CN204359881U - ESD test device under electromagnetic impulse radiation environment - Google Patents
ESD test device under electromagnetic impulse radiation environment Download PDFInfo
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- CN204359881U CN204359881U CN201520014225.2U CN201520014225U CN204359881U CN 204359881 U CN204359881 U CN 204359881U CN 201520014225 U CN201520014225 U CN 201520014225U CN 204359881 U CN204359881 U CN 204359881U
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Abstract
The utility model discloses ESD test device under a kind of electromagnetic impulse radiation environment, relate to ESD test device field; Comprise electromagnetic radiation generating means, electromagnetic screen, vacuum plant and discharging detection device; Electromagnetic radiation generating means comprises electromagnetic radiation simulator, electric discharge rifle and coupling plate, and electric discharge rifle is connected with electromagnetic radiation simulator, coupling plate ground connection; Vacuum plant comprises vacuum pump and vacuum tube; Discharging detection device comprises spray point, ground connection flat board, power supply S1, oscillograph, current-limiting resistance R1, sample resistance R0 and electric capacity C1; Ground connection flat board and spray point are positioned at vacuum tube, oscillograph detects for the electric signal docked between ground flat board and spray point, electric discharge rifle and coupling plate are positioned at electromagnetic screen side, and vacuum tube is positioned at electromagnetic screen opposite side, have certain distance with electric discharge rifle and coupling plate.Under the utility model can carry out electromagnetic impulse radiation environment, electro static discharge characteristic is studied, and has better application prospect.
Description
Technical field
The utility model relates to ESD test device technique field.
Background technology
At space industry, spacecraft (as artificial satellite, space station etc.) is chronically exposed in space environment, and plasma environment and spacecraft surfacing interact, and makes spacecraft surface stored charge.Because the dielectric properties, geometric configuration etc. of spacecraft surfacing there are differences, cause between spacecraft surface, between surface and deep layer and between surface and spacecraft ground connection and there is electric potential difference.When electric potential difference reaches breakdown threshold, the static discharge such as corona, arc light will be there is, electric discharge can cause oxidation, corrosion equivalent damage to spacecraft surfacing, in addition, static discharge electromagnetic pulse is coupled into circuit by spacecraft cable, structure etc., cause electronic equipment to break down, threaten the safe operation of spacecraft.
When static discharge refers to that the field intensity around electrified body exceedes the insulation breakdown field intensity of surrounding medium, make because medium produces ionization the phenomenon that the electrostatic charge of electrified body partially or completely disappears.Affect a lot of because have of electro static discharge characteristic, as electrode structure, material behavior, surrounding environment etc.Due to the difference of material behavior, surface geometry, erosion degree, intensity of illumination and local plasma flux, material surface charging potential is different, and potential difference (PD) is low then tens volts, Gao Keda tens kilovolts.Electronegative potential sensitizing range does not reach breakdown threshold, and now interpolar electric field is more weak, and electron energy is lower, and collision makes molecule, atom is in metastable state, and impact ionization probability is lower, does not cause electric discharge.Charging potential upper zone generation static discharge, the strong electromagnetic pulse of generation is applied to electronegative potential sensitizing range, produces field intensity synergistic effect, and electromagnetic pulse excites metastable molecule, atomic ionization, produce dense plasma, set up ionization channels, bring out vacuum breakdown.This risk factor probably occurs in the exposed surface that solar battery array homalographic is comparatively large, complex structure, material category are many, causes the chain type electric discharge of spacecraft surface.
Therefore, carry out the influence research of electromagnetic impulse radiation to electro static discharge characteristic, can be research spacecraft electro static discharge characteristic and reference is provided, for guaranteeing that the safe operation of spacecraft is significant, in civilian and national defence, all there is good application prospect.
Utility model content
Technical problem to be solved in the utility model is to provide ESD test device under a kind of electromagnetic impulse radiation environment, can carry out electro static discharge characteristic research under electromagnetic impulse radiation environment; For electrostatic discharge protective engineer applied under spacecraft electromagnetic radiation environment with set up spacecraft electrostatic defending system and provide support, in civilian and national defence, all there is good application prospect.
For solving the problems of the technologies described above, technical solution adopted in the utility model is:
ESD test device under a kind of electromagnetic impulse radiation environment, comprises electromagnetic radiation generating means, electromagnetic screen, vacuum plant and discharging detection device;
Described electromagnetic radiation generating means comprises electromagnetic radiation simulator, electric discharge rifle and coupling plate, and described electric discharge rifle is connected with electromagnetic radiation simulator, described coupling plate ground connection;
The vacuum tube that described vacuum plant comprises vacuum pump and is connected with vacuum pump;
Described discharging detection device comprises spray point, ground connection flat board, power supply S1, oscillograph, current-limiting resistance R1, sample resistance R0 and electric capacity C1; Described current-limiting resistance R1 is connected with spray point, and spray point is connected with power supply S1 one end, the other end ground connection of described power supply S1; Described ground connection flat board is connected with sample resistance R0 one end, the other end ground connection of described sample resistance R0; Described electric capacity C1 is in parallel with power supply S1; Described spray point and ground connection flat board are positioned at vacuum tube; Described oscillographic high-voltage probe is connected between current-limiting resistance R1 and spray point, and oscillographic current probe is connected between sample resistance R0 and ground connection flat board;
Described electric discharge rifle and coupling plate are positioned at the side of electromagnetic screen; Described vacuum tube is positioned at the opposite side of electromagnetic screen, has certain distance with electric discharge rifle and coupling plate.
Further technical scheme, described electromagnetic radiation simulator is electrostatic discharge simulation device, and described electric discharge rifle is ESD gun.
Further technical scheme, the hollow housing of described electromagnetic screen to be inwall be absorbing material.
Further technical scheme, described absorbing material is for cutting sharp foam pyramid absorbing material.
Further technical scheme, is provided with vacuum meter between described vacuum pump and vacuum tube.
Further technical scheme, described power supply S1 is DC high-voltage power supply.
The beneficial effect adopting technique scheme to produce is: under the utility model can carry out electromagnetic impulse radiation environment, electro static discharge characteristic is studied, for research spacecraft electro static discharge characteristic provides reference, for guaranteeing that the safe operation of spacecraft is significant, in civilian and national defence, all there is good application prospect.Research spatial electromagnetic impulse radiation environment on the impact of spacecraft surface electrostatic flash-over characteristic, for electrostatic discharge protective engineer applied under spacecraft electromagnetic impulse radiation environment with set up spacecraft electrostatic defending system and provide support.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
In the accompanying drawings: 1, electromagnetic radiation simulator, 2, high pressure resistant cable, 3, electric discharge rifle, 4, electromagnetic screen, 5, vacuum tube, 6, spray point, 7, oscillograph, 8, high-voltage probe, 9, coupling plate, 10, high pressure resistant joint, 11, earthing cable, 12, regulate, 13, current probe, 14, ground connection is dull and stereotyped, and 15, vacuum meter, 16, regulate wire, 17, air valve door, 18, exhaust tube, 19, vacuum pump.
Embodiment
Below in conjunction with the drawings and specific embodiments, the utility model is described in further detail.
As shown in Figure 1, ESD test device under electromagnetic impulse radiation environment, comprises electromagnetic radiation generating means, electromagnetic screen 4, vacuum plant and discharging detection device.Electromagnetic radiation generating means comprises electromagnetic radiation simulator 1, electric discharge rifle 3 and coupling plate 9, and electric discharge rifle 3 is connected with electromagnetic radiation simulator 1, coupling plate 9 ground connection.Electromagnetic radiation simulator 1 is electrostatic discharge simulation device, and electric discharge rifle 3 is ESD gun.Electric discharge rifle 3 is connected with electromagnetic radiation simulator 1 by high pressure resistant cable 2 and the high pressure resistant joint 10 be positioned on electromagnetic screen 4, and coupling plate 9 is by high pressure resistant joint 10 and earthing cable 11 ground connection.Electromagnetic radiation simulator 1 can the old xerographic paper such as anthropomorphic phantom's type, human metalloproteinase model, machine mould and Charged Device Model, continuously adjustabe in-30kV ~ 30kV.High pressure resistant cable 2 is copper core polyvinyl chloride-insulated polyvinyl chloride cable, and withstand voltage scope is 1kV ~ 35kV.Electric discharge rifle 3 can produce the ESD normalized current meeting standard IEC 61000-4-2 and specify, namely the rise time is at 0.7ns ~ 1ns, and the withstand voltage scope of high pressure resistant joint 10 is-50kV ~ 50kV.
Vacuum plant comprises vacuum pump 19 and vacuum tube 5, and vacuum pump 19 is connected with vacuum tube 5 with air valve door 17 by exhaust tube 18.Be provided with vacuum meter 15 between vacuum pump 19 and vacuum tube 5, vacuum meter 15 by regulating wire 16, regulate 12 and be closely connected with air valve door 17, regulate 12 and be positioned on air valve door 17.Vacuum tube 5 internal diameter 0.22m, high 0.4m, by two pumping speed be the mechanical pump of 30L/min (vertical liter/min), the sputter ion pump of the lobe pump of a pumping speed 150L/min, two pumping speed to be the molecular pump of 1200L/min and two pumping speed be 1200L/min realizes the acquisition of vacuum, after starting middle control pump at different levels successively, the unloaded pressure of vacuum tube 5 can reach 10
-5pa.
Discharging detection device comprises spray point 6, ground connection flat board 14, power supply S1, oscillograph 7, current-limiting resistance R1, sample resistance R0 and electric capacity C1; Current-limiting resistance R1 is connected with spray point 6, and spray point 6 is connected with power supply S1 one end, the other end ground connection of power supply S1, and power supply S1 is DC high-voltage power supply.Ground connection dull and stereotyped 14 is connected with sample resistance R0 one end, the other end ground connection of sample resistance R0; Electric capacity C1 in parallel with power supply S1; Spray point 6 and ground connection flat board 14 are positioned at vacuum tube 5; The high-voltage probe 8 of oscillograph 7 is connected between current-limiting resistance R1 and spray point 6, and the current probe 13 of oscillograph 7 is connected between sample resistance R0 and ground connection flat board 14.Because power supply S1 is DC high-voltage power supply, the connecting line of a discharging detection device element is high pressure resistant cable 2, wherein, sample resistance R0 is connected with ground connection dull and stereotyped 14 and spray point 6 respectively by the high pressure resistant joint 10 be fixed on electromagnetic screen 4 with current-limiting resistance R1.After putting into spray point 6, ground connection dull and stereotyped 14 in vacuum tube 5, pressure can reach 10
-4pa.Compound vacuum gauge selected by vacuum meter 15, measurement range 10
5pa ~ 10
-6pa, be equipped with in Pirani gauge and ionization gauge two and regulate 12, reference mark load capacity AC220V/3A noninductive load, control accuracy ± 1%, the response time is less than 1s.Oscillograph 7 bandwidth is 8GHz, and sampling rate can reach 20GS/s.High-voltage probe 8 bandwidth 200MHz, test voltage scope-20kV ~ 20kV; Current-limiting resistance resistance 22.4M Ω; Electric capacity of voltage regulation 0.8nF, withstand voltage can reach 10kV.Current probe 13 bandwidth 25kHz ~ 1GHz, maximum current 12A; The long 40cm of coupling plate 9, wide 40 cm, thick 2 cm.Power supply S1 output voltage range-30kV ~ 30kV, minimum step 0.01kV.Sample resistance 12 is noninductive resistance, resistance 50 Ω.
Electric discharge rifle 3 and coupling plate 9 are positioned at the side of electromagnetic screen 4; Vacuum tube 5 is positioned at the opposite side of electromagnetic screen 4, has certain distance with electric discharge rifle 3 and coupling plate 9.High pressure resistant joint 10 is fixed on the housing of electromagnetic screen 4.The electromagnetic wave of electromagnetic screen 4 couples of frequency range 2GHz ~ 18GHz can absorb 30dB.Electromagnetic screen 4 for inwall be the hollow housing of absorbing material, for preventing outside electromagnetic interference.Absorbing material is for cutting sharp foam pyramid absorbing material, and model is SPT-220.
Operationally, utilize vacuum pump 19 that vacuum tube 5 internal gas pressure is evacuated to 10Pa ~ 4Pa, voltage is applied to spray point 6 by high pressure resistant cable 2, current-limiting resistance 9, high pressure resistant joint 10 to the utility model by power supply S1, and this voltage is lower than the threshold voltage under this condition; Electromagnetic radiation simulator 1 passes through high pressure resistant cable 2, high pressure resistant joint 10 by voltage-drop loading to electric discharge rifle 3, produce static discharge, the gas that electric discharge electromagnetic pulse is applied in vacuum tube 5 produces dense plasma, discharges between induced discharge pin 5 and ground connection flat board 14; Oscillograph 7 is by the voltage jump on high-voltage probe 8 detectability leakage resistance 9, oscillograph 7 detects the discharge current on sample resistance 12 by current probe 13, verifies that the static discharge electromagnetic pulse of discharging between rifle 3 and coupling plate 9 is brought out in vacuum tube 5 produce vacuum breakdown between spray point 6 and ground plate 14 with this.
Claims (6)
1. an ESD test device under electromagnetic impulse radiation environment, is characterized in that comprising electromagnetic radiation generating means, electromagnetic screen (4), vacuum plant and discharging detection device;
Described electromagnetic radiation generating means comprises electromagnetic radiation simulator (1), electric discharge rifle (3) and coupling plate (9), and described electric discharge rifle (3) is connected with electromagnetic radiation simulator (1), described coupling plate (9) ground connection;
The vacuum tube (5) that described vacuum plant comprises vacuum pump (19) and is connected with vacuum pump (19);
Described discharging detection device comprises spray point (6), ground connection flat board (14), power supply S1, oscillograph (7), current-limiting resistance R1, sample resistance R0 and electric capacity C1; Described current-limiting resistance R1 is connected with spray point (6), and spray point (6) is connected with power supply S1 one end, the other end ground connection of described power supply S1; Described ground connection flat board (14) is connected with sample resistance R0 one end, the other end ground connection of described sample resistance R0; Described electric capacity C1 is in parallel with power supply S1; Described spray point (6) and ground connection flat board (14) are positioned at vacuum tube (5); The high-voltage probe (8) of described oscillograph (7) is connected between current-limiting resistance R1 and spray point (6), and the current probe (13) of oscillograph (7) is connected between sample resistance R0 and ground connection flat board (14);
Described electric discharge rifle (3) and coupling plate (9) are positioned at the side of electromagnetic screen (4); Described vacuum tube (5) is positioned at the opposite side of electromagnetic screen (4), has certain distance with electric discharge rifle (3) and coupling plate (9).
2. ESD test device under electromagnetic impulse radiation environment according to claim 1, it is characterized in that described electromagnetic radiation simulator (1) is electrostatic discharge simulation device, described electric discharge rifle (3) is ESD gun.
3. ESD test device under electromagnetic impulse radiation environment according to claim 1, it is characterized in that described electromagnetic screen (4) for inwall be the hollow housing of absorbing material.
4. ESD test device under electromagnetic impulse radiation environment according to claim 3, is characterized in that described absorbing material is for cutting sharp foam pyramid absorbing material.
5. ESD test device under electromagnetic impulse radiation environment according to claim 1, is characterized in that being provided with vacuum meter (15) between described vacuum pump (19) and vacuum tube (5).
6. ESD test device under electromagnetic impulse radiation environment according to claim 1, is characterized in that described power supply S1 is DC high-voltage power supply.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520014225.2U CN204359881U (en) | 2015-01-09 | 2015-01-09 | ESD test device under electromagnetic impulse radiation environment |
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|---|---|---|---|
| CN201520014225.2U CN204359881U (en) | 2015-01-09 | 2015-01-09 | ESD test device under electromagnetic impulse radiation environment |
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| CN204359881U true CN204359881U (en) | 2015-05-27 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN107462753A (en) * | 2016-06-06 | 2017-12-12 | 上海北京大学微电子研究院 | The ultrahigh speed pulse generating device on the piece of ESD detections |
| CN108490225A (en) * | 2018-04-16 | 2018-09-04 | 北京铂帷检测服务有限公司 | A kind of coupling plate electrostatic discharge testing adaptive device and method |
| CN109018457A (en) * | 2018-07-31 | 2018-12-18 | 北京卫星环境工程研究所 | Spacecraft floating potential verification experimental verification method |
| CN109932607A (en) * | 2019-04-16 | 2019-06-25 | 中国人民解放军陆军工程大学 | Strong electromagnetic field induced electrostatic discharge test system in space radiation environment |
| CN110794428A (en) * | 2019-12-18 | 2020-02-14 | 中国人民解放军战略支援部队信息工程大学 | Equivalent substitution test system and method for ESD electromagnetic effect of unmanned aerial vehicle GPS module |
| CN112014660A (en) * | 2020-07-10 | 2020-12-01 | 西安交通大学 | Electromagnetic pulse excitation-based space equipment electrostatic discharge method and device |
| CN113612442A (en) * | 2021-06-28 | 2021-11-05 | 上海空间电源研究所 | Electromagnetic pulse injection solar cell test device |
| CN113702784A (en) * | 2021-08-30 | 2021-11-26 | 河北科技大学 | Electrostatic electromagnetic pulse induced needle-plate discharge experimental device |
-
2015
- 2015-01-09 CN CN201520014225.2U patent/CN204359881U/en not_active Expired - Fee Related
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN107462753A (en) * | 2016-06-06 | 2017-12-12 | 上海北京大学微电子研究院 | The ultrahigh speed pulse generating device on the piece of ESD detections |
| CN108490225A (en) * | 2018-04-16 | 2018-09-04 | 北京铂帷检测服务有限公司 | A kind of coupling plate electrostatic discharge testing adaptive device and method |
| CN108490225B (en) * | 2018-04-16 | 2024-03-26 | 北京铂帷检测服务有限公司 | Coupling plate electrostatic discharge test adapting device and method |
| CN109018457A (en) * | 2018-07-31 | 2018-12-18 | 北京卫星环境工程研究所 | Spacecraft floating potential verification experimental verification method |
| CN109932607B (en) * | 2019-04-16 | 2023-10-13 | 中国人民解放军陆军工程大学 | Space radiation environment strong electromagnetic field induced electrostatic discharge test system |
| CN109932607A (en) * | 2019-04-16 | 2019-06-25 | 中国人民解放军陆军工程大学 | Strong electromagnetic field induced electrostatic discharge test system in space radiation environment |
| CN110794428A (en) * | 2019-12-18 | 2020-02-14 | 中国人民解放军战略支援部队信息工程大学 | Equivalent substitution test system and method for ESD electromagnetic effect of unmanned aerial vehicle GPS module |
| CN112014660A (en) * | 2020-07-10 | 2020-12-01 | 西安交通大学 | Electromagnetic pulse excitation-based space equipment electrostatic discharge method and device |
| CN112014660B (en) * | 2020-07-10 | 2022-04-01 | 西安交通大学 | Electromagnetic pulse excitation-based space equipment electrostatic discharge method and device |
| CN113612442B (en) * | 2021-06-28 | 2023-02-28 | 上海空间电源研究所 | Electromagnetic pulse injection solar cell test device |
| CN113612442A (en) * | 2021-06-28 | 2021-11-05 | 上海空间电源研究所 | Electromagnetic pulse injection solar cell test device |
| CN113702784A (en) * | 2021-08-30 | 2021-11-26 | 河北科技大学 | Electrostatic electromagnetic pulse induced needle-plate discharge experimental device |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150527 Termination date: 20160109 |