CN103267903A - Device and method for measuring satellite material surface electrostatic discharge pulse characteristics - Google Patents
Device and method for measuring satellite material surface electrostatic discharge pulse characteristics Download PDFInfo
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- CN103267903A CN103267903A CN201310145701XA CN201310145701A CN103267903A CN 103267903 A CN103267903 A CN 103267903A CN 201310145701X A CN201310145701X A CN 201310145701XA CN 201310145701 A CN201310145701 A CN 201310145701A CN 103267903 A CN103267903 A CN 103267903A
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Abstract
The invention relates to a device and a method for measuring satellite material surface electrostatic discharge pulse characteristics in the space plasma environment, and belongs to the field of measurement. The device comprises an electronic gun, a vacuum chamber, a vacuum pumping system, a grounded metal board, a reference pulse signal receiving antenna, arrayed pulse signal receiving antennas and a spectrometer. The method comprises the steps of placing satellite surface material samples into the vacuum chamber, start the vacuum pumping system, starting the electronic gun, regulating acceleration voltage and filament current of the electronic gun, conducting real-time monitoring on beams of the electronic gun by means of a Faraday cup, starting the spectrometer, respectively measuring frequency domains of discharge signals of the pulse signal receiving antennas of different positions, and conducting real-time monitoring on space distribution of discharge pulse radiation electromagnetic fields in an experiment process. An arc structure at the tail end of the grounded metal board resolves the problem of edge reflection of the radiation fields, and measurement of the space distribution of the radiation fields is conducted through the antennas.
Description
Technical field
The present invention relates to a kind ofly in the space plasma environment, measurement mechanism and the method for satellite material surface electrostatic discharge pulses characteristic belong to field tests.
Background technology
Satellite in orbit during because surface charging will take place the interaction of its surfacing and paripheral zone electrochondria subenvironment, the Induced by Space Electrostatic Discharges of charged generation (SESD) can cause serious satellite failure.Foreign statistic shows, the satellite failure that is caused by Induced by Space Electrostatic Discharges more than 50% of environmental bug that takes up space.At geostationary orbit, when satellite met with ground magnetic substorm environment, non-equilibrium plasma can make the satellite surface charge to more than ten thousand volts, and the static discharge of generation is to cause the telstar cause faults.In SSO (Sun Synchronous Orbit), polar region aurora sedimentation electronic beam current reaches as high as 100 times of geostationary orbit, and flux is about 30nA/cm
2, will produce the current potential of thousands of volts at large-scale satellite and parts afterbody thereof, simultaneously because charging capacitor is big, and discharge energy is also big, the static discharge of generation with serious threat satellite electron system in rail safety.
Present stage, carried out the test that a large amount of dielectric material surfaces discharges and recharges both at home and abroad, obtained discharge current pulse.But mostly the measuring method that adopts is the method by sample resistance, and this method of testing can not be measured the radiation field of discharge pulse, can not reflect that radiation field is to the interference of satellite.Therefore, set up a kind of test unit that effectively can measure the discharge pulse radiation field and method to carrying out the satellite table face and discharge and recharge research and the protection design being significant.
Summary of the invention
The measurement mechanism and the method that the purpose of this invention is to provide a kind of satellite material surface electrostatic discharge pulses characteristic mainly are charging environment, electromagnetic pulse communication environments and the measurement problems that solves the satellite table flooring.
For achieving the above object, technical scheme of the present invention is as follows;
A kind of measurement mechanism of satellite material surface electrostatic discharge pulses characteristic, described device comprises electron gun, vacuum chamber, vacuum-pumping system, grounding plate, reference burst signal receiving antenna, the pulsed signal antenna of array, frequency spectrograph;
Wherein, electron gun is installed in the vacuum chamber top, and satellite table flooring sample is placed in internal vacuum chamber by insulating support, electron gun transmitting terminal and satellite table flooring sample center over against;
Outside vacuum chamber, fit in grounding plate and vacuum chamber bottom, and the one end is concordant with the vacuum chamber edge, the outside horizontal-extending of the other end, and be bent downwardly camber in the end; With described grounded metal plate earthing;
According to from vacuum chamber position from the close-by examples to those far off, partly punch at the horizontal-extending of grounding plate, the reference burst signal receiving antenna is installed in the hole nearest from vacuum chamber, the pulsed signal antenna of one or more array is installed in all the other holes; The number in hole equates with the sum that fixes up an aerial wire;
The upper end of receiving antenna is receiving end, is positioned at the top of grounding plate; The lower end of receiving antenna is passed grounding plate and is connected with frequency spectrograph respectively, and described frequency spectrograph also is connected with satellite table flooring sample;
Vacuum-pumping system is connected with vacuum chamber;
A preferred described grounding plate outwards horizontally extending end bends to semicircular arc, and radius-of-curvature is 15.24cm;
Pulsed signal antenna the selection of material dipole antenna and the tours antenna of preferred reference burst signal receiving antenna and array, wherein dipole antenna is used for measuring electric field, and tours antenna is used for measuring magnetic field.
Preferably on grounding plate, the distance between adjacent two signal receiving antennas is 30cm.
In order to prevent the effect that discharges and recharges of vacuum chamber inside surface, preferred described vacuum chamber adopts tempered glass, and at tempered glass inner-wall spraying charcoal;
Preferably be provided with Faraday cup above satellite table flooring sample, described Faraday cup is connected by the outer galvanometer of lead and vacuum chamber, and electron gun ejected electron line is monitored in real time;
A kind of measuring method of satellite material surface electrostatic discharge pulses characteristic, described method step is as follows;
Beneficial effect
1. the invention provides a kind of measurement mechanism and method of satellite material surface electrostatic discharge pulses characteristic, the beam current density that the energy electron gun produced during described method adopted is 1～20nA/cm
2, energy is the electronic beam current of 1～50keV, comes analog satellite surface charging space electronic environment.
Described method can the analog satellite surfacing in the simulation of discharge electromagnetic pulse communication environments, be specially the vacuum chamber that adopts fiberglass, can make inner electromagnetic pulse signal propagate out, and at the inner-wall spraying charcoal of fiberglass vacuum chamber, prevent that internal vacuum chamber from discharging and recharging and cause interference.Place the grounding plate that an end is circular arc in the bottom of vacuum chamber, therefore transient field circulation way on grounding plate of surface electrostatic discharge generation just can be simulated discharge pulse in the propagation on satellite surface, and the camber structure of grounding plate end has been eliminated the edge reflection problem of radiation field.
3. on grounding plate, the radiation field of discharge pulse is measured antenna and is adopted electrical dipole antenna and tours antenna respectively, and wherein dipole antenna is used for measuring electric field, and tours antenna is used for measuring magnetic field, and with its installation successively on grounding plate, can carry out the radiation field space distribution and measure.
Description of drawings
Fig. 1 is the test unit structural representation of satellite material surface electrostatic discharge pulses characteristic;
Fig. 2 is from vacuum chamber 60cm place discharge radiated electric field test pattern among the embodiment;
Among the figure: 1-electron gun, 2-vacuum chamber, 3-vacuum-pumping system, 4-satellite table flooring sample, 5-grounding plate, 6-reference burst signal receiving antenna, the pulsed signal antenna of 7-array, 8-frequency spectrograph.
Embodiment
Below by embodiment, the invention will be further described.
The measurement mechanism of a kind of satellite material surface electrostatic discharge pulses characteristic as shown in Figure 1, described device comprises pulsed signal antenna 7, the frequency spectrograph 8 of electron gun 1, vacuum chamber 2, vacuum-pumping system 3, grounding plate 5, reference burst signal receiving antenna 6, array;
Wherein, electron gun 1 is installed in vacuum chamber 2 tops, and satellite table flooring sample 4 is placed in vacuum chamber 2 inside by insulating support, electron gun 1 transmitting terminal and satellite table flooring sample 4 centers over against;
Outside vacuum chamber 2, grounding plate 5 is fitted with vacuum chamber 2 bottoms, and the one end is concordant with vacuum chamber 2 edges, the outside horizontal-extending of the other end, and be bent downwardly camber in the end; With described grounding plate 5 ground connection;
According to from vacuum chamber 2 position from the close-by examples to those far off, horizontal-extending at grounding plate 5 partly punches, reference burst signal receiving antenna 6 is installed in the hole nearest from vacuum chamber 2, the pulsed signal antenna 7 of one or more array is installed in all the other holes; The number in hole equates with the sum that fixes up an aerial wire;
Receiving antenna 6,7 upper end are receiving end, are positioned at the top of grounding plate 5; Receiving antenna 6,7 lower end are passed grounding plate 5 and are connected with frequency spectrograph 8 respectively, and described frequency spectrograph 8 also is connected with satellite table flooring sample 4;
The pulsed signal antenna 7 of satellite table flooring sample 4, reference burst signal receiving antenna 6, array is connected with vacuum chamber 2 frequency spectrograph 8 outward respectively;
Vacuum-pumping system 3 is connected with vacuum chamber 2;
Described grounding plate 5 outside horizontally extending ends bend to semicircular arc, and radius-of-curvature is 15.24cm; Sheet metal is the copper coin of size 50cm * 180cm.
Pulsed signal antenna 7 the selection of material dipole antenna and the tours antennas of reference burst signal receiving antenna 6 and array, wherein dipole antenna is used for measuring electric field, and tours antenna is used for measuring magnetic field.Pulsed signal antenna 7 is 4 groups, and every group comprises a material dipole antenna and a tours antenna, and first pulsed signal antenna is installed in from vacuum chamber 30cm place, and the distance between every two adjacent groups antenna is 30cm.
In order to prevent the effect that discharges and recharges of vacuum chamber 2 inside surfaces, preferred described vacuum chamber 2 adopts tempered glass, and at tempered glass inner-wall spraying charcoal; Vacuum chamber is of a size of Φ 1.0 * 1.5m.
Be provided with Faraday cup above satellite table flooring sample 4, described Faraday cup is connected by the outer galvanometer of lead and vacuum chamber, and electron gun ejected electron line is monitored in real time;
A kind of measuring method of satellite material surface electrostatic discharge pulses characteristic, described method step is as follows;
After test is finished, regulate the electron gun parameter or change satellite table flooring, repeating step one to three.
Fig. 2 is that wherein horizontal ordinate is frequency from vacuum chamber 60cm place discharge radiated electric field test pattern, and ordinate is electric field intensity, illustrates that this device can be used for the detection of electric field.
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. the measurement mechanism of a satellite material surface electrostatic discharge pulses characteristic, it is characterized in that: described device comprises pulsed signal antenna (7), the frequency spectrograph (8) of electron gun (1), vacuum chamber (2), vacuum-pumping system (3), grounding plate (5), reference burst signal receiving antenna (6), array;
Wherein, electron gun (1) is installed in vacuum chamber (2) top, and satellite table flooring sample (4) is placed in vacuum chamber (2) inside by insulating support, electron gun (1) transmitting terminal and satellite table flooring sample (4) center over against;
Outside vacuum chamber (2), fit in grounding plate (5) and vacuum chamber (2) bottom, and the one end is concordant with vacuum chamber (2) edge, the outside horizontal-extending of the other end, and be bent downwardly camber in the end; With described grounding plate (5) ground connection;
According to from vacuum chamber (2) position from the close-by examples to those far off, horizontal-extending at grounding plate (5) partly punches, reference burst signal receiving antenna (6) is being installed in the nearest hole of vacuum chamber (2), the pulsed signal antenna (7) of one or more array is being installed in all the other holes; The number in hole equates with the sum that fixes up an aerial wire;
The upper end of receiving antenna (6,7) is receiving end, is positioned at the top of grounding plate (5); The lower end of receiving antenna (6,7) is passed grounding plate (5) and is connected with frequency spectrograph (8) respectively, and described frequency spectrograph (8) also is connected with satellite table flooring sample (4);
Vacuum-pumping system (3) is connected with vacuum chamber (2).
2. the measurement mechanism of a kind of satellite material surface electrostatic discharge pulses characteristic according to claim 1 is characterized in that: described grounding plate (a 5) outwards horizontally extending end bends to semicircular arc, and radius-of-curvature is 15.24cm.
3. the measurement mechanism of a kind of satellite material surface electrostatic discharge pulses characteristic according to claim 1 is characterized in that: pulsed signal antenna (7) the selection of material dipole antenna and the tours antenna of reference burst signal receiving antenna (6) and array.
4. the measurement mechanism of a kind of satellite material surface electrostatic discharge pulses characteristic according to claim 1, it is characterized in that: on grounding plate (5), the distance between adjacent two signal receiving antennas is 30cm.
5. the measurement mechanism of a kind of satellite material surface electrostatic discharge pulses characteristic according to claim 1 is characterized in that: described vacuum chamber (2) adopts tempered glass, and at tempered glass inner-wall spraying charcoal.
6. the measurement mechanism of a kind of satellite material surface electrostatic discharge pulses characteristic according to claim 1, it is characterized in that: be provided with Faraday cup in satellite table flooring sample (4) top, described Faraday cup is connected by the outer galvanometer of lead and vacuum chamber (2), and electron gun (1) ejected electron line is monitored in real time.
7. the measuring method of a satellite material surface electrostatic discharge pulses characteristic, it is characterized in that: described method is used the measurement mechanism of a kind of satellite material surface electrostatic discharge pulses characteristic as claimed in claim 1, and step is as follows:
Step 1, satellite table flooring sample (4) is placed in the vacuum chamber (2), opens vacuum-pumping system (3) to vacuum tightness and drop to 1.0 * 10
-3Below the Pa;
Step 2, open electron gun (1), transfer accelerating potential and the filament current of electron gun (1), make the control of electron energy and beam current density at 1～50keV and 1～20nA/cm
2
Step 3, open frequency spectrograph (8), measure the frequency domain of the pulsed signal antenna discharge signal of diverse location respectively, the discharge pulse radiation field space distribution in the process of the test is monitored in real time.
8. the measuring method of a kind of satellite material surface electrostatic discharge pulses characteristic according to claim 7 is characterized in that: in step 2, utilize Faraday cup that electron gun (1) line is monitored in real time.
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| CN201310145701XA CN103267903A (en) | 2013-04-24 | 2013-04-24 | Device and method for measuring satellite material surface electrostatic discharge pulse characteristics |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103760393A (en) * | 2013-12-24 | 2014-04-30 | 兰州空间技术物理研究所 | Method and system for monitoring discharge pulse of satellite charge-and-discharge effect |
| CN104360177A (en) * | 2014-11-19 | 2015-02-18 | 中国人民解放军军械工程学院 | Dielectric material low-pressure environment surface electrification 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 |
| CN105242126A (en) * | 2014-07-07 | 2016-01-13 | 中国科学院空间科学与应用研究中心 | High-orbit satellite electrostatic discharge monitoring device |
| 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 |
| CN111044805A (en) * | 2019-12-27 | 2020-04-21 | 中国航空工业集团公司西安飞机设计研究所 | Electrostatic discharge radio frequency noise test 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 |
| CN113163564A (en) * | 2021-04-30 | 2021-07-23 | 中国科学院电工研究所 | Electron beam processing device with static elimination function |
| CN114047229A (en) * | 2021-11-11 | 2022-02-15 | 全球能源互联网研究院有限公司 | Polymer film medium charge transport microscopic parameter extraction device and method |
| CN114509652B (en) * | 2022-04-19 | 2022-06-21 | 合肥航太电物理技术有限公司 | Device and method for testing radio frequency discharge noise of aircraft electrostatic discharger |
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Cited By (14)
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| CN103760393A (en) * | 2013-12-24 | 2014-04-30 | 兰州空间技术物理研究所 | Method and system for monitoring discharge pulse of satellite charge-and-discharge effect |
| CN105242126B (en) * | 2014-07-07 | 2018-08-07 | 中国科学院空间科学与应用研究中心 | A kind of high orbit satellite static discharge monitoring device |
| CN105242126A (en) * | 2014-07-07 | 2016-01-13 | 中国科学院空间科学与应用研究中心 | High-orbit satellite electrostatic discharge monitoring device |
| CN104360177B (en) * | 2014-11-19 | 2015-12-09 | 中国人民解放军军械工程学院 | Dielectric material hypobaric surface band electrical testing system |
| CN104360177A (en) * | 2014-11-19 | 2015-02-18 | 中国人民解放军军械工程学院 | Dielectric material low-pressure environment surface electrification testing system |
| 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 |
| 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 |
| CN111044805A (en) * | 2019-12-27 | 2020-04-21 | 中国航空工业集团公司西安飞机设计研究所 | Electrostatic discharge radio frequency noise test method |
| CN111044805B (en) * | 2019-12-27 | 2021-12-24 | 中国航空工业集团公司西安飞机设计研究所 | Electrostatic discharge radio frequency noise test 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 |
| 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 |
| CN113163564A (en) * | 2021-04-30 | 2021-07-23 | 中国科学院电工研究所 | Electron beam processing device with static elimination function |
| CN114047229A (en) * | 2021-11-11 | 2022-02-15 | 全球能源互联网研究院有限公司 | Polymer film medium charge transport microscopic parameter extraction device and method |
| CN114509652B (en) * | 2022-04-19 | 2022-06-21 | 合肥航太电物理技术有限公司 | Device and method for testing radio frequency discharge noise of aircraft electrostatic discharger |
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Application publication date: 20130828 |