CN113189409B - Device for measuring on-orbit charging potential of space station - Google Patents
Device for measuring on-orbit charging potential of space station Download PDFInfo
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- CN113189409B CN113189409B CN202110400855.3A CN202110400855A CN113189409B CN 113189409 B CN113189409 B CN 113189409B CN 202110400855 A CN202110400855 A CN 202110400855A CN 113189409 B CN113189409 B CN 113189409B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
- G01R29/12—Measuring electrostatic fields or voltage-potential
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R19/00—Arrangements for measuring currents or voltages or for indicating presence or sign thereof
- G01R19/25—Arrangements for measuring currents or voltages or for indicating presence or sign thereof using digital measurement techniques
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Abstract
The invention belongs to the technical field of on-orbit charging potential measuring equipment of an aerospace space station, and particularly relates to a device for measuring an on-orbit charging potential of a space station, which comprises: the device comprises a disc-shaped sensor, a first potential measuring circuit, a second potential measuring circuit, a data processor and a digital display; the disc-shaped sensor is used for interacting with space plasma in real time to generate induction potential, and the induction potential is input to the first potential measuring circuit and the second potential measuring circuit respectively; the first potential measuring circuit is used for calculating a first potential difference according to an induced potential generated by the real-time disc-shaped sensor; the second potential measuring circuit is used for calculating a second potential difference according to the induced potential generated by the real-time disc-shaped sensor; the data processor is used for obtaining the on-orbit charging potential of the space station according to the first potential difference and the second potential difference and inputting the on-orbit charging potential to the digital display; and the digital display is used for displaying the on-rail charging potential of the space station.
Description
Technical Field
The invention belongs to the technical field of space station on-orbit charging potential measuring equipment, and particularly relates to a device for measuring space station on-orbit charging potential.
Background
The space station comprises a sky and core cabin, an inter-day experiment cabin and an dream-day experiment cabin, a plurality of complex scientific instruments are carried, and a person is kept on duty for a long time.
The orbit of the space station is generally 400km, and the space station interacts with space ionized layer plasma during the orbit operation, so that the surface of the space station is charged. The high-voltage battery array used in the space station can further deteriorate the surface charging state of the space station. Typically, the plasma charging alone will not exceed-10V due to the low spatial plasma temperature. However, when high voltage battery arrays are used, space stations are often caused to carry higher charging potentials; wherein, the space station charging potential refers to the potential of the space station cabin ground relative to the space plasma.
The international space station is powered by a 160V high-voltage battery array, and the initial theoretical model calculation shows that the interaction of the high-voltage battery array and plasma can enable the international space station to be at a charging potential above negative-140V. The international space station adopts a series of measures on design, and the lowest charging potential still has negative seventy-eight volts. At present, charging potentials of tens of volts or even hundreds of volts are theoretically generated for a high-voltage battery array used in a space station. The large charging potential of the space station may pose a threat to the safety of the space station's own instruments and astronauts.
Therefore, in the prior art, a device for monitoring and measuring the charging potential of the space station on the rail is not provided, and the data of the charging potential of the space station during the operation on the rail cannot be acquired in real time, so that the risk assessment of the charging potential is not facilitated.
Disclosure of Invention
In order to solve the above-mentioned drawbacks of the prior art, the present invention provides an apparatus for measuring an on-rail charging potential of a space station, the apparatus comprising: the device comprises a disc-shaped sensor, a first potential measuring circuit, a second potential measuring circuit, a data processor and a digital display;
the disc-shaped sensor is fixedly and insulatively arranged outside the cabin body of the space station and faces to the windward side of the space station running on the rail; the first potential measuring circuit, the second potential measuring circuit, the data processor and the digital display are all arranged in the space station cabin; the disc-shaped sensor is respectively in communication connection with the first potential measuring circuit and the second potential measuring circuit; the first potential measuring circuit and the second potential measuring circuit are in communication connection with a data processor, and the data processor is in communication connection with a digital display;
the disc-shaped sensor is used for interacting with space plasma in real time to generate induction potential, and the induction potential is input to the first potential measuring circuit and the second potential measuring circuit respectively;
the first potential measuring circuit is used for calculating a first potential difference according to the induced potential generated by the real-time disc-shaped sensor;
the second potential measuring circuit is used for calculating a second potential difference according to the induced potential generated by the real-time disc-shaped sensor;
the data processor is used for obtaining a space on-orbit charging potential according to the first potential difference and the second potential difference and inputting the space on-orbit charging potential to the digital display;
and the digital display is used for displaying the on-rail charging potential of the space station.
As an improvement of the above technical solution, the disc-shaped sensor is a metal disc probe or a metal disc sensor.
As an improvement of the above technical solution, the first potential measuring circuit includes: the device comprises a high-resistance resistor, a feedback resistor, an operational amplifier and an AD collector;
the high-resistance resistor is connected to the reverse input end of the operational amplifier, the common output end of the operational amplifier is connected with the AD collector, the feedback resistor is connected to the reverse input end and the common output end of the operational amplifier in parallel, and the non-inverting input end of the operational amplifier is connected to the space station cabin ground;
calculating a first potential difference according to the potential of the space plasma outside the space station collected in real time:
wherein, V1 1 To simulateA first potential difference; k is a proportionality coefficient; r is i n is a high resistance value; r f Is a feedback resistance value; v o1 The analog quantity voltage value is obtained by amplifying the first potential difference acquired in real time;
will V o1 Performing analog-to-digital conversion by an AD collector to obtain digital quantity output of the AD collector; the digital output is multiplied by a proportionality coefficient K to calculate a first potential difference V1 1 The first potential difference is a potential between the disc-shaped sensor and the space station cabin ground.
As an improvement of the above technical solution, the second potential measuring circuit includes: an operational amplifier, a Langmuir probe and an AD collector;
the disc-shaped sensor is connected to the reverse input end of the operational amplifier, the non-inverting input end of the operational amplifier is connected to a power ground of the Langmuir probe, the power of the operational amplifier is connected to the power of the Langmuir probe, and the Langmuir probe is also connected to the AD collector;
and (3) keeping the power ground of the Langmuir probe consistent with the induction potential generated by the disc-shaped sensor through a feedback circuit of an operational amplifier, directly measuring the space plasma potential by using the Langmuir probe to obtain the space plasma potential U, carrying out analog-to-digital conversion on the potential between the disc-shaped sensor and the space plasma through an AD collector to obtain a second potential difference digital quantity output which is used as a second potential difference V2 and is the potential between the disc-shaped sensor and the space plasma.
As one of the improvements of the above technical solution, the specific process of the data processor is as follows:
obtaining a space station on-rail charging potential V according to the first potential difference and the second potential difference:
V＝V1+V2；
wherein V1 is a first potential difference; v2 is a second potential difference;
and inputting the calculated space on-rail charging potential V to a digital display.
Compared with the prior art, the invention has the beneficial effects that:
the measuring device of the invention obtains the charging potential of the space station relative to the space plasma by using a combined measuring mode; the on-orbit charging potential real-time measurement of the space station can be realized, and the on-orbit charging potential is displayed in a digital display screen mode, so that observation of astronauts is facilitated.
Drawings
FIG. 1 is a schematic diagram of an apparatus for measuring an on-rail charging potential of a space station according to the present invention;
FIG. 2 is a schematic diagram of a first measurement circuit of the apparatus for measuring an on-rail charging potential of the space station of FIG. 1 according to the present invention;
fig. 3 is a schematic diagram of a second measuring circuit of the apparatus for measuring the on-rail charging potential of the space station of fig. 1 according to the present invention.
Reference numerals:
1. disc-shaped sensor 2, high impedance resistor
3. Feedback resistor 4, space cabin ground
5. Operational amplifier 6, AD collector
7. Langmuir probe 8, power ground
Detailed Description
The invention will now be further described with reference to the accompanying drawings.
As shown in fig. 1, the present invention provides an apparatus for measuring an on-rail charging potential of a space standing on a rail, the apparatus comprising: the device comprises a disc-shaped sensor, a first potential measuring circuit, a second potential measuring circuit, a data processor and a digital display;
the disc-shaped sensor is fixedly and insulatively arranged outside the cabin body of the space station and faces to the windward side of the space station running on the rail; the first potential measuring circuit, the second potential measuring circuit, the data processor and the digital display are all arranged in the space station cabin; the disc-shaped sensor is respectively in communication connection with the first potential measuring circuit and the second potential measuring circuit; the first potential measuring circuit and the second potential measuring circuit are in communication connection with a data processor, and the data processor is in communication connection with a digital display; in the embodiment, the disc-shaped sensor is respectively connected with the first measuring circuit and the second measuring circuit through cables;
the disc-shaped sensor is used for interacting with space plasma in real time to generate induction potential, and the induction potential is input to the first potential measuring circuit and the second potential measuring circuit respectively;
specifically, the disc-shaped sensor is a metal disc probe or a metal disc sensor, and can interact with space plasma in real time to generate an induced potential.
The metal disc sensor needs to be installed outside the cabin body of the space station in an insulated mode and faces the windward side of the space station running on the rail, and the isolation impedance of the insulated installation is larger than 100G omega.
The diameter of the disc-shaped sensor is not less than 100mm; in order to avoid on-track oxidation, gold plating treatment can be adopted on the surface.
The first potential measuring circuit is used for calculating a first potential difference according to the induced potential generated by the disc-shaped sensor;
specifically, as shown in fig. 2, the first potential measuring circuit includes: the device comprises a high-resistance resistor 2, a feedback resistor 3, an operational amplifier 5 and an AD collector 6;
the disc-shaped sensor 1 is connected with a high-resistance resistor 2, the high-resistance resistor 2 is connected with the reverse input end of an operational amplifier 5, the common output end of the operational amplifier 5 is connected with an AD collector 6, a feedback resistor 3 is connected in parallel with the reverse input end and the common output end of the operational amplifier 5, and the non-inverting input end of the operational amplifier 5 is connected with a space station cabin ground 4;
calculating a first potential difference according to the potential of the space plasma outside the space station collected in real time:
wherein, V1 1 To simulate a first potential difference; k is a proportionality coefficient; r in A high resistance value; r f Is a feedback resistance value; v o1 The voltage value is an analog quantity voltage value obtained by amplifying the potential of the V1;
will V o1 And performing analog-to-digital conversion by the AD collector to obtain digital quantity output of the AD collector, and multiplying the digital quantity output by a proportionality coefficient K to obtain the potential between the disc-shaped sensor and the space station cabin ground.
High-resistance resistor R in A resistance value of more than 100G Ω is generally selected, which has the effect of electrically isolating the disk-shaped sensor from the space station bay.
Wherein, the input voltage range of the operational amplifier is usually [ -10V, +10V]. Therefore, the high resistance resistor R in And a feedback resistor R f The formed proportionality coefficient K is adaptively adjusted according to the actual charging potential range to be measured to ensure
Should be in [ -10V, +10V]Within the range.
The operational amplifier is preferably a remote operational amplifier having a high input impedance of not less than 10 13 Ω。
The second potential measuring circuit is used for calculating a second potential difference according to the induced potential generated by the disc-shaped sensor;
specifically, as shown in fig. 3, the second potential measuring circuit includes: an operational amplifier 5, a Langmuir probe 7 and an AD collector 6;
the disc-shaped sensor 1 is connected to the reverse input end of an operational amplifier 5, the non-inverting input end of the operational amplifier 5 is connected to a power ground 8 of a Langmuir probe 7, meanwhile, the power of the operational amplifier 5 is connected to the power of the Langmuir probe 7, and the Langmuir probe 7 is also connected to an AD collector 6; the common output of the operational amplifier 5 is communicatively connected to the langmuir probe 7, and the output of the operational amplifier 5 is connected to the space station bay.
The power supply 8 of the langmuir probe 7 was kept at the same potential as the induced potential generated by the disc sensor 1 by the feedback circuit of the operational amplifier 5, and the space plasma potential U was obtained by directly measuring the space plasma potential by the langmuir probe 7. The space plasma potential U is set to-U with the power ground of the langmuir probe 7 (i.e., the disk sensor 1) as the ground, and when the space plasma is set to the ground, the potential between the disk sensor 1 and the space plasma is analog-to-digital converted by the AD converter to obtain a second potential difference digital quantity output V2, which is set to a second potential difference between the disk sensor and the space plasma.
The data processor is used for obtaining a space on-orbit charging potential according to the first potential difference and the second potential difference and inputting the space on-orbit charging potential to the digital display;
specifically, according to the first potential difference and the second potential difference, the space station on-rail charging potential V, namely the charging potential of the space station relative to the space plasma is obtained:
V＝V1+V2＝K·V o1 +V2；
wherein V1 is a first potential difference; v2 is a second potential difference;
and inputting the calculated space on-rail charging potential V to a digital display.
And the digital display is used for displaying the on-rail charging potential of the space station.
The device can monitor the on-orbit charging potential of the space station in real time, and the AD collector outputs the proportional output voltage V of the first potential difference V1 o1 And the second potential difference V2 is respectively converted into corresponding digital quantity to be output, and then the subsequent data processor carries out simple multiplication and addition calculation, so that the digital quantity of the charging potential V of the space station relative to the space plasma can be obtained, and the digital display can be conveniently carried out on the digital display.
Finally, it should be noted that the above embodiments are only used for illustrating the technical solutions of the present invention and are not limited. Although the present invention has been described in detail with reference to the embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (2)
1. An apparatus for measuring an on-rail charging potential of a space, the apparatus comprising: the device comprises a disc-shaped sensor, a first potential measuring circuit, a second potential measuring circuit, a data processor and a digital display;
the disc-shaped sensor is fixedly and insulatively arranged outside the cabin body of the space station and faces to the windward side of the space station running on the rail; the first potential measuring circuit, the second potential measuring circuit, the data processor and the digital display are all arranged in the space station cabin; the disc-shaped sensor is respectively in communication connection with the first potential measuring circuit and the second potential measuring circuit; the first potential measuring circuit and the second potential measuring circuit are in communication connection with a data processor, and the data processor is in communication connection with a digital display;
the disc-shaped sensor is used for interacting with space plasma in real time to generate induction potential, and the induction potential is input to the first potential measuring circuit and the second potential measuring circuit respectively;
the first potential measuring circuit is used for calculating a first potential difference according to an induced potential generated by the real-time disc-shaped sensor;
the second potential measuring circuit is used for calculating a second potential difference according to the induced potential generated by the real-time disc-shaped sensor;
the data processor is used for obtaining a space on-orbit charging potential according to the first potential difference and the second potential difference and inputting the space on-orbit charging potential to the digital display;
the digital display is used for displaying the on-orbit charging potential of the space station;
the first potential measurement circuit includes: the device comprises a high-resistance resistor, a feedback resistor, an operational amplifier and an AD collector;
the high-resistance resistor is connected to the reverse input end of the operational amplifier, the common output end of the operational amplifier is connected with the AD collector, the feedback resistor is connected to the reverse input end and the common output end of the operational amplifier in parallel, and the non-inverting input end of the operational amplifier is connected to the space station cabin ground;
calculating a first potential difference according to the potential of the space plasma outside the space station collected in real time:
wherein, V1 1 To simulate a first potential difference; k is a proportionality coefficient; r in A high resistance value; r f Is a feedback resistance value; v o1 The analog quantity voltage value is obtained by amplifying the first potential difference acquired in real time;
will V o1 Performing analog-to-digital conversion by an AD collector to obtain digital quantity output of the AD collector; the digital output is multiplied by a proportionality coefficient K to calculate a first potential difference V1 1 The first potential difference is the potential between the disc-shaped sensor and the cabin ground of the space station;
the second potential measuring circuit includes: an operational amplifier, a Langmuir probe and an AD collector;
the disc-shaped sensor is connected to the reverse input end of the operational amplifier, the non-inverting input end of the operational amplifier is connected to a power ground of the Langmuir probe, the power of the operational amplifier is connected to the power of the Langmuir probe, and the Langmuir probe is also connected to the AD collector;
keeping the power ground of the Langmuir probe consistent with the induced potential generated by the disc-shaped sensor through a feedback circuit of an operational amplifier, directly measuring the potential of the space plasma by using the Langmuir probe to obtain the potential U of the space plasma, carrying out analog-to-digital conversion on the potential between the disc-shaped sensor and the space plasma through an AD collector to obtain a second potential difference digital quantity output which is used as a second potential difference V2 and is the potential between the disc-shaped sensor and the space plasma;
the specific process of the data processor is as follows:
obtaining a space station on-rail charging potential V according to the first potential difference and the second potential difference:
V＝V1+V2；
wherein V1 is a first potential difference; v2 is a second potential difference;
and inputting the calculated space on-rail charging potential V to a digital display.
2. The apparatus for measuring a space on-rail charging potential of claim 1, wherein the disk sensor is a metal disk probe or a metal disk sensor.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1374260A (en) * | 1970-12-29 | 1974-11-20 | Itt | Electrical measuring instruments |
| CN104828263A (en) * | 2015-04-07 | 2015-08-12 | 中国科学院空间科学与应用研究中心 | Detection device for spacecraft surface charging effects |
| 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 |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102540127B (en) * | 2012-01-05 | 2014-06-18 | 北京东方计量测试研究所 | Calibration platform for space potential detector of low-orbit spacecraft |
| GB201300799D0 (en) * | 2013-01-16 | 2013-02-27 | Uni I Olso | Langmuir Probe |
| CN109803475A (en) * | 2017-11-15 | 2019-05-24 | 中国科学院国家空间科学中心 | A kind of device for establishing detector reference potential in space plasma environment |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1374260A (en) * | 1970-12-29 | 1974-11-20 | Itt | Electrical measuring instruments |
| CN104828263A (en) * | 2015-04-07 | 2015-08-12 | 中国科学院空间科学与应用研究中心 | Detection device for spacecraft surface charging effects |
| 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 |
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