CN106697338A - Spacecraft potential active control method based on neutral gas release - Google Patents
Spacecraft potential active control method based on neutral gas release Download PDFInfo
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- CN106697338A CN106697338A CN201510416459.4A CN201510416459A CN106697338A CN 106697338 A CN106697338 A CN 106697338A CN 201510416459 A CN201510416459 A CN 201510416459A CN 106697338 A CN106697338 A CN 106697338A
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- spacecraft
- neutral gas
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- control method
- current potential
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Abstract
The invention discloses a spacecraft potential active control method based on neutral gas release. The spacecraft potential active control method based on the neutral gas release comprises the following steps of connecting a neutral gas cylinder, a deflating solenoid valve and a spray pipe with each other through pipelines in sequence so that neutral gas flows to the spray pipe through the deflating solenoid valve; enabling the spray pipe to approach and to be aligned with a high voltage charged part of a spacecraft and generating townsend discharge under a strong electric field which is formed by the charged part and a surrounding space plasma environment; electrically connecting the solenoid valve with a potential probe through a control circuit; enabling the probe to be positioned on the surface of the charged part and to monitor the potential; and enabling the probe and the control circuit to monitor the potential in real time so as to control the deflating solenoid valve to be opened and closed. The spacecraft potential active control method based on the neutral gas release has the advantages that the effectiveness of the control method is high, the control method is simple and novel, and the kilo-volt negative voltage of the spacecraft in the space environment can be instantaneously reduced to a safe level through a plasma generated by townsend discharge of low voltage neutral gas in the strong electric field.
Description
Technical field
The invention belongs to spacecraft control of Electric potentials and protection Design technical field, and in particular to during one kind is based on
Property gas release spacecraft potential control method.
Background technology
Space motion spacecraft and around plasma, high energy charged particles, magnetic field and sun spoke
The interaction of environmental factor such as penetrate, cause electric charge to be accumulated on spacecraft, make spacecraft and space etc.
There are relative potentials between gas ions or between spacecraft different parts poor.When potential difference is too high, can cause
Electrostatic discharge event occurs, and disturbs spacecraft and ground communications, or even cause spacecraft flight task
Failure；If additionally, using static discharge, spacecraft surfacing can be made to produce physical damnification,
Cause its deterioration.
[1] at present, the method for spacecraft current potential is controlled to be generally divided into two classes：One class is passive type control,
One class is active control.Passive type controls (Lai S T.A Critical Overview on
Spacecraft Charging Mitigation Methods[J].IEEE Transactions on
Plasma Science,2003,V31(6):1118-1124) include that point discharge method, secondary electron suppress
Band electrical method；(Zhang Shufeng, Lu Runxi spacecraft active potential controls .2008 are measured for active control
With test seminar collection of thesis [C] .2008:233-236) include launching electronics beam, launching electronics beam,
Transmitting low-energy plasma beam etc..The several ways of passive type control are specifically described as follows：
1st, point discharge method
Metal tip is inserted on the charged structures body of spacecraft, it is sophisticated when structure current potential is raised
Electric field also strengthens therewith, and when electric-field enhancing is to certain value, metal tip will produce field emission,
Excess electron is discharged and makes the reduction of conductive surface current potential.
2nd, secondary electron suppresses band electrical method
The secondary electron yield δ of material is defined as, when material is bombarded by incoming particle, swashing
The secondary electron of hair and the ratio of number of incoming particle.When spacecraft surface uses secondary system
Number (δ higher>1) during material, when being bombarded by incident electron, the negative electricity that secondary electron is taken away
Lotus and the charge cancellation of spacecraft surface accumulation, reach the purpose for reducing current potential.
The several ways of active control are specifically described as follows：
1st, launching electronics beam
Because electronics has taken away negative electrical charge, spacecraft positively charged will be made or make the negative of spacecraft surface institute band
Electric potential portion discharges or discharges completely.The degree of electric discharge depends on the environmental condition of line, energy and surrounding.
But electronic beam current crosses conference and causes the inequality of satellite to charge.Therefore, the efficiency comparison of this discharge mode
It is low.
2nd, ion beam is launched
Intuitively see, transmitting ion beam can make the negative potential of satellite surface more negative, but, in SCATHA
In the experiment of satellite observe, launch low energy ion beam can also make the negative potential of satellite surface discharge (by
Attracted to return to satellite surface by negative potential in low energy ion, neutralized negative potential).
3rd, low-energy plasma beam is launched
This radiation pattern electron beam more single than transmitting or single low energy ion beam more effectively make
The negative electrical charge of satellite surface bleeds off.This phenomenon is confirmed on later ATS-6 satellites.Also by
Later synchronous satellite DSCS Charge controlleds experiment is confirmed.
Though above-mentioned each method is no lack of the case of successful Application, there is certain application limitation, and be based on
The spacecraft current potential Active Control Method validity of neutral gas release is high, simple easily operated, can
Significantly reduce the current potential of spacecraft.
The content of the invention
By unremitting research, inventors have surprisingly discovered that using the release of neutral gas and right
The control of jet speed, significantly reduces the current potential of spacecraft.It is therefore an object of the present invention to utilize
A kind of Townsend model of neutral gas low pressure discharge, there is provided spacecraft current potential based on neutral gas release
Active Control Method, by spacecraft control of Electric potentials in level of security.
Technical scheme is as follows：
A kind of spacecraft current potential Active Control Method based on neutral gas release, comprises the following steps：
1) gas cylinder of neutral gas, pressure-releasing electromagnetic valve and jet pipe are passed sequentially through into gas piping connection, is made
The neutral gas for being stored in gas cylinder flows to jet pipe by pressure-releasing electromagnetic valve；Jet pipe is close to and is directed at spacecraft
High-voltage live parts；The neutral gas that jet pipe sprays is in high-voltage live parts and ambient space plasma ring
There is Townsend avalanche under the highfield that border is formed；Pressure-releasing electromagnetic valve is carried out by controlling circuit with potential probes
Electrical connection, potential probes are located at the surface of spacecraft high-voltage live parts and current potential are monitored, current potential
Probe and control circuit carry out real-time monitoring, the electricity that potential probes will be monitored to the current potential of high-voltage live parts
Pressure passes to control circuit in the way of electric signal, unlatching and closure for controlling electromagnetic release valve.
Wherein, neutral gas is inert gas, including helium, argon gas and neon etc..
Wherein, jet pipe is Laval nozzle.
Wherein, gas injection speed is supersonic speed.
Wherein, neutral gas is used for the gas that gesture stability or boost motor are produced from spacecraft.
Wherein, jet pipe remains 10cm with the distance of high-voltage live parts.
Wherein, when potential probes monitor that the voltage of spacecraft high-voltage live parts exceedes safe threshold,
Control circuit controling electromagnetism vent valve is opened, and high-voltage live parts is discharged by jet, until current potential is visited
Pin monitors that the current potential of high-voltage live parts drops to when below level of security, and potential probes pass electric signal
Control circuit is passed, control circuit controling electromagnetism vent valve is closed, and stops jet, potential probes and control
Circuit carries out real-time monitoring again to the current potential of high-voltage live parts.
Compared with prior art, the spacecraft current potential Active Control Method validity based on neutral gas release
Height, it is simple novel, and neutral gas can come from spacecraft for gesture stability or the gas of boost motor generation
Body, during such practical application the method control spacecraft current potential, it is not necessary to carry a large amount of neutral gases, favorably
In the weight for mitigating spacecraft.By neutral gas, the low pressure Townsend avalanche in highfield is produced this method
Plasma, the negative voltage moment of thousands of volts of spacecraft band can be reduced to level of security,
Brief description of the drawings
Fig. 1 is the schematic diagram of the spacecraft current potential active control system based on neutral gas release of the invention
Wherein, 1- gas cylinders；2- pressure-releasing electromagnetic valves；3- jet pipes；4- control systems；5- potential probes；
The high-voltage live parts of 6- spacecrafts.
Fig. 2 shows that the spacecraft current potential Active Control Method based on neutral gas release of the invention is carried out
Active discharge control when high-voltage live parts voltage with discharge time graph of a relation.
Specific embodiment
The spacecraft current potential active control based on neutral gas release of the invention is entered below in conjunction with the accompanying drawings
Row is further illustrated, what the explanation was merely exemplary, it is no intended to limit the scope of the invention.
Fig. 1 is the signal of the spacecraft current potential active control system based on neutral gas release of the invention
Figure.The control system of the method includes gas cylinder 1, electromagnetic release valve 2, jet pipe 3, control circuit 4, electricity
Position and needs to carry out the spacecraft high-voltage live parts 6 of control of Electric potentials, the high-voltage live parts probe 5
Connect with spacecraft structure body phase.
In a specific embodiment, when implementing control, helium gas cylinder 1, pressure-releasing electromagnetic valve 2 and Bearing score
You are connected jet pipe 3 by gas piping, the neutral gas for being stored in gas cylinder is passed through pressure-releasing electromagnetic valve stream 2
To Laval nozzle 3；Laval nozzle 3 keeps 10cm and is directed at high pressure belt with high-voltage live parts 6
Electric part 6；Laval nozzle 3 sprays helium atmosphere with supersonic speed, and the helium atmosphere of ejection is in high pressure belt
There is low pressure Townsend avalanche under the highfield that electric part 6 is formed with ambient space plasma environment；Put
Used between pneumoelectric magnet valve 2, control circuit 4 and the three of potential probes 5 and electrically connected, potential probes 5
In charging member surface, the voltage of monitoring is passed into control circuit 4 in the way of electric signal, for controlling
The unlatching of electromagnetic release valve processed 2 and closure.
Spacecraft interacts when space environment is run with ambient space plasma, often makes boat
The negative electricity of kilovolt on its device part band.Present invention control spacecraft current potential is introduced below in conjunction with accompanying drawing 1
Specific steps.
Step 1：When potential probes 5 monitor that the voltage of spacecraft high-voltage live parts 6 exceedes safety valve
During value (safe threshold of solar array such as is set into positive and negative 40V), potential probes 5 transmit electric signal
Open to control circuit 4, the control control electromagnetic release valve 2 of circuit 4, the helium atmosphere of helium gas cylinder 1
Laval nozzle 3 is diffused into by vent valve 2 and gas piping, and to the jet of high-voltage live parts 6.
Helium atmosphere occurs under the highfield that high-voltage live parts 6 and ambient space plasma environment are formed
Townsend avalanche forms plasma, so as to formation etc. between Laval nozzle 3 and high-voltage live parts 6
Ion body region.
Step 2：Helium atmosphere ionizes ion in the plasma to be formed by by high-voltage live parts 6
Negative potential attracts, and neutralizes negative potential, so that the negative potential reduction of high-voltage live parts 6；And plasma
Electronics in body is repelled by the negative potential of high-voltage live parts 6, away from high-voltage live parts 6, and remote
Collided with helium during, make the helium atmosphere of ejection that Townsend avalanche further to occur, ionize shape
Into more plasmas.So ion is used for neutralizing negative potential, and electronics is used for ionization by collision helium atmosphere,
Go round and begin again.
Step 3：Until potential probes 5 monitor that the current potential of high-voltage live parts 6 drops to level of security
When following, electric signal is passed to control circuit 4 by potential probes 5, and the control control electromagnetism of circuit 4 is deflated
Valve 2 is closed, and stops jet.
Step 4：Potential probes and control circuit are returned to real-time monitoring pattern.When again spacecraft occurs height
During pressure zone electricity, control method of the invention is by repeat step 1,2,3.
The electric discharge of present embodiment reduces the effect of current potential as shown in Fig. 2 Fig. 2 shows base of the invention
Electrification in high voltage when active discharge is controlled is carried out in the spacecraft current potential Active Control Method of neutral gas release
The voltage of part with discharge time graph of a relation.Wherein, transverse axis represents discharge time, and the longitudinal axis represents structure
Bulk voltage, in the τ times after electric discharge starts, voltage decays to U from initial U0.
Although giving detailed description to specific embodiment of the invention above and illustrating, should refer to
It is bright, we can according to it is of the invention conception above-mentioned implementation method is carried out it is various it is equivalent change and repair
Change, the function produced by it still without departing from specification and accompanying drawing covered it is spiritual when, all should this
Within the protection domain of invention.
Claims (7)
1. a kind of spacecraft current potential Active Control Method based on neutral gas release, comprises the following steps：
The gas cylinder of neutral gas, pressure-releasing electromagnetic valve and jet pipe are passed sequentially through into gas piping connection, makes storage
Jet pipe is flowed to by pressure-releasing electromagnetic valve in the neutral gas of gas cylinder；Jet pipe is close to and is directed at the high pressure of spacecraft
Charging member；The neutral gas that jet pipe sprays is in high-voltage live parts and ambient space plasma environment shape
Into highfield under there is Townsend avalanche；Pressure-releasing electromagnetic valve is electrically connected by controlling circuit with potential probes
Connect, potential probes are located at the surface of spacecraft high-voltage live parts and current potential are monitored, potential probes
Carry out real-time monitoring to the current potential of high-voltage live parts with control circuit, the voltage that potential probes will be monitored with
The mode of electric signal passes to control circuit, unlatching and closure for controlling pressure-releasing electromagnetic valve.
It is 2. as claimed in claim 1 to be based on the spacecraft current potential Active Control Method that neutral gas discharges,
Wherein, neutral gas is inert gas, including helium, argon gas and neon.
It is 3. as claimed in claim 1 to be based on the spacecraft current potential Active Control Method that neutral gas discharges,
Wherein, jet pipe is Laval nozzle.
4. as described in claim any one of 1-3 based on neutral gas release spacecraft current potential actively
Control method, wherein, gas injection speed is supersonic speed.
5. as described in claim any one of 1-3 based on neutral gas release spacecraft current potential actively
Control method, wherein, neutral gas is used for the gas that gesture stability or boost motor are produced from spacecraft.
6. as described in claim any one of 1-3 based on neutral gas release spacecraft current potential actively
Control method, wherein, jet pipe remains 10cm with the distance of high-voltage live parts.
7. as described in claim any one of 1-3 based on neutral gas release spacecraft current potential actively
Control method, wherein, when potential probes monitor that the voltage of spacecraft high-voltage live parts exceedes safety valve
During value, control circuit controling electromagnetism vent valve is opened, and high-voltage live parts is discharged by jet, until
Potential probes monitor that the current potential of high-voltage live parts drops to when below level of security, and potential probes are by electricity
Signal transmission closes to control circuit, control circuit controling electromagnetism vent valve, stops jet, potential probes
Real-time monitoring is carried out again to the current potential of high-voltage live parts with control circuit.
Priority Applications (1)
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| CN201510416459.4A CN106697338B (en) | 2015-07-15 | 2015-07-15 | Spacecraft current potential Active Control Method based on neutral gas release |
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| CN201510416459.4A CN106697338B (en) | 2015-07-15 | 2015-07-15 | Spacecraft current potential Active Control Method based on neutral gas release |
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| CN106697338B CN106697338B (en) | 2018-10-19 |
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Cited By (3)
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| CN107979910A (en) * | 2017-11-29 | 2018-05-01 | 中国人民解放军陆军工程大学 | Dielectric material surface potential Active Control Method under high vacuum environment |
| CN109041554A (en) * | 2018-06-01 | 2018-12-18 | 芯创智（北京）微电子有限公司 | The method and device of electronic reliability is protected when a kind of ionizing particle bombards |
| CN111177910A (en) * | 2019-12-23 | 2020-05-19 | 西安空间无线电技术研究所 | Numerical simulation method for inducing spacecraft to discharge by releasing neutral gas |
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| CN103786904A (en) * | 2013-12-17 | 2014-05-14 | 兰州空间技术物理研究所 | Spacecraft structural potential active control system and control method |
| CN104260905A (en) * | 2014-09-05 | 2015-01-07 | 兰州空间技术物理研究所 | Method for actively controlling surface electric potential of spacecraft |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107979910A (en) * | 2017-11-29 | 2018-05-01 | 中国人民解放军陆军工程大学 | Dielectric material surface potential Active Control Method under high vacuum 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 |
| CN109041554A (en) * | 2018-06-01 | 2018-12-18 | 芯创智（北京）微电子有限公司 | The method and device of electronic reliability is protected when a kind of ionizing particle bombards |
| CN111177910A (en) * | 2019-12-23 | 2020-05-19 | 西安空间无线电技术研究所 | Numerical simulation method for inducing spacecraft to discharge by releasing neutral gas |
| CN111177910B (en) * | 2019-12-23 | 2023-03-21 | 西安空间无线电技术研究所 | Numerical simulation method for inducing spacecraft to discharge by releasing neutral gas |
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| CN106697338B (en) | 2018-10-19 |
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Granted publication date: 20181019 Termination date: 20210715 |