of the operating circuit of described solar battery group is: by high-voltage power supply 12 give substrate 18 add negative high voltage (scope 0～-10kV), simultaneously with Ar plasma source 3 simulation LEO track plasma band electrical environments, be subject to the effect of substrate 18 negative high voltages when the Ar plasma of emission, so that the Ions Bombardment of positively charged accumulates the formation positive potential on solar battery group 4; Once discharge occurs when the positive potential that accumulates surpasses the breakdown threshold of solar battery group 4, is that solar battery group 4 is powered by regulated power supply 14 afterwards again, and after surpassing the secondary discharge threshold value, the secondary discharge phenomenons occur solar battery group 4.
A kind of Low Earth Orbit High-Voltage Solar Array secondary discharge test method, described method step is as follows:
Step 1, solar battery group 4 is positioned in the vacuum chamber 1, opens 5 pairs of vacuum chambers 1 of vacuum-pumping system and vacuumize, to vacuum tightness≤3.0 * 10 -4Pa;
Step 2, unlatching Ar plasma source transmitting plasma, the plasma environment of simulation LEO track; Plasma temperature is 0.3eV, and density is 1 * 10 12/ m 3
High-voltage power supply 12 and regulated power supply 14 are namely opened by step 3, unlatching High-Voltage Solar Array work simulation system 8, and 12 pairs of substrates 18 of high-voltage power supply apply-10 4The negative high voltage of V～0V, regulated power supply 14 is begun by 0V for the operating voltage that solar battery group 4 provides, and increases 10V in per 10 minutes, until 200V; Working current is direct current 2.1A, is set as unrestricted model, brings out the discharge of solar battery group 4 surface electrostatics;
Step 4, unlatching potential test system realize that by three-dimensional driving mechanism 10 contactless pot 9 is in the movement on solar battery group 4 surfaces; Adopt the contactless pot 9 monitoring solar battery group of potential test system and Trek341 4 surface potential levels, adopt the first pulse current probe 16, the second pulse current probe 17 and oscillograph 15 monitoring solar battery group 4 surface electrostatic sparking voltages and secondary discharge transient pulse waveforms, and take the secondary discharge process of solar battery group 4 by camera 2.
When test finishes, close successively High-Voltage Solar Array work simulation system 8, Ar plasma source 3, close at last vacuum-pumping system 5.
In sum, above is preferred embodiment of the present invention only, is 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 (9)

1. Low Earth Orbit High-Voltage Solar Array secondary discharge experimental provision, it is characterized in that: described device comprises: vacuum chamber (1), Ar plasma source (3), camera (2), three-dimensional driving mechanism (10), vacuum-pumping system (5), testing table (7), insulating mat (6), High-Voltage Solar Array work simulation system (8), solar battery group (4), contactless pot (9), potential test system;
Wherein, in vacuum chamber (1) inside, testing table (7) is installed on the vacuum chamber bottom surface, and solar battery group is positioned at testing table (7) and upward and with testing table (7) insulate; Three-dimensional driving mechanism (10) is positioned at vacuum chamber (1) inside, and contactless pot (9) is positioned at solar battery group (4) top and is fixedly connected with three-dimensional driving mechanism (10); Camera (2) is installed in vacuum chamber (1) top;
In vacuum chamber (1) outside, the potential test system is connected with contactless pot (9) by wire; High-Voltage Solar Array work simulation system (8) is connected with solar battery group (4); Vacuum-pumping system (5) is connected with vacuum chamber (1).
2. a kind of Low Earth Orbit High-Voltage Solar Array secondary discharge experimental provision according to claim 1, it is characterized in that: described solar cell working simulation system (8) comprises pull-up resistor (11), high-voltage power supply (12), building-out capacitor (13), regulated power supply (14), oscillograph (15), the first pulse current probe (16), the second pulse current probe (17), substrate (18); Described solar battery group (4) is installed in the substrate (18), comprises the first solar battery group and the second solar battery group; First, second solar battery group is one or an above solar cell series connection, and the type of described solar cell, size and number are identical;
Described solar cell working simulation system and solar battery group consist of the solar battery group operating circuit, and its annexation is as follows:
Wherein, high-voltage power supply (12) one end ground connection, the other end is connected with substrate (18); One end of regulated power supply (14) is successively with after the first solar battery group, pull-up resistor (11), the second solar battery group are connected, and is combined into one the tunnel with the other end of regulated power supply (14), then by building-out capacitor (13) ground connection; Between high-voltage power supply (12) and substrate (18), be provided with the first pulse current probe (16), between regulated power supply (14) and the first solar battery group, be provided with the second pulse current probe (17); Described the first pulse current probe (16), the second pulse current probe (17) are connected with oscillograph (15) respectively.
3. Low Earth Orbit High-Voltage Solar Array secondary discharge test method, it is characterized in that: described method is used device as claimed in claim 1 or 2, it is characterized in that: described method step is as follows:
Step 1, unlatching vacuum-pumping system (5) vacuumize vacuum chamber (1), to vacuum tightness≤3.0 * 10 -4Pa;
Step 2, unlatching Ar plasma source (3) transmitting plasma, the plasma environment of simulation LEO track;
Step 3, unlatching High-Voltage Solar Array work simulation system (8) bring out the discharge of solar battery group (4) surface electrostatic;
Step 4, unlatching potential test system realize that by three-dimensional driving mechanism (10) contactless pot (9) is in the movement on solar battery group (4) surface; By potential test system and contactless pot (9) monitoring solar battery group (4) surface charging current potential, and pass through the secondary discharge process that camera (2) is taken solar battery group (4).
4. a kind of Low Earth Orbit High-Voltage Solar Array secondary discharge test method as claimed in claim 3 is characterized in that: in the step 2, the energy range of the plasma that Ar plasma source (3) produces is 0.1～0.3eV, and density range is 1 * 10 9～1 * 10 12/ m 3
5. a kind of Low Earth Orbit High-Voltage Solar Array secondary discharge test method as claimed in claim 3, it is characterized in that: in the step 3, described unlatching High-Voltage Solar Array work simulation system (8) is for opening high-voltage power supply (12) and regulated power supply (14).
6. a kind of Low Earth Orbit High-Voltage Solar Array secondary discharge test method as claimed in claim 5, it is characterized in that: in the step 3, the voltage range that high-voltage power supply (12) provides for substrate (18) is-10 4V～0V, the operating voltage range that regulated power supply (14) provides for solar battery group (4) is 0V～200V; Current margin is direct current 0A～4.0A.
7. a kind of Low Earth Orbit High-Voltage Solar Array secondary discharge test method as claimed in claim 3 is characterized in that: in the step 4, by the secondary discharge transient pulse waveform of oscillograph (15) monitoring solar battery group (4).
8. a kind of Low Earth Orbit High-Voltage Solar Array secondary discharge test method as claimed in claim 3, it is characterized in that: in the step 4, adopt contactless pot (9) monitoring solar battery group (4) surface potential level, pot (9) measurement range be 0V～± 20000V; Adopt the first pulse current probe (16), the second pulse current probe (17) and oscillograph (15) monitoring solar battery group (4) surface electrostatic sparking voltage and secondary discharge transient pulse waveform.
9. a kind of Low Earth Orbit High-Voltage Solar Array secondary discharge test method as claimed in claim 3 is characterized in that: the building-out capacitor in the operating circuit (13) value is C=0.033 μ F.
CN201210484715XA 2012-11-25 2012-11-25 LEO (low earth orbit) high-voltage solar cell secondary discharge test device and method Pending CN102937697A (en)

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Cited By (8)

* Cited by examiner, † Cited by third party
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
CN104378067A (en) * 2014-11-05 2015-02-25 北京卫星环境工程研究所 Solar cell module unit elemental oxygen effect testing system
CN104535868A (en) * 2015-01-09 2015-04-22 中国人民解放军军械工程学院 Electrostatic discharge test device under electromagnetic pulse radiation environment
CN105044613A (en) * 2015-07-31 2015-11-11 上海卫星工程研究所 High-fidelity satellite load scene reproduction device and method
CN105182648A (en) * 2015-10-28 2015-12-23 深圳市华星光电技术有限公司 Liquid crystal display panel and liquid crystal display panel ESD monitoring method
CN109525193A (en) * 2018-09-30 2019-03-26 兰州空间技术物理研究所 A kind of low orbit high pressure acid leaching electric current collection test macro and method
CN112953381A (en) * 2021-02-04 2021-06-11 中国科学院微小卫星创新研究院 Ground test method for solar cell array driving device
CN113533914A (en) * 2021-07-09 2021-10-22 中国人民解放军陆军工程大学 Electrostatic pulse induced electrostatic discharge experimental system and method in vacuum environment

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3984730A (en) * 1975-07-11 1976-10-05 The Unites States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Method and apparatus for neutralizing potentials induced on spacecraft surfaces
US6248950B1 (en) * 1998-02-21 2001-06-19 Space Systems/Loral, Inc. Solar array augmented electrostatic discharge for spacecraft in geosynchronous earth orbit
CN101275989A (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 high pressure sun array electrostatic punch-through effect earth surface simulation test
CN102507717A (en) * 2011-10-20 2012-06-20 中国航天科技集团公司第五研究院第五一〇研究所 Device and method for on-orbit monitoring of charging of satellite material surface
CN102540093A (en) * 2011-12-19 2012-07-04 北京卫星环境工程研究所 Ground simulating test device and method for secondary electric arc of solar cell array for aerospace

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3984730A (en) * 1975-07-11 1976-10-05 The Unites States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Method and apparatus for neutralizing potentials induced on spacecraft surfaces
US6248950B1 (en) * 1998-02-21 2001-06-19 Space Systems/Loral, Inc. Solar array augmented electrostatic discharge for spacecraft in geosynchronous earth orbit
CN101275989A (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 high pressure sun array electrostatic punch-through effect earth surface simulation test
CN102507717A (en) * 2011-10-20 2012-06-20 中国航天科技集团公司第五研究院第五一〇研究所 Device and method for on-orbit monitoring of charging of satellite material surface
CN102540093A (en) * 2011-12-19 2012-07-04 北京卫星环境工程研究所 Ground simulating test device and method for secondary electric arc of solar cell array for aerospace

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
李凯等: "空间太阳阵二次放电的模拟实验研究", 《物理学报》 *

Cited By (10)

* Cited by examiner, † Cited by third party
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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
CN104378067A (en) * 2014-11-05 2015-02-25 北京卫星环境工程研究所 Solar cell module unit elemental oxygen effect testing system
CN104535868A (en) * 2015-01-09 2015-04-22 中国人民解放军军械工程学院 Electrostatic discharge test device under electromagnetic pulse radiation environment
CN105044613A (en) * 2015-07-31 2015-11-11 上海卫星工程研究所 High-fidelity satellite load scene reproduction device and method
CN105044613B (en) * 2015-07-31 2018-02-02 上海卫星工程研究所 Hi-Fi satellite load scene reproducer and method
CN105182648A (en) * 2015-10-28 2015-12-23 深圳市华星光电技术有限公司 Liquid crystal display panel and liquid crystal display panel ESD monitoring method
CN109525193A (en) * 2018-09-30 2019-03-26 兰州空间技术物理研究所 A kind of low orbit high pressure acid leaching electric current collection test macro and method
CN112953381A (en) * 2021-02-04 2021-06-11 中国科学院微小卫星创新研究院 Ground test method for solar cell array driving device
CN112953381B (en) * 2021-02-04 2021-12-14 中国科学院微小卫星创新研究院 Ground test method for solar cell array driving device
CN113533914A (en) * 2021-07-09 2021-10-22 中国人民解放军陆军工程大学 Electrostatic pulse induced electrostatic discharge experimental system and method in vacuum environment

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Application publication date: 20130220