CN106697338B - Spacecraft current potential Active Control Method based on neutral gas release - Google Patents
Spacecraft current potential Active Control Method based on neutral gas release Download PDFInfo
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- CN106697338B CN106697338B CN201510416459.4A CN201510416459A CN106697338B CN 106697338 B CN106697338 B CN 106697338B CN 201510416459 A CN201510416459 A CN 201510416459A CN 106697338 B CN106697338 B CN 106697338B
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- spacecraft
- current potential
- neutral gas
- gas
- live parts
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Abstract
The invention discloses the spacecraft current potential Active Control Method discharged based on neutral gas, neutral gas gas cylinder, venting solenoid valve and jet pipe successively piping connection are made neutral gas pass through venting solenoid valve and flow to jet pipe by this method；Jet pipe is close and is directed at the high-voltage live parts of spacecraft and Townsend avalanche occurs under the highfield that charging member and ambient space plasma environment are formed；Solenoid valve is electrically connected by control circuit and potential probes, and probe is located at the surface of charging member and is monitored to current potential, and probe and control circuit monitor current potential in real time, the unlatching for controlling venting solenoid valve and closure.This control method validity is high, simple novel, by the low pressure neutral gas plasma that Townsend avalanche generates in highfield, can thousands of volt negative voltage moments of the spacecraft band in space environment be reduced to level of security.
Description
Technical field
The invention belongs to spacecraft control of Electric potentials and protection Design technical field, and in particular to one kind is released based on neutral gas
The spacecraft potential control method put.
Background technology
Space motion spacecraft and around the environment such as plasma, high energy charged particles, magnetic field and solar radiation because
The interaction of element, causes charge to be accumulated on spacecraft, makes between spacecraft and space plasma or spacecraft different parts
Between relative potentials occur poor.When potential difference is too high, electrostatic discharge event can be caused, interfere spacecraft and ground communications,
Even cause the failure of spacecraft flight task；In addition, if using static discharge, then it can make spacecraft surfacing generation
Reason damage, leads to its deterioration.
[1] currently, the method for control spacecraft current potential is generally divided into two classes：One kind is passive type control, and one kind is actively
Formula controls.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 point discharge method, secondary electron inhibition band electrical method；(Zhang Shufeng, Lu Runxi spacecrafts are actively electric for active control
Position control .2008 meterings and test seminar collection of thesis [C] .2008:233-236) include launching electronics beam, transmitting electricity
Beamlet, transmitting low-energy plasma beam etc..The several ways of passive type control are specifically described as follows：
1, point discharge method
Be inserted into metal tip on the charged structures body of spacecraft, when structure current potential increases, the electric field at tip also with
Enhancing, when electric-field enhancing is to certain value, metal tip just will produce field emission, and excess electron is discharged and makes conductor table
Face current potential reduces.
2, secondary electron inhibits band electrical method
The secondary electron yield δ of material is defined as when material is bombarded by incoming particle, the secondary electricity of excitation
The ratio of number of son and incoming particle.When spacecraft surface uses the higher (δ of secondary electron yield>1) when material, when by
When being bombarded to incident electron, the charge cancellation of negative electrical charge and the accumulation of spacecraft surface that secondary electron is taken away reaches reduction current potential
Purpose.
The several ways of active control are specifically described as follows：
1, launching electronics beam
Since electronics has taken away negative electrical charge, spacecraft will be kept positively charged or make the negative electricity bit position of spacecraft surface institute band
Electric discharge or completely electric discharge.The degree of electric discharge depends on the environmental condition of line, energy and surrounding.But electronic beam current is crossed conference and is caused
The inequality of satellite charges.Therefore, the efficiency of this discharge mode is relatively low.
2, emit ion beam
It intuitively sees, transmitting ion beam can make the negative potential of satellite surface more negative, still, in the experiment of SCATHA satellites
It observes, emitting the ion beam of low energy can also make the negative potential of satellite surface discharge (since low energy ion is returned by negative potential attraction
Satellite surface is returned, negative potential has been neutralized).
3, emit low-energy plasma beam
This radiation pattern more effectively makes satellite surface than emitting single electron beam or single low energy ion beam
Negative electrical charge bleed off.This phenomenon is confirmed on later ATS-6 satellites.Also by later synchronous satellite DSCS charge controls
System experiment is confirmed.
Though above-mentioned each method is no lack of the case of successful application, there is certain application limitation, and is based on neutral gas
The spacecraft current potential Active Control Method validity of release is high, simple easily operated, can significantly reduce the current potential of spacecraft.
Invention content
By unremitting research, inventors have surprisingly discovered that using the release of neutral gas and to jet rate
Control, significantly reduce the current potential of spacecraft.Therefore, the purpose of the present invention is to the soup using neutral gas low pressure discharge
Gloomy model is provided a kind of spacecraft current potential Active Control Method discharged based on neutral gas, spacecraft control of Electric potentials is being pacified
It is complete horizontal.
Technical scheme is as follows：
A kind of spacecraft current potential Active Control Method based on neutral gas release, includes the following steps：
1) gas cylinder of neutral gas, venting solenoid valve and jet pipe are passed sequentially through gas piping to connect, makes to be stored in gas cylinder
Neutral gas jet pipe is flowed to by venting solenoid valve；Jet pipe is close and is directed at the high-voltage live parts of spacecraft；Jet pipe sprays
Neutral gas Townsend avalanche occurs under the highfield that high-voltage live parts and ambient space plasma environment are formed；It deflates
Solenoid valve is electrically connected by control circuit and potential probes, and potential probes are located at the surface of spacecraft high-voltage live parts simultaneously
Current potential is monitored, potential probes and control circuit monitor the current potential of high-voltage live parts in real time, and potential probes will
The voltage of monitoring passes to control circuit in a manner of electric signal, the unlatching for controlling electromagnetic release valve and closure.
Wherein, neutral gas is inert gas, including helium, argon gas and neon etc..
Wherein, jet pipe is Laval nozzle.
Wherein, gas injection rate is supersonic speed.
Wherein, the gas that neutral gas is generated from spacecraft for gesture stability or boost motor.
Wherein, jet pipe remains 10cm at a distance from high-voltage live parts.
Wherein, when potential probes monitor that the voltage of spacecraft high-voltage live parts is more than safe threshold, control circuit
It controls electromagnetic release valve to open, so that high-voltage live parts is discharged by jet, until potential probes monitor high-voltage live parts
Current potential when dropping to level of security or less, electric signal is passed to control circuit by potential probes, and control circuit control electromagnetism is put
Air valve is closed, and stops jet, potential probes and control circuit monitor the current potential of high-voltage live parts in real time again.
Compared with prior art, the spacecraft current potential Active Control Method validity based on neutral gas release is high, simply
Novelty, and neutral gas can come from spacecraft for the gas that gesture stability or boost motor generate, such practical application party
When method controls spacecraft current potential, it is not necessary to carry a large amount of neutral gases, be conducive to the weight for mitigating spacecraft.This method passes through neutrality
The gas plasma that low pressure Townsend avalanche generates in highfield, can drop the negative voltage moment of thousands of volts of spacecraft band
As low as level of security,
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 present invention
Wherein, 1- gas cylinders；2- venting solenoid valves；3- jet pipes；4- control systems；5- potential probes；The height of 6- spacecrafts
Pressure zone electrical components.
Fig. 2 shows that the spacecraft current potential Active Control Method of the present invention discharged based on neutral gas carries out active discharge
When control the voltage of high-voltage live parts with discharge time relational graph.
Specific implementation mode
The spacecraft current potential active control based on neutral gas release of the present invention is carried out below in conjunction with the accompanying drawings further
Illustrate, which is only exemplary, it is no intended to limit the scope of the invention.
Fig. 1 is the schematic diagram of the spacecraft current potential active control system based on neutral gas release of the present invention.This method
Control system include gas cylinder 1, electromagnetic release valve 2, jet pipe 3, control circuit 4, potential probes 5 and need carry out control of Electric potentials
Spacecraft high-voltage live parts 6, which is connected with spacecraft structure body.
In a specific embodiment, when implementing control, helium gas cylinder 1, venting solenoid valve 2 and Laval nozzle 3 pass through
Gas piping connects, and so that the neutral gas for being stored in gas cylinder is passed through venting solenoid valve stream 2 and arrives Laval nozzle 3；Laval nozzle 3
10cm is kept with high-voltage live parts 6 and is directed at high-voltage live parts 6；Laval nozzle 3 sprays helium atmosphere, spray with supersonic speed
Under the highfield that high-voltage live parts 6 and ambient space plasma environment are formed low pressure Townsend occurs for the helium atmosphere gone out
Electric discharge；Using being electrically connected between venting solenoid valve 2, control circuit 4 and 5 three of potential probes, potential probes 5 are located at charging member
The voltage of monitoring is passed to control circuit 4 by surface in a manner of electric signal, unlatching for controlling electromagnetic release valve 2 and is closed
It closes.
Spacecraft interacts with ambient space plasma when space environment is run, often makes spacecraft component
Take the negative electricity of kilovolt.The specific steps of present invention control spacecraft current potential are introduced below in conjunction with attached drawing 1.
Step 1：When potential probes 5 monitor spacecraft high-voltage live parts 6 voltage be more than safe threshold (such as by the sun
The safe threshold of windsurfing is set as positive and negative 40V) when, electric signal is passed to control circuit 4 by potential probes 5, and control circuit 4 controls electricity
Magnetic vent valve 2 is opened, and the helium atmosphere of helium gas cylinder 1 is diffused into Laval nozzle 3 by vent valve 2 and gas piping, and to
6 jet of high-voltage live parts.Helium atmosphere is under the highfield that high-voltage live parts 6 and ambient space plasma environment are formed
Townsend avalanche occurs and forms plasma, to form plasma slab between Laval nozzle 3 and high-voltage live parts 6
Domain.
Step 2：Helium atmosphere, which ionizes the ion in the plasma to be formed, to be inhaled by the negative potential of high-voltage live parts 6
Draw, negative potential is neutralized, to make the negative potential of high-voltage live parts 6 reduce；And the electronics in plasma is by electrification in high voltage portion
The negative potential of part 6 repels, and far from high-voltage live parts 6, and is colliding with helium far from during, is making the helium gas of ejection
Townsend avalanche further occurs for body, and ionization forms more plasmas.Ion is used for neutralizing negative potential in this way, and electronics is used for touching
Ionized helium gas is hit, in cycles.
Step 3：Until when potential probes 5 monitor that the current potential of high-voltage live parts 6 drops to level of security or less, current potential
Electric signal is passed to control circuit 4 by probe 5, and control circuit 4 controls electromagnetic release valve 2 and closes, and stops jet.
Step 4：Potential probes and control circuit are returned to real-time monitoring pattern.When again electrification in high voltage occurs for spacecraft,
The control method of the present invention will repeat steps 1 and 2,3.
Present embodiment electric discharge reduce current potential effect as shown in Fig. 2, Fig. 2 show the present invention based on neutral gas
The spacecraft current potential Active Control Method of release carries out the voltage of high-voltage live parts when active discharge control with discharge time
Relational graph.Wherein, horizontal axis indicate discharge time, the longitudinal axis indicate structure bulk voltage, electric discharge start after the τ times in, voltage from
Initial U0 decays to U.
Although the detailed description and description of the specific embodiments of the present invention are given above, it should be noted that
We can carry out various equivalent changes and modification to the above embodiment according to the concept of the present invention, and generated function is made
It, should all be within protection scope of the present invention when with the spirit still covered without departing from specification and attached drawing.
Claims (6)
1. based on the spacecraft current potential Active Control Method of neutral gas release, include the following steps：
The gas cylinder of neutral gas, venting solenoid valve and jet pipe are passed sequentially through gas piping to connect, make the neutrality for being stored in gas cylinder
Gas flows to jet pipe by venting solenoid valve；Jet pipe is close and is directed at the high-voltage live parts of spacecraft；The neutrality that jet pipe sprays
Under the highfield that high-voltage live parts and ambient space plasma environment are formed Townsend avalanche occurs for gas；Venting solenoid valve
It is electrically connected by control circuit and potential probes, potential probes are located at the surface of spacecraft high-voltage live parts and to current potential
It is monitored, potential probes and control circuit monitor the current potential of high-voltage live parts in real time, and potential probes are by monitoring
Voltage passes to control circuit in a manner of electric signal, the unlatching for controlling venting solenoid valve and closure, when potential probes are supervised
When measuring the voltage of spacecraft high-voltage live parts more than safe threshold, control circuit controls electromagnetic release valve and opens, and passes through spray
Gas makes high-voltage live parts discharge, until potential probes monitor that the current potential of high-voltage live parts drops to level of security or less
When, electric signal is passed to control circuit by potential probes, and control circuit controls electromagnetic release valve and closes, and stops jet, and current potential is visited
Needle and control circuit monitor the current potential of high-voltage live parts in real time again.
2. the spacecraft current potential Active Control Method as described in claim 1 based on neutral gas release, wherein neutral gas
For inert gas.
3. the spacecraft current potential Active Control Method as described in claim 1 based on neutral gas release, wherein jet pipe is to draw
Wa Er jet pipes.
4. the spacecraft current potential Active Control Method as described in any one of claims 1-3 based on neutral gas release, wherein
Gas injection rate is supersonic speed.
5. the spacecraft current potential Active Control Method as described in any one of claims 1-3 based on neutral gas release, wherein
The gas that neutral gas is generated from spacecraft for gesture stability or boost motor.
6. the spacecraft current potential Active Control Method as described in any one of claims 1-3 based on neutral gas release, wherein
Jet pipe remains 10cm at a distance from high-voltage live parts.
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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 true CN106697338B (en) | 2018-10-19 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN109041554B (en) * | 2018-06-01 | 2020-03-24 | 芯创智（北京）微电子有限公司 | Method and device for protecting reliability of electronic device during ionizing particle bombardment |
| 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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| 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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| US8205838B2 (en) * | 2009-08-13 | 2012-06-26 | Moorer Jr Daniel F | Electrostatic spacecraft reorbiter |
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| CN102540127A (en) * | 2012-01-05 | 2012-07-04 | 北京东方计量测试研究所 | Calibration platform for space potential detector of low-orbit spacecraft |
| CN102781150A (en) * | 2012-07-23 | 2012-11-14 | 北京卫星环境工程研究所 | Component for autonomously controlling structural potential of spacecraft |
| CN102774511A (en) * | 2012-08-03 | 2012-11-14 | 北京卫星环境工程研究所 | Spacecraft potential active control device based on helicon wave plasma and application thereof |
| CN103770953A (en) * | 2013-12-17 | 2014-05-07 | 兰州空间技术物理研究所 | Active control device and method for spacecraft structure potential |
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