CN105460238A - Spacecraft surface potential active control system - Google Patents
Spacecraft surface potential active control system Download PDFInfo
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- CN105460238A CN105460238A CN201410452549.4A CN201410452549A CN105460238A CN 105460238 A CN105460238 A CN 105460238A CN 201410452549 A CN201410452549 A CN 201410452549A CN 105460238 A CN105460238 A CN 105460238A
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Abstract
The invention provides a spacecraft surface potential active control system. A liquid metal ion emitter is used for emitting positive ion current to the space to correct current balance on a spacecraft surface to control spacecraft surface potential, thereby avoiding an unequal electrification phenomenon; and photoelectron disturbed plasma ions and electronically measured energy bands can also be reduced to approach the range limited by instrument measurement, thereby improving the measurement stability and accuracy. A potential active control method provided by the invention can simultaneously control positive potential and negative potential so that the range of application is wider. The control system provided by the invention adopts the liquid metal ion emitter for controlling the spacecraft surface potential, and heating and high voltage power supply can be acquired from a satellite power supply, so that the system has the characteristics of simple structure and easiness in implementation.
Description
Technical field
The present invention relates to spacecraft space environmental effect protection field, particularly relate to a kind of spacecraft current potential active control system.
Background technology
Spacecraft is period in orbit, affects by the space environment such as space plasma, illumination, and generation surface charge is accumulated the electrification phenomenon caused.In earth's shadow district, Satellite surface potential likely reaches negative thousands of volts volt even up to ten thousand; And under solar irradiation condition, affect by photoelectron emissions, the current potential of spacecraft illuminating surface likely reaches positive tens of volts.Spacecraft surface band electrical phenomena can to its in-orbit the accuracy of safe and stable operation and detection data cause and have a strong impact on:
(1) spacecraft surface inevitably will adopt the material of multiple different qualities, and the parameter such as specific inductance capacity, secondary electron yield, photoelectron emissions coefficient of these materials all there are differences, under environment of the same race, therefore also can produce difference of potential; Spacecraft surface often uses dielectric material, also can there is difference of potential at the same media material of spacecraft surface area of illumination and non-area of illumination.When above-mentioned difference of potential acquires a certain degree, may discharge, puncture surface material or the operation of interference spacecraft;
(2) spacecraft is when to space environment, especially plasma environment is accurately measured, require that spacecraft has lower current potential, and the surface potential that spacecraft surface band electrical phenomena causes can affect track and the energy of plasma around spacecraft, make plasma distribution function become distortion, be difficult to Measurement accuracy ion distribution function and low-energy electron spectrum.
Have employed the measures such as strict ground connection to prevent the generation of inequality electrification phenomenon in China's Spacecraft guidance and control process.But along with the impact such as size increase, life, operating voltage raising of each Orbital Space Vehicle of China, simple grounding measures has more and more been difficult to meet the demands.Especially all kinds of space environment exploration satellite proposes spacecraft control of Electric potentials and is close to harsh requirement, therefore, is necessary to develop a kind of Satellite surface potential control system.
Summary of the invention
In view of this, the invention provides a kind of Satellite surface potential active control system, Satellite surface potential is controlled to spatial emission positive ion stream by adopting liquid metal ion projector, avoid inequality electrification phenomenon, improve the stability and accuracy measured, and can simultaneously control surface positive potential and negative potential, be with a wide range of applications.
In order to solve the problems of the technologies described above, the present invention is achieved in that
A kind of spacecraft current potential active control system, comprises control unit, power subsystem unit, surface potential monitoring probe and liquid metal ion projector; Described control unit is connected with power subsystem unit, surface potential monitoring probe and liquid metal ion projector respectively; Described power subsystem unit is connected with the satellite power supply in spacecraft with liquid metal ion projector respectively;
Described surface potential monitoring probe is fixed on spacecraft surface, for the current potential on Real-time Collection spacecraft surface, and electric potential signal is sent to described control unit;
Described liquid metal ion projector is fixed on spacecraft surface, liquid metal ion projector and the equal ground connection of spacecraft outside face, both mutual insulatings; Liquid metal ion projector is used for the spatial emission positive ion stream to spacecraft place, meanwhile, by the temperature signal in its interior metal pond to described control unit;
Described power subsystem unit is according to the power demands of described liquid metal ion projector, power supply from satellite power supply is changed, and provides the extraction pole of heating power supply or liquid towards metallic ion projector to provide high voltage supply according to the solid metallic of the control signal liquid towards metallic ion projector received from control unit;
Described control unit, according to the temperature signal from liquid metal ion transmitter receipt, transmits control signal to described power subsystem unit, controls power subsystem unit and starts or terminate to power to the heating of solid metallic, makes the metal in metal pool maintain molten condition;
Described control unit, according to the electric potential signal received from described surface potential monitoring probe, transmits control signal to described power subsystem unit: when electric potential signal is higher than preset potential scope, sends start high voltage supply control signal to power subsystem unit; When electric potential signal is equal to or less than preset potential scope, sends to power subsystem unit and terminate high voltage supply control signal, realize the ACTIVE CONTROL to Satellite surface potential thus.
The ACTIVE CONTROL of described control unit to Satellite surface potential comprises the control to positive potential and the control to negative potential:
When ACTIVE CONTROL is carried out to positive potential: as judgement Satellite surface potential V
sbe greater than default positive potential V
ltime, send to described power subsystem unit and start high voltage supply control signal; As Satellite surface potential V
sreach or be less than default positive potential V
ltime, send to described power subsystem unit and stop high voltage supply control signal;
When ACTIVE CONTROL is carried out to negative potential: as judgement Satellite surface potential V
sbe less than default negative potential lower limit V
2time, the ground connection of liquid metal ion projector disconnects by control unit, and sends beginning high voltage supply control signal to described power subsystem unit simultaneously; As judgement Satellite surface potential V
sreach or surpass preset negative current potential V
3time, send to described power subsystem unit and stop high voltage supply control signal;
Wherein, described default negative potential lower limit V
2be taken as the minimum safe current potential that spacecraft surface does not occur to discharge; Described preset negative current potential V
3be greater than default negative potential lower limit V
2.
Metal in described liquid metal ion projector selects indium metal.
Described liquid metal ion projector is carried in the voltage on the extraction pole of liquid metal ion projector to control unit Real-time Feedback; The extraction pole on load voltage of feedback and the described magnitude of voltage exported to power subsystem unit compare by described control unit, once judge whether power subsystem unit is in normal working.
Described control unit is also connected with the satellite power supply of spacecraft, for powering to self and surface potential monitoring probe.
Described control unit is also connected with the switching on and shutting down control convenience of spacecraft, for receiving the switching on and shutting down signal of spacecraft, after receiving the starting-up signal of spacecraft, just starts to control power subsystem unit.
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 following beneficial effect:
(1) the present invention is by launching the current balance type on positive ion beam correction spacecraft surface, reduce Satellite surface potential, avoid inequality electrification phenomenon, also the energy band that photoelectron upsets plasma ion and electronic measurement can be reduced, close to the scope of apparatus measures restriction, improve the stability and accuracy measured;
(2) current potential Active Control Method of the present invention can control positive potential and negative potential simultaneously, therefore has field of application widely;
(3) control system of the present invention controls Satellite surface potential by adopting liquid metal ion projector, obtains heating and high voltage supply from satellite power supply, and therefore native system has structure simply, is easy to the feature realized.
Accompanying drawing explanation
Fig. 1 is the structural representation of control system of the present invention.
Fig. 2 is the schematic diagram of control system of the present invention.
Wherein, 1-surface potential monitoring probe, 2-liquid metal ion projector, 3-control unit, 4-power subsystem unit.
Detailed description of the invention
To develop simultaneously embodiment below in conjunction with accompanying drawing, describe the present invention.
A kind of spacecraft current potential active control system of the present invention, as illustrated in fig. 1 and 2, comprises control unit, power subsystem unit, surface potential monitoring probe and liquid metal ion projector; Control unit is connected with power subsystem unit, surface potential monitoring probe and liquid metal ion projector respectively; Power subsystem unit is connected with the satellite power supply in spacecraft with liquid metal ion projector respectively;
Surface potential monitoring probe is fixed on spacecraft surface, for the current potential on Real-time Collection spacecraft surface, and electric potential signal is sent to control unit;
Liquid metal ion projector is fixed on spacecraft surface, liquid metal ion projector and the equal ground connection of spacecraft outside face, both mutual insulatings; Liquid metal ion projector is used for the spatial emission positive ion stream to spacecraft place, meanwhile, by the temperature signal in its interior metal pond to control unit;
Power subsystem unit is according to the power demands of liquid metal ion projector, power supply from satellite power supply is changed, and provides heating power supply according to the solid metallic of the control signal liquid towards metallic ion projector received from control unit or provide high voltage supply to extraction pole;
Control unit, according to the temperature signal from liquid metal ion transmitter receipt, transmits control signal to power subsystem unit, controls power subsystem unit and starts or terminate to power to the heating of solid metallic, makes the metal in metal pool maintain molten condition;
Control unit, according to the electric potential signal received from surface potential monitoring probe, transmits control signal to power subsystem unit: when electric potential signal is higher than preset potential, sends start high voltage supply control signal to power subsystem unit; When electric potential signal is equal to or less than preset potential, sends to power subsystem unit and terminate high voltage supply control signal, realize the ACTIVE CONTROL to Satellite surface potential thus.
Wherein, the ACTIVE CONTROL of control unit to Satellite surface potential comprises the control to positive potential and the control to negative potential:
When ACTIVE CONTROL is carried out to positive potential: as judgement Satellite surface potential V
sbe greater than default positive potential V
ltime, send to power subsystem unit and start high voltage supply control signal, power subsystem unit liquid towards metallic ion projector carries out high voltage supply, and liquid metal ion projector starts to launch positive ion stream, reduces the positive potential on spacecraft surface; As Satellite surface potential V
sreach or be less than default positive potential V
ltime, send to power subsystem unit and stop high voltage supply control signal, liquid metal ion projector stops launching positive ion stream.
When ACTIVE CONTROL is carried out to negative potential: as judgement Satellite surface potential V
sbe less than default negative potential lower limit V
2time, the ground connection of liquid metal ion projector disconnects by control unit, and carry out high voltage supply to power subsystem unit transmission beginning high voltage supply control signal power subsystem unit liquid towards metallic ion projector simultaneously, liquid metal ion projector starts to launch positive ion stream, because spacecraft surface is negative potential, the positive ion stream launched can get back to spacecraft surface under graviational interaction, because liquid metal ion projector ground connection disconnects, and and spacecraft surface insulation, launch positive ion stream and can't assemble electronics, therefore, the positive ion fallen after rise has neutralized the negative charge on spacecraft surface, which thereby enhance Satellite surface potential, as judgement Satellite surface potential V
sreach or surpass preset negative current potential V
3time, send to power subsystem unit and stop high voltage supply control signal, liquid metal ion projector stops launching positive ion stream.
Wherein, the negative potential lower limit V preset
2be taken as the minimum safe current potential that spacecraft surface does not occur to discharge; For avoiding liquid metal ion source frequently to start shooting, preset negative current potential V
3be greater than default negative potential lower limit V
2; In order to extend the service life of liquid metal ion source, the switching on and shutting down number of times of liquid metal ion source to be reduced, therefore preset negative current potential V as far as possible
3size to ensure that spacecraft is in the operational process of track shaded area as far as possible, its surface potential can not drop to default negative potential lower limit V again
2.
Liquid metal ion projector is carried in the voltage on extraction pole to control unit Real-time Feedback; The extraction pole on load voltage of feedback and the magnitude of voltage exported to power subsystem unit compare by control unit, once judge whether power subsystem unit is in normal working.
Control unit is also connected with the satellite power supply of spacecraft, for powering to self and surface potential monitoring probe.
Control unit is also connected with the switching on and shutting down control convenience of spacecraft, for receiving the switching on and shutting down signal of spacecraft, after receiving the starting-up signal of spacecraft, just transmits control signal to power subsystem unit.
Control unit is also connected with the communication bus of spacecraft respectively, and the electric potential signal on spacecraft surface is uploaded to spacecraft.
Liquid metal ion projector current potential ACTIVE CONTROL certification testing is illustrated:
Control electric spacecraft surface positive potential for liquid metal ion projector, devise a kind of control system based on indium liquid metal ion projector.During the work of indium liquid metal ion projector current potential ACTIVE CONTROL, the first cut-in voltage of control system be the heating power supply of 30V by liquid metal heating between to 180 ~ 200 DEG C, by surface potential monitoring probe monitoring surface potential, when surface potential is greater than presetting potential, control system opening point ignition source, actual ignition voltage <8kV, lights a fire successfully, real-world operation voltage <7kV; Monitoring ion energy by mass spectrograph is 5 ~ 10keV, and single projector ion beam current is 10 ~ 100 μ A, and during exemplary operation electric current 20 μ A, operating voltage is 6kV.By detecting surface potential in real time, through system analysis process, controlling the power-off of igniting high tension supply when surface potential drops to presetting potential, liquid metal ion projector cutting out, thus realizes the ACTIVE CONTROL of effects on surface positive potential.
For controlling the reliability of spacecraft surface positive potential in this control system of ground validation, in the vacuum system that solar simulator is housed, indium liquid metal ion projector potential active control device is installed, as simple analog space environment Spacecraft charging current potential active control experiment.Concise and to the point control process is as follows:
1) open liquid metal ion projector heating power supply by control unit, make liquid metal temperature reach the range of temperatures of design, now detect that liquid metal ion emitter temperature is 185 DEG C;
2) open the charging of solar simulator space environmental simulation, detect surface potential in real time, preset voltage is 0V, being charged to maximum potential, not comparing with presetting potential for simulating most harsh environment.
3) when surface potential detection reaches+40V, control unit opens the work of liquid metal ion projector.During voltage 5kV, liquid metal ion projector is lighted a fire, and during extraction pole voltage 6kV, detecting transmitter current is 20 μ A;
4) through about 5 ~ 6 minutes, detect that surface potential is 0.4V;
5) when detecting that surface potential is 0V, the high voltage supply unit that control unit controls power subsystem unit is closed, and liquid metal ion projector cuts out, and realizes the ACTIVE CONTROL of surface potential.
By above citing and verification experimental verification be example, illustrate that this system effectively can realize the ACTIVE CONTROL of Satellite surface potential.
In sum, these are only preferred embodiment of the present invention, be not intended to limit protection scope of the present invention.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (7)
1. a spacecraft current potential active control system, is characterized in that, comprises control unit, power subsystem unit, surface potential monitoring probe and liquid metal ion projector; Described control unit is connected with power subsystem unit, surface potential monitoring probe and liquid metal ion projector respectively; Described power subsystem unit is connected with the satellite power supply in spacecraft with liquid metal ion projector respectively;
Described surface potential monitoring probe is fixed on spacecraft surface, for the current potential on Real-time Collection spacecraft surface, and electric potential signal is sent to described control unit;
Described liquid metal ion projector is fixed on spacecraft surface, liquid metal ion projector and the equal ground connection of spacecraft outside face, both mutual insulatings; Liquid metal ion projector is used for the spatial emission positive ion stream to spacecraft place, meanwhile, by the temperature signal in its interior metal pond to described control unit;
Described power subsystem unit is according to the power demands of described liquid metal ion projector, power supply from satellite power supply is changed, and provides the extraction pole of heating power supply or liquid towards metallic ion projector to provide high voltage supply according to the solid metallic of the control signal liquid towards metallic ion projector received from control unit;
Described control unit, according to the temperature signal from liquid metal ion transmitter receipt, transmits control signal to described power subsystem unit, controls power subsystem unit and starts or terminate to power to the heating of solid metallic, makes the metal in metal pool maintain molten condition;
Described control unit, according to the electric potential signal received from described surface potential monitoring probe, transmits control signal to described power subsystem unit: when electric potential signal is higher than preset potential scope, sends start high voltage supply control signal to power subsystem unit; When electric potential signal is equal to or less than preset potential scope, sends to power subsystem unit and terminate high voltage supply control signal, realize the ACTIVE CONTROL to Satellite surface potential thus.
2. a kind of spacecraft current potential active control system according to claim 1, it is characterized in that, the ACTIVE CONTROL of described control unit to Satellite surface potential comprises the control to positive potential and the control to negative potential:
When ACTIVE CONTROL is carried out to positive potential: as judgement Satellite surface potential V
sbe greater than default positive potential V
ltime, send to described power subsystem unit and start high voltage supply control signal; As Satellite surface potential V
sreach or be less than default positive potential V
ltime, send to described power subsystem unit and stop high voltage supply control signal;
When ACTIVE CONTROL is carried out to negative potential: as judgement Satellite surface potential V
sbe less than default negative potential lower limit V
2time, the ground connection of liquid metal ion projector disconnects by control unit, and sends beginning high voltage supply control signal to described power subsystem unit simultaneously; As judgement Satellite surface potential V
sreach or surpass preset negative current potential V
3time, send to described power subsystem unit and stop high voltage supply control signal;
Wherein, described default negative potential lower limit V
2be taken as the minimum safe current potential that spacecraft surface does not occur to discharge; Described preset negative current potential V
3be greater than default negative potential lower limit V
2.
3. a kind of spacecraft current potential active control system according to claim 1, it is characterized in that, the metal in described liquid metal ion projector selects indium metal.
4. a kind of spacecraft current potential active control system according to claim 2, it is characterized in that, described liquid metal ion projector is carried in the voltage on the extraction pole of liquid metal ion projector to control unit Real-time Feedback; The extraction pole on load voltage of feedback and the described magnitude of voltage exported to power subsystem unit compare by described control unit, once judge whether power subsystem unit is in normal working.
5. a kind of spacecraft current potential active control system according to claim 1, it is characterized in that, described control unit is also connected with the satellite power supply of spacecraft, for powering to self and surface potential monitoring probe.
6. a kind of spacecraft current potential active control system according to claim 1, it is characterized in that, described control unit is also connected with the switching on and shutting down control convenience of spacecraft, for receiving the switching on and shutting down signal of spacecraft, after receiving the starting-up signal of spacecraft, just start to control power subsystem unit.
7. a kind of spacecraft current potential active control system according to claim 1, it is characterized in that, 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.
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| CN105923173A (en) * | 2016-06-08 | 2016-09-07 | 中国空间技术研究院 | GEO satellite external multilayer thermal insulation assembly earthing system and method |
| CN106927069A (en) * | 2017-03-29 | 2017-07-07 | 北京卫星环境工程研究所 | Spacecraft current potential autonomous control membrane structure |
| CN107979910A (en) * | 2017-11-29 | 2018-05-01 | 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 |
| CN109319172A (en) * | 2018-09-28 | 2019-02-12 | 兰州空间技术物理研究所 | A kind of spacecraft is in track surface charged effect control method |
| 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 |
| 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 |
| CN114325041A (en) * | 2021-12-09 | 2022-04-12 | 兰州空间技术物理研究所 | Space station active potential control system and ground simulation test method thereof |
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| 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 |
| CN114325041A (en) * | 2021-12-09 | 2022-04-12 | 兰州空间技术物理研究所 | Space station active potential control system and ground simulation test method thereof |
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