CN103456831A - Arc discharge restraining method for high-voltage solar cell array in low-rail plasma environment - Google Patents
Arc discharge restraining method for high-voltage solar cell array in low-rail plasma environment Download PDFInfo
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- CN103456831A CN103456831A CN2012101772575A CN201210177257A CN103456831A CN 103456831 A CN103456831 A CN 103456831A CN 2012101772575 A CN2012101772575 A CN 2012101772575A CN 201210177257 A CN201210177257 A CN 201210177257A CN 103456831 A CN103456831 A CN 103456831A
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Abstract
The invention relates to an arc discharge restraining method for a high-voltage solar cell array in a low-rail plasma environment. The arc discharge restraining method is especially suitable for operating the high-voltage solar cell array in the low-rail plasma environment. The method comprises the steps that an exposed conductor of a solar cell circuit is coated by RTV silica gel or embedded into a substrate to prevent a conductor and a plasma from being in contact, the distance between series cell circuits is optimized and designed, the current of the single circuit is reduced and is effectively isolated by an added isolating diode, a glass cover plate completely cover the solar cells to prevent the contact between the electrified portion and the plasma, and a ground simulation low-rail plasma environment discharge test is utilized to carry out verification. The arc discharge restraining method solves the problem of restraining arc discharge of the high-voltage solar cell array in the low-rail plasma environment, improves the threshold values of primary discharge and secondary discharge of the high-voltage solar cell array in the low-rail plasma environment and improves adaptability in the low-rail plasma environment.
Description
Technical field
The present invention relates to a kind of low rail plasma environment high pressure sun battery battle array arc discharge inhibition method, belong to spacecraft power supply system solar battery array technical field.
Background technology
The main space aircraft of China's manned astro-engineering is operated on the Low Earth Orbit of 300 ~ 500km height, and this height district space plasma is mainly ionospheric plasma.The environment more complicated of 300 ~ 500km track, the density of plasma in this interval has individual peak value.The power supply source of spacecraft is mainly solar battery array, along with spacecraft, to long-life needs, the power stage of solar battery array becomes increasing, long apart from the loss in electrical transmission in order to reduce, reduce weight, need to adopt the novel high-pressure solar battery array of high efficiency light in structure.Because velocity of electrons is more much larger than ion, the electronegative position of Flight Vehicle Structure meeting, the electronics random current that arrives aircraft is more much larger than ionic current, and most of area of battery battle array and the conducting structure of connection can be assembled ion, and causing the net current on battery battle array and Flight Vehicle Structure is zero.According to the characteristics of space environment, most of electric current of assembling on the battery front is back bias voltage, reaches 100V and above high pressure sun battery battle array, and it can produce arc discharge in the low orbit plasma environment.Once electric discharge can cause power loss and electromagnetic interference, and secondary arc discharge meeting causes larger power loss and electromagnetic interference, damages the solar cell circuit and even causes permanent short.Domestic existing technology is for high rail high pressure rigid solar cell array electrostatic defending.Different due to high rail environment and low rail environment, the difference of solar battery array structure, so this technology be not suitable for low rail high pressure sun battery battle array.The present invention is directed to low rail high pressure sun battery battle array, solved low rail plasma environment solar battery array arc discharge and suppressed problem.
Do not have at present to find and explanation or the report of technology similar to the present invention, not yet collect both at home and abroad similarly data yet.
Summary of the invention
For overcoming the prior art deficiency, problem to be solved by this invention is to realize that the low rail plasma environment arc discharge of high pressure sun battery battle array suppresses, and verify the validity of inhibition method by discharge test, improve the adaptability of high pressure sun battery battle array in low rail plasma environment.
For solving the problems of the technologies described above, the present invention is directed to low rail high pressure sun battery battle array characteristics, low rail plasma environment arc discharge inhibition and verification method have been proposed: adopt solar cell circuit bare exposed conductor to apply the method for RTV silica gel, or circuit is embedded in substrate, insulated conductor contacts with plasma, improve discharge threshold, reduce the generation of arc discharge; Optimize the design of cloth sheet, make voltage between the maximum string of battery circuit be less than 55V, be less than secondary arc discharge threshold value; Optimize the design of battery circuit string spacing, improve secondary arc discharge threshold value, design string spacing 2mm; Single crosstalk pond modular circuit output current is less than 0.8A and adds isolating diode is isolated, and with this, reduces the electric current that maintains of secondary arc discharge, improves the voltage threshold of secondary arc discharge; Meet the cover glass edge and surpass battery edge 0.1mm, cover solar cell fully, the blocking-up battery contacts with plasma, reduces the generation of arc discharge; Adopt the low rail vacuum environment of vacuum tank simulation, adopt ECR type plasma source to produce plasma, the low rail plasma environment of simulation, the solar battery array small specimen is placed in vacuum tank, carry out an arc discharge and secondary arc discharge analogue test, obtain an arc discharge of high pressure sun battery battle array and secondary arc discharge voltage current threshold, complete the checking of the low rail plasma environment electric discharge of high pressure sun battery battle array.
Adopt arc discharge inhibition method of the present invention, can effectively solve the low rail plasma environment arc discharge inhibition of high pressure sun battery battle array and validation problem, adopt the present invention in low rail high pressure sun battery battle array design, develop the semi-rigid solar cell array that can fly in-orbit and passed through the higher flexible solar cell array of discharge threshold of verification experimental verification, can improve the adaptability of high pressure sun battery battle array in low rail plasma environment, reach and reduce its arc discharge in-orbit, stop the inhibition of secondary arc discharge in-orbit.
The accompanying drawing explanation
Fig. 1 semi-rigid solar cell plate schematic diagram
Fig. 2 flexible solar cell plate schematic diagram
The semi-rigid cell panel test specimen of Fig. 3 schematic diagram
Fig. 4 flexible battery plate test specimen schematic diagram
Fig. 5 single step of releasing electric test allocation plan
Fig. 6 secondary arc discharge test configurations figure
Fig. 7 single step of releasing power path schematic diagram
Fig. 8 secondary arc discharge path schematic diagram.
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.
As shown in Figure 1, adopt solar cell circuit bare exposed conductor to apply the method for RTV silica gel 1, insulated conductor contacts with plasma.Semi-rigid high pressure sun cell panel and rigidity solar panel have relatively big difference, the battery module of semi-rigid solar cell array is fixed on grid panel, bigger face glass cover plate 3 and the back side cover glass 4 of physical dimension pasted on the two sides of solar cell piece 7, with the junction, charged position (chip interconnect sheet 5---solar cell piece 7 edges) that will be exposed in plasma environment, isolates completely; Battery module is comprised of 6 or 4 battery units (2 * 3 or 2 * 2 array); Guide to the busbar 6 at the back side from the battery module front as electrical transmission, surface-coated RTV silica gel 1, realize exposed conductor and the isolation of plasma ambient.Controlling gap between the adjacent cell string is 2mm.
Fig. 2 shows the execution mode of flexible solar cell plate, and the flexible solar cell plate is comprised of solar cell 8 and flexible base, board 11.Solar cell 8 is bonded on flexible base, board 11 by egative film glue 9, and size of the positive stickup of solar cell 8 is slightly larger than the cover glass 10 of battery.The flexible solar cell plate, on semi-rigid solar cell plate protection Design basis, is embedded in part solar cell 8 connecting circuits in flexible base, board 11, is formed with the flexible base, board 11 of pre-buried circuit, and the minimizing energized conductor contacts with plasma.
Can improve the arc discharge threshold voltage by above-mentioned execution mode, reduce the once probability of electric discharge, suppress between string to occur between adjacent block the secondary arc discharge.Adopt the low rail plasma environment of ground simulation to carry out discharge test, can verify the validity of the low rail plasma environment electric discharge of above-mentioned high pressure sun battery battle array inhibition method.
Be illustrated in figure 3 semi-rigid cell panel test specimen schematic diagram.The semi-rigid solar cell plate is installed solar battery module, is divided into two circuit of ARRAY1 and ARRAY2, and battery module positive and negative electrode place and bare exposed conductor apply RTV silica gel 1, size 272mm * 391mm.
Be illustrated in figure 4 flexible battery plate test specimen schematic diagram.Flexible solar cell plate testpieces is installed solar cell, and positive and negative electrode place and bare exposed conductor apply RTV silica gel 1, size 130mm * 128mm.
The discharge test condition is implemented as follows:
A. vacuum tank air pressure: under plasma environment, be not more than 2 * 10
-2pa;
B. plasma density: 10
12~ 10
13m
-3;
C. plasma temperature :≤5eV;
D. temperature: battery battle array temperature<42 ℃.
Be illustrated in figure 5 single step of releasing electric test allocation plan.Testing equipment comprises the vacuum tank 12, ECR type plasma source 13 of diameter 1.5m, DC power supply 14 that 0 ~ 600V is adjustable, temperature sensor 15, pulse-generating circuit 16, oscillosynchroscope 17, PC 18, video camera 19 etc.
Test specimen is semi-rigid cell panel, comprises battery module 20 and substrate, and the substrate outward flange is framework 21.In test, substrate is also wanted biasing and is separated test with circuit, position and intensity image by watch window 22 use video camera 19 record electric discharges, measure the voltage and current of discharge loop, CP1 and CP2 are two electric current measuring points, by oscilloscope 17 pick-and-place electrical waveform, and can on PC 18, carry out Storage and Processing.Be illustrated in figure 6 single step of releasing power path schematic diagram.
Be illustrated in figure 7 secondary arc discharge test configurations figure.With the single step of releasing electric test, compare, testing equipment will increase solar battery array simulator 23(0 ~ 300V/0 ~ 5A), protective circuit 24 and slide-wire rheostat 25.Apply short circuit current 0.9A between string, between string, voltage 50V rises, the experimental condition that back bias voltage-100V rises.The position and the intensity image that in test, with video camera 19 records, discharge.CP1 ~ CP4 is four electric current measuring points, by oscilloscope 18 pick-and-place electrical waveform.Be illustrated in figure 8 secondary arc discharge path schematic diagram.
Visible, adopt the present invention successfully to solve the low rail plasma environment arc discharge inhibition of high pressure sun battery battle array and validation problem.
Adopt the present invention in the design of low rail high pressure sun battery battle array, develop the semi-rigid solar cell array that can fly in-orbit and passed through the higher flexible solar cell array of discharge threshold of verification experimental verification.Can improve the adaptability of high pressure sun battery battle array in low rail plasma environment, reach and reduce its arc discharge in-orbit, stop the inhibition of secondary arc discharge in-orbit.
Claims (1)
1. one kind is applicable to low rail plasma environment high pressure sun battery battle array arc discharge inhibition method, it is characterized in that:
Adopt solar cell circuit bare exposed conductor to apply the method for RTV silica gel, or circuit is embedded in substrate, insulated conductor contacts with plasma, improves discharge threshold, reduces the generation of arc discharge;
Optimize the design of cloth sheet, make voltage between the maximum string of battery circuit be less than 55V, be less than secondary arc discharge threshold value;
Optimize the design of battery circuit string spacing, improve secondary arc discharge threshold value, design string spacing 2mm;
Single crosstalk pond modular circuit output current is less than 0.8A and adds isolating diode is isolated, and with this, reduces the electric current that maintains of secondary arc discharge, improves the voltage threshold of secondary arc discharge;
Meet the cover glass edge and surpass battery edge 0.1mm, cover solar cell fully, the blocking-up battery contacts with plasma, reduces the generation of arc discharge;
Adopt the low rail vacuum environment of vacuum tank simulation, adopt ECR type plasma source to produce plasma, the low rail plasma environment of simulation, the solar battery array small specimen is placed in vacuum tank, carry out an arc discharge and secondary arc discharge analogue test, obtain an arc discharge of high pressure sun battery battle array and secondary arc discharge voltage current threshold, complete the checking of the low rail plasma environment electric discharge of high pressure sun battery battle array.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210177257.5A CN103456831B (en) | 2012-06-01 | 2012-06-01 | Low rail plasma environment high pressure acid leaching arc discharge suppressing method |
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|---|---|---|---|
| CN201210177257.5A CN103456831B (en) | 2012-06-01 | 2012-06-01 | Low rail plasma environment high pressure acid leaching arc discharge suppressing method |
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| CN103456831B CN103456831B (en) | 2015-11-18 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106533354A (en) * | 2016-12-05 | 2017-03-22 | 上海空间电源研究所 | Low-orbit solar cell circuit |
| CN106784101A (en) * | 2016-12-08 | 2017-05-31 | 上海空间电源研究所 | Discharge test part of low orbit |
| CN107681977A (en) * | 2017-07-05 | 2018-02-09 | 上海空间电源研究所 | Verify the in-orbit exposure test part of the low rail plasma environment guard technology of solar battery array |
| CN113114102A (en) * | 2021-03-18 | 2021-07-13 | 中国空间技术研究院 | Solar wing grounding circuit based on anti-static and fault isolation |
| 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 (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6228662B1 (en) * | 1999-03-24 | 2001-05-08 | Kaneka Corporation | Method for removing short-circuited sections of a solar cell |
| CN101483204A (en) * | 2009-02-13 | 2009-07-15 | 苏州富能技术有限公司 | Thin-film solar cell module in series parallel connection structure and processing method thereof |
-
2012
- 2012-06-01 CN CN201210177257.5A patent/CN103456831B/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6228662B1 (en) * | 1999-03-24 | 2001-05-08 | Kaneka Corporation | Method for removing short-circuited sections of a solar cell |
| CN101483204A (en) * | 2009-02-13 | 2009-07-15 | 苏州富能技术有限公司 | Thin-film solar cell module in series parallel connection structure and processing method thereof |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106533354A (en) * | 2016-12-05 | 2017-03-22 | 上海空间电源研究所 | Low-orbit solar cell circuit |
| CN106784101A (en) * | 2016-12-08 | 2017-05-31 | 上海空间电源研究所 | Discharge test part of low orbit |
| CN107681977A (en) * | 2017-07-05 | 2018-02-09 | 上海空间电源研究所 | Verify the in-orbit exposure test part of the low rail plasma environment guard technology of solar battery array |
| CN113114102A (en) * | 2021-03-18 | 2021-07-13 | 中国空间技术研究院 | Solar wing grounding circuit based on anti-static and fault isolation |
| CN113114102B (en) * | 2021-03-18 | 2022-05-24 | 中国空间技术研究院 | Solar wing grounding circuit based on anti-static and fault isolation |
| 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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| CN103456831B (en) | 2015-11-18 |
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