CN105460238B - A kind of Satellite surface potential active control system - Google Patents
A kind of Satellite surface potential active control system Download PDFInfo
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- CN105460238B CN105460238B CN201410452549.4A CN201410452549A CN105460238B CN 105460238 B CN105460238 B CN 105460238B CN 201410452549 A CN201410452549 A CN 201410452549A CN 105460238 B CN105460238 B CN 105460238B
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Abstract
The invention provides a kind of Satellite surface potential active control system, the current balance type on spacecraft surface is corrected to spatial emission cation stream by using liquid metal ion transmitter, control Satellite surface potential, avoid inequality electrification phenomenon, also photoelectron can be reduced and upset plasma ion and the energy band of electronic surveying, the scope limited close to apparatus measures, improves the stability and accuracy of measurement；The current potential Active Control Method of the present invention can control positive potential and negative potential simultaneously, therefore with wider application；The present invention control system Satellite surface potential is controlled by using liquid metal ion transmitter, heated from satellite power supply and high voltage supply, thus the system have it is simple in construction, it is easy to accomplish the characteristics of.
Description
Technical field
Field, more particularly to a kind of spacecraft current potential active control system are protected the present invention relates to spacecraft space environmental effect
System.
Background technology
Spacecraft in orbit during, influenceed by space environments such as space plasma, illumination, by produce surface charge product
The tired electrification phenomenon caused.In earth's shadow area, Satellite surface potential is possible to reach negative thousands of volts even volts up to ten thousand；And
Under the conditions of solar irradiation, influenceed by photoelectron emissions, the current potential of spacecraft illuminating surface is possible to reach positive tens of volts.Boat
Its device surface electrification phenomenon can cause to have a strong impact on to the accuracy of its in-orbit safe and stable operation and detection data：
(1) spacecraft surface will inevitably use the material of a variety of different qualities, the dielectric constant of these materials, two
The parameters such as secondary electron emission coefficiency, photoelectron emissions coefficient all have differences, therefore can also produce under environment of the same race potential difference；
Dielectric material is commonly used in spacecraft surface, can also exist in the same media material of spacecraft surface area of illumination and non-area of illumination
Potential difference.When above-mentioned potential difference reaches to a certain degree, it may occur that electric discharge, puncture surfacing or interference spacecraft fortune
OK；
(2) spacecraft to space environment especially plasma environment is accurately measured when, it is desirable to spacecraft have compared with
Low current potential, and the surface potential that spacecraft surface electrification phenomenon is caused can influence the track of plasma and energy around spacecraft
Amount, makes plasma distribution function become distortion, it is difficult to accurate measurement ion distribution function and low-energy electron spectrum.
The measures such as strict ground connection are employed during China's Spacecraft guidance and control to prevent the generation of inequality electrification phenomenon.But
It is that simple grounding measures are with influences such as the size increase of each Orbital Space Vehicle of China, life, operating voltage raisings
It is increasingly difficult to meet requirement.Especially all kinds of space environment exploration satellites propose intimate harshness to spacecraft control of Electric potentials
It is required that, therefore, it is necessary to develop a kind of Satellite surface potential control system.
The content of the invention
In view of this, the invention provides a kind of Satellite surface potential active control system, by using liquid metal
Ion emitter controls Satellite surface potential to spatial emission cation stream, it is to avoid inequality electrification phenomenon, improves measurement
Stability and accuracy, and can simultaneously control surface positive potential and negative potential, be with a wide range of applications.
In order to solve the above-mentioned technical problem, the present invention is realized in：
A kind of spacecraft current potential active control system, including control unit, power subsystem, surface potential monitoring probe and
Liquid metal ion transmitter；Described control unit respectively with power subsystem, surface potential monitoring probe and liquid metal from
Sub- transmitter is connected；The power subsystem is connected with the satellite power supply in liquid metal ion transmitter and spacecraft respectively；
The surface potential monitoring probe is fixed on spacecraft surface, the current potential for gathering spacecraft surface in real time, and
Electric potential signal is sent to described control unit；
The liquid metal ion transmitter is fixed on spacecraft surface, liquid metal ion transmitter and spacecraft appearance
Face is grounded, both mutual insulatings；Liquid metal ion transmitter is used for the spatial emission cation stream where spacecraft, together
When, by the temperature signal in its interior metal pond to described control unit；
The power subsystem is according to the power demands of the liquid metal ion transmitter, by the power supply from satellite power supply
Changed, and heating is provided to the solid metallic of liquid metal ion transmitter according to the control signal received from control unit
Power supply or the extraction pole offer high voltage supply to liquid metal ion transmitter；
Described control unit is sent according to the temperature signal from liquid metal ion transmitter receipt to the power subsystem
Control signal, the heating that control power subsystem starts or terminated to solid metallic is powered, and the metal in metal pool is maintained melting
State；
The electric potential signal that described control unit is popped one's head in and received according to being monitored from the surface potential, sends out to the power subsystem
Send control signal：When electric potential signal is higher than preset potential scope, is sent to power subsystem and start high voltage supply control signal；When
When electric potential signal is equal to or less than preset potential scope, is sent to power subsystem and terminate high voltage supply control signal, be achieved in
To the active control of Satellite surface potential.
Described control unit includes to the control of positive potential and to negative potential to the active control of Satellite surface potential
Control：
When carrying out active control to positive potential：As judgement Satellite surface potential VsMore than default positive potential VlWhen, to described
Power subsystem, which is sent, starts high voltage supply control signal；As Satellite surface potential VsReach or less than default positive potential VlWhen, to
The power subsystem, which is sent, stops high voltage supply control signal；
When carrying out active control to negative potential：As judgement Satellite surface potential VsLess than default negative potential lower limit V2
When, control unit disconnects the ground connection of liquid metal ion transmitter, and sends beginning high pressure confession to the power subsystem simultaneously
Electric control signal；As judgement Satellite surface potential VsReach or surpass default negative potential V3When, send and stop to the power subsystem
Only high voltage supply control signal；
Wherein, the default negative potential lower limit V2It is taken as the minimum safe current potential not discharged on spacecraft surface；
The default negative potential V3More than default negative potential lower limit V2。
Metal in the liquid metal ion transmitter selects indium metal.
The liquid metal ion transmitter is carried in drawing for liquid metal ion transmitter to control unit Real-time Feedback
The voltage gone out on extremely；Described control unit enters the extraction pole on-load voltage of feedback and the magnitude of voltage that is exported to power subsystem
Row compares, and once judges whether power subsystem is in normal operating conditions.
Described control unit is also connected with the satellite power supply of spacecraft, for itself and surface potential monitoring probe progress
Power supply.
Described control unit is also connected with the switching on and shutting down control device of spacecraft, and the switching on and shutting down for receiving spacecraft are believed
Number, after the starting-up signal of spacecraft is received, just start to be controlled power subsystem.
Described control unit is also connected with the communication bus of spacecraft respectively, and the electric potential signal on spacecraft surface is uploaded to
Spacecraft.
The present invention has the advantages that：
(1) current balance type of the invention by launching positive ion beam amendment spacecraft surface, reduces Satellite surface potential,
Inequality electrification phenomenon is avoided, photoelectron can be also reduced and upset plasma ion and the energy band of electronic surveying, close to instrument
The scope of limitation is measured, the stability and accuracy of measurement is improved；
(2) current potential Active Control Method of the invention can control positive potential and negative potential simultaneously, therefore with more extensive
Application；
(3) control system of the invention is controlled by using liquid metal ion transmitter to Satellite surface potential
System, heated from satellite power supply and high voltage supply, therefore the system have it is simple in construction, it is easy to accomplish the characteristics of.
Brief description of the drawings
Fig. 1 is the structural representation of the control system of the present invention.
Fig. 2 is the schematic diagram of the control system of the present invention.
Wherein, 1- surface potentials monitoring probe, 2- liquid metal ion transmitters, 3- control units, 4- power subsystems.
Embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
A kind of spacecraft current potential active control system of the present invention, as illustrated in fig. 1 and 2, including control unit, power supply list
Member, surface potential monitoring probe and liquid metal ion transmitter；Control unit is monitored with power subsystem, surface potential respectively
Probe and liquid metal ion transmitter are connected；Power subsystem respectively with defending in liquid metal ion transmitter and spacecraft
Star power supply is connected；
Surface potential monitoring probe is fixed on spacecraft surface, the current potential for gathering spacecraft surface in real time, and by electricity
Position signal is sent to control unit；
Liquid metal ion transmitter is fixed on spacecraft surface, and liquid metal ion transmitter and spacecraft outer surface are equal
Ground connection, both mutual insulatings；Liquid metal ion transmitter is used for the spatial emission cation stream where spacecraft, meanwhile,
By the temperature signal in its interior metal pond to control unit；
Power subsystem is turned the power supply from satellite power supply according to the power demands of liquid metal ion transmitter
Change, and according to the control signal received from control unit the solid metallic of liquid metal ion transmitter is provided heating power supply or
High voltage supply is provided to extraction pole；
Control unit sends control letter according to the temperature signal from liquid metal ion transmitter receipt to power subsystem
Number, the heating that control power subsystem starts or terminated to solid metallic is powered, and the metal in metal pool is maintained molten condition；
The electric potential signal that control unit is popped one's head in and received according to being monitored from surface potential, control signal is sent to power subsystem：
When electric potential signal is higher than preset potential, is sent to power subsystem and start high voltage supply control signal；Be equal to when electric potential signal or
During less than preset potential, sent to power subsystem and terminate high voltage supply control signal, be achieved in Satellite surface potential
Active control.
Wherein, control unit includes to the control of positive potential and to negative potential to the active control of Satellite surface potential
Control：
When carrying out active control to positive potential：As judgement Satellite surface potential VsMore than default positive potential VlWhen, to power supply
Unit, which is sent, starts high voltage supply control signal, and power subsystem carries out high voltage supply, liquid gold to liquid metal ion transmitter
Category ion emitter starts to launch cation stream, the positive potential on reduction spacecraft surface；As Satellite surface potential VsReach or
Less than default positive potential VlWhen, sent to power subsystem and stop high voltage supply control signal, liquid metal ion transmitter stops
Launch cation stream.
When carrying out active control to negative potential：As judgement Satellite surface potential VsLess than default negative potential lower limit V2
When, control unit disconnects the ground connection of liquid metal ion transmitter, and sends beginning high voltage supply control to power subsystem simultaneously
Signal power source unit processed to liquid metal ion transmitter carry out high voltage supply, liquid metal ion transmitter start transmitting just from
Subflow, because spacecraft surface is negative potential, the cation stream of transmitting can return to spacecraft surface under graviational interaction, due to liquid
State metal ion transmitter ground connection disconnect, and with spacecraft surface insulation, transmitting cation stream can't assemble electronics, therefore,
The cation of falling has neutralized the negative electrical charge on spacecraft surface, which thereby enhances Satellite surface potential；When judgement spacecraft table
Face current potential VsReach or surpass default negative potential V3When, to power subsystem send stop high voltage supply control signal, liquid metal from
Sub- transmitter stops transmitting cation stream.
Wherein, default negative potential lower limit V2It is taken as the minimum safe current potential not discharged on spacecraft surface；To keep away
Exempt from liquid metal ion source frequently to start shooting, preset negative potential V3More than default negative potential lower limit V2；In order to extend liquid metal
The service life of ion gun, the switching on and shutting down number of times of liquid metal ion source, therefore default negative potential V will be reduced as far as possible3Size
To ensure spacecraft as far as possible in the running of track shadow region, its surface potential will not be re-lowered under default negative potential
Limit value V2。
Liquid metal ion transmitter is carried in the voltage on extraction pole to control unit Real-time Feedback；Control unit will be anti-
Whether the extraction pole on-load voltage of feedback is compared with the magnitude of voltage exported to power subsystem, once judge power subsystem in just
Normal working condition.
Control unit is also connected with the satellite power supply of spacecraft, for supplying itself and surface potential monitoring probe
Electricity.
Control unit is also connected with the switching on and shutting down control device of spacecraft, the switching on and shutting down signal for receiving spacecraft,
After the starting-up signal for receiving spacecraft, just control signal is sent to power subsystem.
Control unit is also connected with the communication bus of spacecraft respectively, and the electric potential signal on spacecraft surface is uploaded into space flight
Device.
Liquid metal ion transmitter current potential active control checking test is illustrated：
So that liquid metal ion transmitter controls electric spacecraft surface positive potential as an example, devise a kind of based on indium liquid gold
Belong to the control system of ion emitter.When indium liquid metal ion transmitter current potential active control works, control system is first opened
Voltage heats liquid metal between 180~200 DEG C for 30V heating power supply, and probe monitors are monitored by surface potential
Surface potential, when surface potential is more than presetting potential, control system opens priming supply, actual ignition voltage<8kV, igniting
After success, actual motion voltage<7kV；Monitor that ion energy is 5~10keV, single transmitter ion beam current by mass spectrograph
For 10~100 μ A, operating voltage is 6kV during 20 μ A of exemplary operation electric current.By detecting surface potential in real time, through control system point
Analysis is handled, and when surface potential drops to presetting potential, control igniting high voltage power supply power-off, closes liquid metal ion transmitter,
So as to realize the active control to surface positive potential.
For in the reliability of ground validation this control system control spacecraft surface positive potential, equipped with solar simulator
In vacuum system, indium liquid metal ion transmitter potential active control device is installed, simple analog space environment space flight is used as
Device charging potential active control experiment.Brief control process is as follows：
1) liquid metal ion transmitter heating power supply is opened by control unit, liquid metal temperature is reached design
Temperature range, now detects liquid metal ion emitter temperature for 185 DEG C；
2) charging of solar simulator space environmental simulation is opened, surface potential is detected in real time, preset voltage is 0V, for simulation
Most adverse circumstances are charged to maximum potential, are not compared with presetting potential.
3) when surface potential detection reaches+40V, control unit opens the work of liquid metal ion transmitter.Voltage 5kV
When, the igniting of liquid metal ion transmitter, when drawing pole tension 6kV, detection emission current is 20 μ A；
4) pass through 5~6 minutes or so, detect surface potential for 0.4V；
5) when detecting surface potential for 0V, the high voltage supply unit of control unit control power subsystem is closed, liquid
Metal ion transmitter is closed, and realizes the active control of surface potential.
Citing illustrates that this system can effectively realize the active of Satellite surface potential with exemplified by verification experimental verification more than
Control.
In summary, presently preferred embodiments of the present invention is these are only, is not intended to limit the scope of the present invention.
Within the spirit and principles of the invention, any modification, equivalent substitution and improvements made etc., should be included in the present invention's
Within protection domain.
Claims (7)
1. a kind of spacecraft current potential active control system, it is characterised in that including control unit, power subsystem, surface potential prison
Probing head and liquid metal ion transmitter；Described control unit respectively with power subsystem, surface potential monitoring probe and
Liquid metal ion transmitter is connected；The power subsystem respectively with liquid metal ion transmitter and spacecraft satellite electricity
Source is connected；
Surface potential monitoring probe is fixed on spacecraft surface, the current potential for gathering spacecraft surface in real time, and by electricity
Position signal is sent to described control unit；
The liquid metal ion transmitter is fixed on spacecraft surface, and liquid metal ion transmitter and spacecraft outer surface are equal
Ground connection, both mutual insulatings；Liquid metal ion transmitter is used for the spatial emission cation stream where spacecraft, meanwhile,
The temperature signal in its interior metal pond is sent to described control unit；
The power subsystem is carried out the power supply from satellite power supply according to the power demands of the liquid metal ion transmitter
Conversion, and provide heating power supply to the solid metallic of liquid metal ion transmitter according to the control signal received from control unit
Or provide high voltage supply to the extraction pole of liquid metal ion transmitter；
Described control unit sends to the power subsystem and controlled according to the temperature signal from liquid metal ion transmitter receipt
Signal, the heating that control power subsystem starts or terminated to solid metallic is powered, and the metal in metal pool is maintained molten condition；
The electric potential signal that described control unit is popped one's head in and received according to being monitored from the surface potential, sends to the power subsystem and controls
Signal processed：When electric potential signal is higher than preset potential scope, is sent to power subsystem and start high voltage supply control signal；Work as current potential
When signal is equal to or less than preset potential scope, is sent to power subsystem and terminate high voltage supply control signal, be achieved in boat
The active control of its device surface potential.
2. a kind of spacecraft current potential active control system according to claim 1, it is characterised in that described control unit pair
The active control of Satellite surface potential includes the control to positive potential and the control to negative potential：
When carrying out active control to positive potential：As judgement Satellite surface potential VsMore than default positive potential VlWhen, to the power supply
Unit, which is sent, starts high voltage supply control signal；As Satellite surface potential VsReach or less than default positive potential VlWhen, to described
Power subsystem, which is sent, stops high voltage supply control signal；
When carrying out active control to negative potential：As judgement Satellite surface potential VsLess than default negative potential lower limit V2When, control
Unit processed disconnects the ground connection of liquid metal ion transmitter, and sends beginning high voltage supply control to the power subsystem simultaneously
Signal；As judgement Satellite surface potential VsReach or surpass default negative potential V3When, sent to the power subsystem and stop high pressure
Power supplying control signal；
Wherein, the default negative potential lower limit V2It is taken as the minimum safe current potential not discharged on spacecraft surface；It is described pre-
If negative potential V3More than default negative potential lower limit V2。
3. a kind of spacecraft current potential active control system according to claim 1, it is characterised in that the liquid metal from
Metal in sub- transmitter selects indium metal.
4. a kind of spacecraft current potential active control system according to claim 2, it is characterised in that the liquid metal from
Sub- transmitter is carried in the voltage on the extraction pole of liquid metal ion transmitter to control unit Real-time Feedback；The control is single
First extraction pole on-load voltage by feedback is compared with the magnitude of voltage exported to power subsystem, once whether judges power subsystem
In normal operating conditions.
5. a kind of spacecraft current potential active control system according to claim 1, it is characterised in that described control unit is also
It is connected with the satellite power supply of spacecraft, for being powered to itself and surface potential monitoring probe.
6. a kind of spacecraft current potential active control system according to claim 1, it is characterised in that described control unit is also
It is connected with the switching on and shutting down control device of spacecraft, the switching on and shutting down signal for receiving spacecraft is receiving the start of spacecraft
After signal, just start to be controlled power subsystem.
7. a kind of spacecraft current potential active control system according to claim 1, it is characterised in that described control unit is also
It is connected respectively with the communication bus of spacecraft, the electric potential signal on spacecraft surface is uploaded to spacecraft.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105923173B (en) * | 2016-06-08 | 2017-12-22 | 中国空间技术研究院 | A kind of GEO satellite external multi-layer insulating assembly earthed system and method |
| CN106927069B (en) * | 2017-03-29 | 2019-10-08 | 北京卫星环境工程研究所 | Spacecraft current potential autonomous control membrane structure |
| 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 |
| CN107979910B (en) * | 2017-11-29 | 2020-06-05 | 中国人民解放军陆军工程大学 | Active control method for surface potential of dielectric material in high vacuum environment |
| CN109319172B (en) * | 2018-09-28 | 2022-01-21 | 兰州空间技术物理研究所 | Method for controlling on-orbit surface charging effect of spacecraft |
| CN111060773A (en) * | 2019-12-31 | 2020-04-24 | 北京空间技术研制试验中心 | Spacecraft docking potential control test method |
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