CN103604979A - Detector based on capacitor voltage distribution and detecting method thereof - Google Patents
Detector based on capacitor voltage distribution and detecting method thereof Download PDFInfo
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- CN103604979A CN103604979A CN201310631637.6A CN201310631637A CN103604979A CN 103604979 A CN103604979 A CN 103604979A CN 201310631637 A CN201310631637 A CN 201310631637A CN 103604979 A CN103604979 A CN 103604979A
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Abstract
The invention relates to a detector based on capacitor voltage distribution and a detecting method thereof. The detector comprises an electric conducting measurement electrode and an insulation thin film adhered to the electric conducting measurement electrode, the electric conducting measurement electrode is connected with a spacecraft structure through a measurement capacitor, measurement is conducted through a voltage measurement circuit, a compensating electrode is arranged on the periphery of the electric conducting measurement electrode and is isolated from the electric conducting measurement electrode. The detector based on capacitor voltage distribution does not need a complex long extending rod mechanism, a voltage scanning circuit and a voltage current curve processing procedure, and a suspension level value can be directly obtained. The detector is simple in design and high in reliability.
Description
Technical field
The invention belongs to space environment detection application technical field, be specifically related to a kind of detector and detection method thereof based on capacitance partial pressure.
Background technology
Spacecraft can produce interaction with space plasma in space environment, because velocity of electrons is faster than ion, so the charging potential of spacecraft is mainly negative potential.Spacecraft is because the charging effect of space plasma causes the generation of static discharge, and the reason that causes static discharge is because charging rate and the equilibrium potential of spacecraft structure conductor are different from charging rate and the equilibrium potential of spacecraft surface dielectric material, thereby cause inequality charging.For guarantee to spacecraft in-orbit static discharge effect carry out ACTIVE CONTROL, just need to have corresponding detection means.
At present the detection means to spacecraft floating potential is mainly used on scientific satellite, adopts and on long boom, places probe realization.Probe can adopt Langmuir probe, space electric field probe, several modes of emitting probe, realizes the object of surveying spacecraft floating potential.Wherein, Langmuir probe adopts the scanning voltage being carried on probe to obtain the curve of collected current, and obtains floating potential according to corresponding theory model; Space electric field probe is for measurement space current potential, and the distance of popping one's head according to boom diverse location acquisition electric field, also can be used for analyzing current potential that spacecraft is with; Emitting probe passes through heated filament electron emission, and regulates the potential difference (PD) of probe space environment, and when regulated value reaches after floating potential, its collected current can produce saltus step due to the effect of thermionic emission, thereby obtains floating potential.Above-mentioned these technology have several common ground, first all need long boom, make it to spacecraft, have certain requirement, secondly above-mentioned several method all adopts the means such as voltage scanning and indirect measurement, design is comparatively complicated, realizes corresponding means tool and acquire a certain degree of difficulty under the high reliability request in Practical Project.In addition, because Instrument Design is complicated, its weight and power consumption are also larger.For this reason, provide a kind of spacecraft floating potential detection method simple in structure, easy to use, lightweight and that power consumption is little very necessary.
Summary of the invention
The present invention is directed to above-mentioned technical barrier, utilize capacitance partial pressure method, and conductor and the medium principle of equilibrium establishment process in plasma environment respectively, a kind of detector and detection method thereof based on capacitance partial pressure proposed, simplicity of design of the present invention, can directly measure floating potential, simultaneously to boom without high requirement, can adopt shorter boom to realize.
For reaching above object, the technical solution used in the present invention is:
A kind of detector based on capacitance partial pressure, comprise conduction potential electrode and paste insulation film thereon, between conduction potential electrode and spacecraft structure ground, with measurement electric capacity, be connected, and measure by tension measuring circuit, compensating electrode is arranged in conduction potential electrode periphery and isolates with conduction potential electrode.
Further, described compensating electrode by protective resistance and bias voltage source and spacecraft structure be connected.
A kind of method that adopts described detector to carry out floating potential detection, equivalent capacity and measurement electric capacity by insulation film form capacitance partial pressure network, adjust the on-off circuit of measuring in electric capacity and control its capacitance, and utilize tension measuring circuit to obtain two groups of corresponding voltage measuring values, by capacitance and the measuring voltage value of known measurement electric capacity, can determine the equivalent capacity that draws insulation film, according to capacitance and the measuring voltage value of the value of the equivalent capacity of insulation film, measurement electric capacity, determine floating potential value.
Further, adopt at set intervals two groups of different measurement capacitances of switching over to calibrate the measured value of insulation film equivalent capacity, and obtain floating potential value with this value and definite, immovable measurement electric capacity.
Detector and detection method thereof based on capacitance partial pressure of the present invention, does not need complicated long boom mechanism, voltage scanning circuit and voltage-current curve handling procedure, directly can obtain floating potential value, simplicity of design, and reliability is high.
Accompanying drawing explanation
Fig. 1 is that detector of the present invention forms schematic diagram.
Fig. 2 is the equivalent schematic diagram that floating potential is surveyed.
Wherein, 1, insulation film; 2, conduction potential electrode; 3, compensating electrode; 4, measure electric capacity; 5, tension measuring circuit; 6, bias voltage source; 7, spacecraft structure ground; 8, protective resistance; 9, the equivalent capacity of insulation film; 10, measuring voltage value; 11, floating potential value.
Embodiment
What below introduce is the embodiment as content of the present invention, below by embodiment, described content of the present invention is further illustrated.Certainly, describing following embodiment is only the content of example different aspect of the present invention, and should not be construed as the restriction scope of the invention.
As shown in Figure 1, a kind of detector based on capacitance partial pressure, it comprises conduction potential electrode 2 and pastes insulation film 1 thereon, between conduction potential electrode 2 and spacecraft structure ground 7, with measurement electric capacity 4, be connected, and measure by tension measuring circuit 5, compensating electrode 3 is arranged in conduction potential electrode 2 peripheries and isolates with conduction potential electrode 2.Compensating electrode 3 is connected with spacecraft structure ground 7 with bias voltage source 6 by protective resistance 8.
This detector can be positioned over the outside surface of spacecraft, when spacecraft charges due to space plasma impact, spacecraft conductive structure ground 7 can produce more negative current potential, but dielectric film effect, its dielectric layer outside surface current potential and space plasma current potential approximately equal due to conduction potential electrode surface.Now, by the equivalent capacity 9 of insulation film with measure electric capacity 4 and form capacitance partial pressure network, adjust the on-off circuit of measuring in electric capacity 4 and control its capacitance, and utilize tension measuring circuit 5 to obtain two groups of corresponding voltage measuring values.By capacitance and the measuring voltage value 10 of known measurement electric capacity 4, can determine the equivalent capacity 9 that draws insulation film, according to the value of the equivalent capacity 9 of insulation film, the capacitance of measuring electric capacity 4 and measuring voltage value 10, just can determine floating potential value 11.Concrete, spacecraft floating potential is approximately equal to the potential difference (PD) U between dielectric layer outside surface current potential and spacecraft structure ground
fwherein, the capacitance that dielectric film self can be equivalent between space plasma and conduction potential electrode is C1, between conduction potential electrode and spacecraft structure earth potential, be connected measurement capacitor C 2, when spacecraft charges while reaching certain floating potential in plasma environment, between conduction potential electrode and spacecraft structure ground, voltage measuring value is U
m.According to capacitance partial pressure method, known:
Wherein, when changing 2 groups of different C2 values, can be by measuring voltage U
mand capacitor C 2 values obtain size and the U of C1
fvalue.When obtaining after C1 value through measuring, can not change the size of C2 value, directly measure floating potential value.
When measuring, because space plasma can change with spacecraft orbit position, adopt at set intervals 2 groups of different C2 values of switching over to calibrate the measured value of C1, and obtain floating potential values 11 with this value and definite, immovable measurement electric capacity 4, reduce to measure the access times of switch in electric capacity 4, increase its serviceable life in-orbit.
During measurement, while having other spacecraft outside surface bare exposed conductor near conduction potential electrode 2, can adjust the voltage of compensating electrode 3, the Outside Dimensions of compensating electrode 3 is greater than conduction potential electrode 2.When bucking voltage and space plasma current potential are approximate identical, just can reduce the impact of sheath layer around, by the bias voltage using measured value as relative spacecraft structure ground, be added on compensating electrode 3, realize and eliminate the object of disturbing around, can form feedback simultaneously, measured value after eliminate disturbing continues as new bias voltage, until that measured value reaches is at short notice stable.
Although above the specific embodiment of the present invention has been given to describe in detail and explanation; but what should indicate is; those skilled in the art can carry out various equivalences to above-mentioned embodiment according to spirit of the present invention and changes and revise; its function producing, all should be within protection domain of the present invention when not exceeding spiritual that instructions and accompanying drawing contain.
Claims (4)
1. the detector based on capacitance partial pressure, it is characterized in that, comprise conduction potential electrode (2) and paste insulation film (1) thereon, between conduction potential electrode (2) and spacecraft structure ground (7), with measurement electric capacity (4), be connected, and measure by tension measuring circuit (5), compensating electrode (3) is arranged in conduction potential electrode (2) periphery and isolates with conduction potential electrode (2).
2. detector as claimed in claim 1, is characterized in that, described compensating electrode (3) is connected with spacecraft structure ground (7) with bias voltage source (6) by protective resistance (8).
3. the method that the employing detector as described in aforementioned any one claim carries out floating potential detection, it is characterized in that, equivalent capacity (9) and measurement electric capacity (4) by insulation film form capacitance partial pressure network, adjust the on-off circuit of measuring in electric capacity (4) and control its capacitance, and utilize tension measuring circuit (5) to obtain two groups of corresponding voltage measuring values, by capacitance and the measuring voltage value (10) of known measurement electric capacity, can determine the equivalent capacity (9) that draws insulation film, according to the value of the equivalent capacity of insulation film (9), measure capacitance and the measuring voltage value (10) of electric capacity, determine floating potential value (11).
4. the method that floating potential as claimed in claim 3 is surveyed, it is characterized in that, adopt at set intervals two groups of different measurement capacitances of switching over to calibrate the measured value of insulation film equivalent capacity, and obtain floating potential value (11) with this value and definite, immovable measurement electric capacity (4).
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| CN201310631637.6A CN103604979A (en) | 2013-11-29 | 2013-11-29 | Detector based on capacitor voltage distribution and detecting method thereof |
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| CN201310631637.6A CN103604979A (en) | 2013-11-29 | 2013-11-29 | Detector based on capacitor voltage distribution and detecting method thereof |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104793043A (en) * | 2015-04-20 | 2015-07-22 | 中国科学院空间科学与应用研究中心 | Electric potential monitoring device used for plasmas in space environment |
| CN105631180A (en) * | 2014-10-31 | 2016-06-01 | 中国科学院空间科学与应用研究中心 | Method for assessing suspended potential on surface of spacecraft equipped with high-voltage battery array |
| CN105785103A (en) * | 2016-03-03 | 2016-07-20 | 兰州空间技术物理研究所 | Capacitive voltage divider type satellite surface potential monitoring device |
| CN107992150A (en) * | 2017-12-05 | 2018-05-04 | 北京卫星环境工程研究所 | Spacecraft surfactant suspension current potential super capacitor control method |
| CN109752602A (en) * | 2018-12-10 | 2019-05-14 | 兰州空间技术物理研究所 | A kind of space station potential detector electrostatic charge resets method and clear circuit |
| CN111175584A (en) * | 2019-12-26 | 2020-05-19 | 兰州空间技术物理研究所 | Low-orbit spacecraft suspension potential detection device and method |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105631180A (en) * | 2014-10-31 | 2016-06-01 | 中国科学院空间科学与应用研究中心 | Method for assessing suspended potential on surface of spacecraft equipped with high-voltage battery array |
| CN104793043A (en) * | 2015-04-20 | 2015-07-22 | 中国科学院空间科学与应用研究中心 | Electric potential monitoring device used for plasmas in space environment |
| CN105785103A (en) * | 2016-03-03 | 2016-07-20 | 兰州空间技术物理研究所 | Capacitive voltage divider type satellite surface potential monitoring device |
| CN107992150A (en) * | 2017-12-05 | 2018-05-04 | 北京卫星环境工程研究所 | Spacecraft surfactant suspension current potential super capacitor control method |
| CN109752602A (en) * | 2018-12-10 | 2019-05-14 | 兰州空间技术物理研究所 | A kind of space station potential detector electrostatic charge resets method and clear circuit |
| CN109752602B (en) * | 2018-12-10 | 2021-02-02 | 兰州空间技术物理研究所 | Static charge zero clearing method and zero clearing circuit for space station potential detector |
| CN111175584A (en) * | 2019-12-26 | 2020-05-19 | 兰州空间技术物理研究所 | Low-orbit spacecraft suspension potential detection device and method |
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Application publication date: 20140226 |