CN103267910A - Device and method for utilizing plasma generated by electric propeller to induce charge-discharge effect - Google Patents
Device and method for utilizing plasma generated by electric propeller to induce charge-discharge effect Download PDFInfo
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- CN103267910A CN103267910A CN2013101453485A CN201310145348A CN103267910A CN 103267910 A CN103267910 A CN 103267910A CN 2013101453485 A CN2013101453485 A CN 2013101453485A CN 201310145348 A CN201310145348 A CN 201310145348A CN 103267910 A CN103267910 A CN 103267910A
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Abstract
The invention relates to a device and method for utilizing plasma generated by an electric propeller to induce the charge-discharge effect, and belongs to the field of testing. The device for utilizing the plasma generated by the electric propeller to induce the charge-discharge effect comprises an electronic gun, an ion engine, a neutralizer, a first non-contact surface potential probe, a first potentiometer, a discharge pulse test probe, an oscilloscope, a specimen stage, material samples, a vacuum-pumping system, an insulation pad, an insulation supporting frame, a second non-contact surface potential probe, a second potentiometer and a vacuum chamber. The method for utilizing the plasma generated by the electric propeller to induce the charge-discharge effect comprises the steps that a space electrification environment is simulated by electron and the plasma generated by the electronic gun and the electric propeller, charge accumulates on the surfaces of the material samples under comprehensive irradiation of the electron and the plasma, the surface electrification effect is generated, a non-contact surface potential tester is utilized to test potential of the material samples, a discharge pulse tester is utilized to obtain discharge pulses of the material samples, and therefore a test for utilizing the plasma generated by the electric propeller to induce the charge-discharge effect is achieved.
Description
Technical field
The present invention relates to a kind of electric propulsion and produce plasma and bring out the device and method that discharges and recharges effect, produce when being applicable to electric propulsion work that satellite discharges and recharges the effect analog test under plasma and the space natural plasma combined action, belong to field tests.
Background technology
During the ground magnetic substorm, geostationary orbit (GEO) meeting produce power causes GEO satellite surface charging to be up to more than ten thousand volts at the big flux plasma of 1～50keV scope, and the static discharge of generation is that satellites such as communication and meteorology produce cause faults.Along with China to satellite long-life high-performance growth of requirement, the electric propulsion technology will be used widely as a kind of high specific impulse, long-life, high efficiency space propultion technology.Can produce low temperature, highdensity plasma during thruster work, will with mechanisms such as the naturally occurring high-temperature in space, low-density plasma generation charge exchange, cause the charge and discharge process of satellite more complicated, simultaneously when electric propulsion system neutralizer operation irregularity, will cause the satellite structure current potential to raise rapidly, thereby influence satellite in the rail safe operation.
Document " Cai Zhenbo; the xenon ion engine is to the influence of GEO satellite surface charge/discharge effect; spacecraft environment engineering 22(5); 2005 " factors such as the xenon ion that ejects during only to the xenon ion engine operation on the GEO orbiter and electronics, space plasma, surfacing secondary electron light induced electron have carried out qualitative analysis to the influence of the surperficial charge and discharge process of GEO satellite, and have inquired into its designing requirement.Because domestic electric propulsion technology also is not applied at spacecraft, the domestic electric propulsion generation plasma that also do not form brings out the effect test method that discharges and recharges.
Summary of the invention
The invention provides a kind of electric propulsion generation plasma and bring out the device and method that discharges and recharges effect, comprehensive utilization electron gun and the charged environment of electric propulsion device virtual space, and material sample surface potential and discharge pulse monitored, produce the effect analog experiment that discharges and recharges that plasma brings out when being applicable to electric propulsion work.
For achieving the above object, technical scheme of the present invention is as follows:
A kind of electric propulsion produces plasma and brings out the device that discharges and recharges effect, and described device comprises electron gun, ion engine, neutralizer, the first contactless surface potential probe, first pot, discharge pulse test probe, oscillograph, sample platform, material sample, pumped vacuum systems, insulating mat, insulation bracing frame, the second contactless surface potential probe, second pot, vacuum chamber;
At internal vacuum chamber, electron gun is installed in the vacuum chamber top; Ion engine and neutralizer are formed electric propulsion system, are installed in the vacuum chamber top by the insulation bracing frame, thereby guarantee the insulation of electric propulsion system and vacuum chamber;
The sample platform is set in vacuum chamber bottom, described sample platform center and electron gun transmitting terminal over against; Material sample is positioned on the insulating mat of sample platform, keeps the insulation of material sample and sample platform;
Material sample lower surface metal-coated membrane, by lead with the metal film of material sample lower surface with after neutralizer is connected, be connected back ground connection with second pot with the vacuum chamber second contactless surface potential probe outward successively, material sample is connected with electric propulsion device ground; Preferred described metal film is the aluminium film;
The first contactless surface potential probe is positioned at the material sample top, and outer first pot, one end of vacuum chamber passes vacuum chamber and is connected other end ground connection with the first contactless surface potential probe;
The material sample upper surface is provided with lead, described lead one end is fixed on the material sample upper surface, the other end passes ground connection behind the vacuum chamber, be provided with the discharge pulse test probe at lead, oscillograph is connected with the discharge pulse test probe, and described discharge pulse test probe and oscillograph are positioned at the vacuum chamber outside;
In the vacuum chamber outside, pumped vacuum systems is connected with vacuum chamber;
A kind of electric propulsion produces plasma and brings out the effect test method that discharges and recharges, and described method concrete steps are as follows:
Preferred described electron gun ejected electron energy is 5～50keV, and beam current density is 1～10nA/cm
2
Step 2, unlatching first pot by first pot and the first contactless surface potential probe, are tested the surface potential of material sample;
Open oscillograph simultaneously, by discharge pulse test probe and oscillograph, obtain discharge pulse number of times and the waveform of material sample;
Preferred described oscillographic test bandwidth is 500MHz; First, second potentiometric test specification is-20～20KV;
The density of preferred described plasma is 10
15～10
17m
-3, the electron temperature that neutralizer produces is 10～50eV;
Step 4, by first pot and first contactless surface potential probe, and discharge pulse test probe and oscillograph, the surface potential of test material sample and discharge pulse again;
Step 5, close neutralizer, the plasma that the electric propulsion device produces during simulation neutralizer fault discharges and recharges effect, and records electric propulsion device structure current potential, the i.e. earth potential of satellite by the second contactless surface potential probe and second pot.
Beneficial effect
1) plasma environment that utilizes plasma that electronics that electron gun produces and ion engine and neutralizer produce to produce when the natural charged environment of virtual space and electric propulsion work respectively among the present invention is used the satellite that causes and is discharged and recharged environment thereby obtain electric propulsion system.
2) electric propulsion system is connected with the metal film ground of material sample lower surface, actual electric connection state during with this analog satellite work, and utilize surface potential tester monitoring electric propulsion structure current potential, obtain electric propulsion system under the neutralizer failure condition fills the generating effect to satellite influence with this.
3) utilize contactless surface potential tester and discharge pulse tester surface potential, discharge pulse and the structure current potential of test material sample respectively, thereby the plasma that obtains to produce when electric propulsion is worked brings out the means of testing that discharges and recharges effect test.
Description of drawings
Fig. 1 brings out the apparatus structure synoptic diagram that discharges and recharges effect for electric propulsion produces plasma;
Among the figure: 1-electron gun, 2-ion engine, 3-neutralizer, the 4-first contactless surface potential probe, 5-first pot, 6-discharge pulse test probe, 7-oscillograph, 8-sample platform, 9-material sample, 10-pumped vacuum systems, 11-insulating mat, 12-insulation bracing frame, the 13-second contactless surface potential probe, 14-second pot, 15-vacuum chamber.
Embodiment
By shown in Figure 1, electric propulsion generation plasma brings out and discharges and recharges electronics and the computer simulated plasma that the charged environment in space is produced by electron gun and electric propulsion device in the effect test, utilize contactless surface potential tester test material sample surfaces current potential, the discharge pulse test is the discharge pulse that instrument obtains material sample, and its embodiment is as follows:
A kind of electric propulsion produces plasma and brings out the device that discharges and recharges effect, and described device comprises electron gun 1, ion engine 2, neutralizer 3, first contactless surface potential probe 4, first pot 5, discharge pulse test probe 6, oscillograph 7, sample platform 8, material sample 9, pumped vacuum systems 10, insulating mat 11, insulation bracing frame 12, second contactless surface potential probe 13, second pot 14, vacuum chamber 15;
In vacuum chamber 15 inside, electron gun 1 is installed in vacuum chamber 15 tops; Ion engine 2 and neutralizer 3 are formed electric propulsion system, are installed in vacuum chamber 15 tops by insulation bracing frame 12, thereby guarantee the insulation of electric propulsion system and vacuum chamber 15;
In vacuum chamber 15 bottoms sample platform 8 is set, described sample platform 8 centers and electron gun 1 transmitting terminal over against; Material sample 9 is positioned on the insulating mat 11 of sample platform 8, keeps the insulation of material sample 9 and sample platform 8;
The first contactless surface potential probe 4 is positioned at material sample 9 tops, and vacuum chamber 15 outer first pot, 5 one ends pass vacuum chamber 15 and are connected other end ground connection with the first contactless surface potential probe 4;
In vacuum chamber 15 outsides, pumped vacuum systems 10 is connected with vacuum chamber 15;
A kind of electric propulsion produces plasma and brings out the effect test method that discharges and recharges, and described method concrete steps are as follows:
Step 2, unlatching first pot 5 by first pot 5 and the first contactless surface potential probe 4, are tested the surface potential of material sample 9;
Open oscillograph 7 simultaneously, by discharge pulse test probe 6 and oscillograph 7, obtain discharge pulse number of times and the waveform of material sample 9;
Wherein, the test bandwidth of described oscillograph 7 is 500MHz; First, second pot 5,14 test specification are-20～20KV;
The density of described plasma is 10
13m
-3, the electron temperature that neutralizer 3 produces is 15eV;
Step 4, by first pot 5 and first contactless surface potential probe 4, and discharge pulse test probe 6 and oscillograph 7, the surface potential of test material sample 9 and discharge pulse again;
Step 5, close neutralizer 3, the plasma that the electric propulsion device produces during simulation neutralizer 3 faults discharges and recharges effect, and records electric propulsion device structure current potential, the i.e. earth potential of satellite by second contactless surface potential probe 13 and second pot 14;
Analysis-by-synthesis electric propulsion device is not worked (corresponding step 2), is worked (corresponding step 3, four) and the test result of material sample 9 surface potentials, discharge pulse and structure current potential during neutralizer fault (corresponding step 5), and the plasma that produces when finishing electric propulsion work brings out and discharges and recharges the effect testing experiment.
In the described method, electronics and computer simulated plasma that the spatial charging environment is produced by electron gun 1 and electric propulsion device, under electronics and the comprehensive irradiation of plasma, material sample 9 surfaces are with stored charge, produce the surface charging effect, and utilizing contactless surface potential tester test material sample 9 current potentials, the discharge pulse test is the discharge pulse that instrument obtains material sample 9, produces plasma and brings out and discharge and recharge effect test thereby finish electric propulsion.
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 (5)
1. an electric propulsion generation plasma brings out the device that discharges and recharges effect, it is characterized in that: described device comprises electron gun (1), ion engine (2), neutralizer (3), first contactless surface potential probe (4), first pot (5), discharge pulse test probe (6), oscillograph (7), sample platform (8), material sample (9), pumped vacuum systems (10), insulating mat (11), insulation bracing frame (12), second contactless surface potential probe (13), second pot (14), vacuum chamber (15);
In vacuum chamber (15) inside, electron gun (1) is installed in vacuum chamber (15) top; Ion engine (2) and neutralizer (3) are formed electric propulsion system, are installed in vacuum chamber (15) top by insulation bracing frame (12);
Sample platform (8) is set in vacuum chamber (15) bottom, described sample platform (8) center and electron gun (1) transmitting terminal over against; Material sample (9) is positioned on the insulating mat (11) of sample platform (8);
Material sample (9) lower surface metal-plated membrane, by lead with the metal film of material sample (9) lower surface with after neutralizer (3) is connected, be connected ground connection afterwards with second pot (14) with the outer second contactless surface potential probe (13) of vacuum chamber (15) successively;
The first contactless surface potential probe (4) is positioned at material sample (9) top, and outer first pot (5) one ends of vacuum chamber (15) pass vacuum chamber (15) and are connected other end ground connection with the first contactless surface potential probe (4);
Material sample (9) upper surface is provided with lead, described lead one end is fixed on material sample (9) upper surface, the other end passes vacuum chamber (15) back ground connection, be provided with discharge pulse test probe (6) at lead, oscillograph (7) is connected with discharge pulse test probe (6), and described discharge pulse test probe (6) and oscillograph (7) are positioned at vacuum chamber (15) outside;
In vacuum chamber (15) outside, pumped vacuum systems (10) is connected with vacuum chamber (15).
2. an electric propulsion generation plasma brings out and discharges and recharges the effect test method, and it is characterized in that: described method is used device as claimed in claim 1, and concrete steps are as follows:
Step 1, use pumped vacuum systems (10) vacuumize vacuum chamber (15), make vacuum tightness≤10
-4Pa, and unlocking electronic rifle (1) produce electron irradiation material sample (9);
Step 2, unlatching first pot (5) by first pot (5) and the first contactless surface potential probe (4), are tested the surface potential of material sample (9);
Open oscillograph (7) simultaneously, by discharge pulse test probe (6) and oscillograph (7), obtain discharge pulse number of times and the waveform of material sample (9);
Step 3, open the electric propulsion device, the plasma that makes its generation irradiation material sample (9) during with the electron synchrotron of electron gun (1) generation;
Step 4, pop one's head in (4) by first pot (5) and the first contactless surface potential, and discharge pulse test probe (6) and oscillograph (7), surface potential and the discharge pulse of test material sample (9) again;
Step 5, close neutralizer (3), the plasma that the electric propulsion device produces during simulation neutralizer (3) fault discharges and recharges effect, and pops one's head in (13) and second pot (14) records the structure current potential of electric propulsion device by the second contactless surface potential.
3. a kind of electric propulsion generation plasma according to claim 2 brings out and discharges and recharges the effect test method, and it is characterized in that: in the step 1, described electron gun (1) ejected electron energy is 5～50keV, and beam current density is 1～10nA/cm
2
4. a kind of electric propulsion generation plasma according to claim 2 brings out and discharges and recharges the effect test method, and it is characterized in that: in the step 2, the test bandwidth of described oscillograph (7) is 500MHz; The test specification of first, second pot (5,14) is-20～20KV.
5. a kind of electric propulsion generation plasma according to claim 2 brings out and discharges and recharges the effect test method, and it is characterized in that: in the step 3, the density of described plasma is 10
15～10
17m
-3, the electron temperature that neutralizer (3) produces is 10～50eV.
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Cited By (8)
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| CN103760432A (en) * | 2013-12-20 | 2014-04-30 | 兰州空间技术物理研究所 | Polar orbit satellite bus power cable secondary discharge ground simulation test system and method |
| CN103760887A (en) * | 2013-12-24 | 2014-04-30 | 兰州空间技术物理研究所 | Verification test device and method of spacecraft structural potential active control 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 |
| CN106680612A (en) * | 2015-11-11 | 2017-05-17 | 北京卫星环境工程研究所 | Performance test device for emitter of field emission electric thruster of satellite |
| CN107657079A (en) * | 2017-08-29 | 2018-02-02 | 兰州空间技术物理研究所 | A kind of satellite charged effect induced malfunction and environments match analysis method |
| CN109142924A (en) * | 2015-10-01 | 2019-01-04 | 景祝强 | A kind of charge and discharge analogy method induced based on electronics |
| CN109752401A (en) * | 2019-01-16 | 2019-05-14 | 清华大学 | Increasing material manufacturing device and method with real-time in-situ detection function |
| CN112149340A (en) * | 2020-09-11 | 2020-12-29 | 兰州空间技术物理研究所 | Satellite surface charging potential calculation method combining PIC and charging current fitting |
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| CN103760432A (en) * | 2013-12-20 | 2014-04-30 | 兰州空间技术物理研究所 | Polar orbit satellite bus power cable secondary discharge ground simulation test system and method |
| CN103760432B (en) * | 2013-12-20 | 2016-09-28 | 兰州空间技术物理研究所 | Polar-orbiting satellite bus feed cable secondary discharge injection ground simulation test system and method |
| CN103760887A (en) * | 2013-12-24 | 2014-04-30 | 兰州空间技术物理研究所 | Verification test device and method of spacecraft structural potential active control device |
| CN103760887B (en) * | 2013-12-24 | 2016-07-20 | 兰州空间技术物理研究所 | The checking assay device of spacecraft structural potential active control device and method |
| 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 |
| CN109142924A (en) * | 2015-10-01 | 2019-01-04 | 景祝强 | A kind of charge and discharge analogy method induced based on electronics |
| CN106680612A (en) * | 2015-11-11 | 2017-05-17 | 北京卫星环境工程研究所 | Performance test device for emitter of field emission electric thruster of satellite |
| CN106680612B (en) * | 2015-11-11 | 2019-08-06 | 北京卫星环境工程研究所 | The performance testing device of satellite field emission electric thruster emitter |
| CN107657079A (en) * | 2017-08-29 | 2018-02-02 | 兰州空间技术物理研究所 | A kind of satellite charged effect induced malfunction and environments match analysis method |
| CN109752401A (en) * | 2019-01-16 | 2019-05-14 | 清华大学 | Increasing material manufacturing device and method with real-time in-situ detection function |
| CN112149340A (en) * | 2020-09-11 | 2020-12-29 | 兰州空间技术物理研究所 | Satellite surface charging potential calculation method combining PIC and charging current fitting |
| CN112149340B (en) * | 2020-09-11 | 2023-02-24 | 兰州空间技术物理研究所 | Satellite surface charging potential calculation method combining PIC and charging current fitting |
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