CN109319172A - A kind of spacecraft is in track surface charged effect control method - Google Patents
A kind of spacecraft is in track surface charged effect control method Download PDFInfo
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- CN109319172A CN109319172A CN201811140258.6A CN201811140258A CN109319172A CN 109319172 A CN109319172 A CN 109319172A CN 201811140258 A CN201811140258 A CN 201811140258A CN 109319172 A CN109319172 A CN 109319172A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/54—Protection against radiation
- B64G1/546—Protection against radiation shielding electronic equipment
Abstract
The invention discloses a kind of spacecrafts in track surface charged effect control method, it is primarily based on electron flux and Satellite surface potential relationship, and plasma temperature and Satellite surface potential relationship, the potential threshold that can be born according to spacecraft surface, it obtains flux threshold and temperature threshold passes through real-time monitoring electron flux and electron temperature in real-time control, can controlling potential active controller switch, achieve the purpose that surface potential control；What it is due to observation is electron flux and plasma temperature, and whether prediction spacecraft surface can reach potential threshold and carry out surface potential control according to this, rather than control of Electric potentials is carried out again after the accumulation of spacecraft surface reaches potential threshold after electronics and plasma, therefore response speed can be improved, and improve the stability and accuracy of spacecraft surface electrification active control.
Description
Technical field
The invention belongs to spacecraft space environmental effect protection technology fields, and in particular to a kind of spacecraft is in track surface band
Electrical effect control method.
Background technique
Magnetosphere magnetic storm/substorm can cause the violent disturbance of terrestrial space environment, and it is close all kinds of particle events, Thermosphere occur
Increase, ionospheric storm etc. are spent, spacecraft activity, communication and navigation system can be posed a serious threat.As hot plasma increases
Strong event, the energy that space hot plasma caused by this magnetospheric disturbance injects can be up to tens of keV, can cause satellite table
Face is charged to higher current potential, influences the safe and stable operation of satellite.Research shows that injection hot plasma electron flux and
Electron temperature respectively to the electrification of the spacecraft surface in shadow region and area of illumination have important influence [Davis, V.A.,
Mandell,M.J.,and Thomsen,M.F..Characterization of Magnetospheric Spacecraft
Charging Environments Using the LANL Magnetospheric Plasma Analyzer Data
Set.NASA/CR-2003-212745].After Expansion phase starts, the disturbance meeting of magnetosphere is so that plasma is heated rapidly
Be injected near geostationary orbit, and the injection of energy particle is energy non-dispersive (while increase suddenly), particle without
There is close contact in the time of dispersion injection with magnetosphere magnetic storm/substorm triggering.Magnetic storm time substorm event is different from isolated substorm,
Usually the energy density of Near-Earth magnetotail and level of stretch are relatively high under the conditions of magnetic storm, it is believed that substorm outburst is by middle magnetic tail
Magnetic Reconnection induces what ecto-entad developed, and it is more serious that energy particle injects event.
Spacecraft safe and stable operation is endangered since static discharge can occur for the higher current potential of spacecraft band, it is necessary to taken
Effect measure charges level to it and is protected and controlled.Existing Satellite surface potential control mainly has passive control and actively controls
Method processed.Passive control is to coat by grounding, or on spacecraft surface or wrap up one layer of antistatic film, in certain journey
Surface electrification is reduced on degree, but can not thoroughly reduce Satellite surface potential.Active control is developed in recent years
A kind of potential control method is fallen the charge discharging resisting that spacecraft surface accumulates by transmitting particle beam, but existing method is
1) it is monitored and is triggered by surface potential, but have retardance；2) current potential active control system clocked flip is set, cannot be timely responded to
The variation of environment；3) it is triggered by ground telemetering, due to the delay of signal transmission, the hysteresis quality of control is serious with family.
Summary of the invention
In view of this, the object of the present invention is to provide a kind of spacecrafts in track surface charged effect control method, it can be fast
Speed response spacecraft surface charged effect, and accurately control surface potential.
A kind of spacecraft includes the following steps: in track surface charged effect control method
Step 1, the electronics obtained under the plasma electron temperature for being radiated spacecraft surface and different energy sections in real time are logical
Measure summation；
Step 2, according to electron flux summation ∑ JiRelational expression between the structure current potential φ on spacecraft surface:
φ=- 1.359 × 10-12(∑Ji)2.03
Obtain the corresponding flux threshold of spacecraft potential threshold of setting；Wherein, JiFor the electron flux under different energy sections；
Step 3, according to the relational expression between plasma electron temperature and the structure current potential φ on spacecraft surface:
φ=- 2.4 × 10-7T2.51
Obtain the corresponding temperature threshold of spacecraft potential threshold of setting；In formula, T is plasma temperature；
Step 4 judges spacecraft in shadow region still in area of illumination:
If obtaining the electron flux summation of different energy sections in shadow region, judging whether it reaches flux threshold, if reached
It arrives, the booting of evoked potential active controller, emission current；After the electron flux summation is lower than flux threshold, evoked potential
Active controller shutdown；
If leaving track shadow region, judge whether plasma temperature reaches temperature threshold, if reached, evoked potential master
Movement controller booting, emission current；After plasma temperature is lower than temperature threshold, the shutdown of evoked potential active controller.
Preferably, the energy range of the space plasma obtained in real time is 5~100keV in the step 1.
Preferably, judging spacecraft in shadow region still in light by spacecraft battery battle array working condition in the step 4
According to area.
The invention has the following beneficial effects:
(1) present invention is primarily based on electron flux and Satellite surface potential relationship and plasma temperature and spacecraft
Surface potential relationship obtains flux threshold and temperature threshold, in real-time control according to the potential threshold that spacecraft surface can be born
In, pass through real-time monitoring electron flux and electron temperature, so that it may which controlling potential active controller switch reaches surface potential control
The purpose of system；What it is due to observation is electron flux and plasma temperature, and whether prediction spacecraft surface can reach electricity according to this
Position threshold value simultaneously carries out surface potential control, rather than after electronics and plasma after the accumulation of spacecraft surface reaches potential threshold
Control of Electric potentials is carried out again, therefore response speed can be improved, and improves the stability and standard of spacecraft surface electrification active control
True property；
(2) band risk Intelligentized method in surface of the invention may be implemented surface conductive environment automatic identification and do automatically
Corresponding active control switching on and shutting down movement out, therefore there is wider application range.
Detailed description of the invention
Fig. 1 is flow chart of the method for the present invention；
Fig. 2 is the structural schematic diagram that intelligent control method is charged on spacecraft surface of the invention.
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
A kind of spacecraft surface band electric control method of the invention, as shown in Figure 1, the electricity on spacecraft surface is arrived in detection irradiation
Sub- flux and plasma temperature；When spacecraft is located at shadow region, when electron flux is higher than preset threshold, evoked potential is actively
Controller booting, when electron flux is lower than preset threshold, the shutdown of evoked potential active controller；Spacecraft is located at area of illumination
When, when plasma temperature is higher than preset value, evoked potential active controller booting, when ion temperature is lower than default flux
When, the shutdown of evoked potential active controller.By electron flux and plasma temperature size and controlling potential master can also be carried out
Movement controller line emissive porwer, electron flux is bigger, and plasma temperature is higher, then line emissive porwer is bigger, is achieved in
Accurate control to Satellite surface potential.
A kind of in-orbit spacecraft surface band electric control method of the invention, is triggered using Space environment monitor real time data and is navigated
Its device surface potential active controller is run in due course carries out surface potential control, wherein the Space environment monitor device and electricity
Position active controller is fixed on the outer surface of spacecraft, and this method specifically comprises the following steps:
(1) by environment monitoring device, (such as electrostatic analyzer, silicon surface barrier solid probe and row time system composition, can
The electron flux measurement of realization plasma electron temperature and different energy sections) obtain range in real time as space 5~100keV etc.
Electron flux under gas ions electron temperature and different energy sections；Wherein, dividing for electronics energy section can be according to the sky of spacecraft carrying
Between plasma detection device performance determine；
(2) when spacecraft injection shadow region, according to it is different can electron flux summation under sections and spacecraft surface
Structure current potential φ between relational expression, obtain the corresponding flux threshold of potential threshold:
Wherein, relational expression be document [Davis, V.A., Mandell, M.J., and Thomsen,
M.F..Characterization of Magnetospheric Spacecraft Charging Environments
Using the LANL Magnetospheric Plasma Analyzer Data Set.NASA/CR-2003-212745] in
The method of introduction:
φ=- 1.359 × 10-12(∑Ji)2.03
In formula, φ is the structure current potential on spacecraft surface, J in formulaiFor the electron flux (cm under different energy sections-2/s/sr/
eV)。
It is assumed that Spacecraft charging to -500V threshold potential when to occur static discharge, then according to above-mentioned relation formula calculate
Obtaining the corresponding electron flux summation of potential threshold is 1.5 × 107cm-2/s/sr/eV；Then the electron flux summation is defined as leading to
Measure threshold value；
When electron flux reaches flux threshold -1.5 × 10 under different energy sections7cm-2When/s/sr/eV, evoked potential is actively
Controller booting；When it is different can under sections electron flux less than 1.5 × 107cm-2When/s/sr/eV, evoked potential active controller is closed
Machine；The electron flux threshold value preset under different energy sections can also be true according to the mission requirements of spececraft charging to maximum potential
It is fixed.
(3) when spacecraft injection area of illumination, according to the structure on plasma electron temperature and spacecraft surface electricity
Relational expression between the φ of position obtains the corresponding temperature threshold of potential threshold:
Wherein, relational expression be document [Davis, V.A., Mandell, M.J., and Thomsen,
M.F..Characterization of Magnetospheric Spacecraft Charging Environments
Using the LANL Magnetospheric Plasma Analyzer Data Set.NASA/CR-2003-212745] in
The method of introduction:
φ=- 2.4 × 10-7T2.51
In formula, T is plasma temperature (eV).
It is assumed that plasma electron is calculated to static discharge occurs when Spacecraft charging is to potential threshold--500V
Temperature is 5.16 × 103.7EV, then the temperature is temperature threshold.
When plasma electron temperature reaches 5.16 × 103When eV, the booting of evoked potential active controller；Work as plasma
Electron temperature is less than 5.16 × 103When eV, the shutdown of evoked potential active controller；Default plasma electron temperature threshold value can also
It is determined according to the mission requirements of spececraft charging to maximum potential.
(4) judge spacecraft in shadow region still in area of illumination by spacecraft battery battle array working condition:
If obtaining the electron flux summation of different energy sections in shadow region, judging whether it reaches flux threshold, if reached
It arrives, the booting of evoked potential active controller, emission current；After flux summation is lower than flux threshold, evoked potential active control
Device shutdown；
If leaving track shadow region, judge whether plasma temperature reaches temperature threshold, if reached, evoked potential master
Movement controller booting, emission current；After temperature is lower than temperature threshold, the shutdown of evoked potential active controller.
As shown in Fig. 2, realizing that the control system of the method for the present invention includes environment monitoring device, control unit and current potential active
Controller；Environment monitoring device and current potential active controller are separately fixed at spacecraft surface, are used for real-time space ambient electronic
Flux and plasma temperature variation, and monitoring signals are sent to control unit；Control unit to by electron flux and it is equal from
Daughter temperature is compared with flux threshold and temperature threshold respectively, and issues booting or shutdown control to current potential active controller
System instruction.Wherein, current potential active controller may be selected electron source type (to launching electronics) or plasma source type (launching electronics and
Ion).
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (3)
1. a kind of spacecraft is in track surface charged effect control method, which comprises the steps of:
Step 1, the electron flux obtained under the plasma electron temperature for being radiated spacecraft surface and different energy sections in real time are total
With；
Step 2, according to electron flux summation ∑ JiRelational expression between the structure current potential φ on spacecraft surface:
φ=- 1.359 × 10-12(∑Ji)2.03
Obtain the corresponding flux threshold of spacecraft potential threshold of setting；Wherein, JiFor the electron flux under different energy sections；
Step 3, according to the relational expression between plasma electron temperature and the structure current potential φ on spacecraft surface:
φ=- 2.4 × 10-7T2.51
Obtain the corresponding temperature threshold of spacecraft potential threshold of setting；In formula, T is plasma temperature；
Step 4 judges spacecraft in shadow region still in area of illumination:
If obtaining the electron flux summation of different energy sections in shadow region, judging whether it reaches flux threshold, if reached,
The booting of evoked potential active controller, emission current；After the electron flux summation is lower than flux threshold, evoked potential is actively
Controller shutdown；
If leaving track shadow region, judge whether plasma temperature reaches temperature threshold, if reached, evoked potential is actively controlled
Device booting processed, emission current；After plasma temperature is lower than temperature threshold, the shutdown of evoked potential active controller.
2. a kind of spacecraft as described in claim 1 is in track surface charged effect control method, which is characterized in that the step
In 1, the energy range of the space plasma obtained in real time is 5~100keV.
3. a kind of spacecraft as described in claim 1 is in track surface charged effect control method, which is characterized in that the step
In 4, judge spacecraft in shadow region still in area of illumination by spacecraft battery battle array working condition.
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Cited By (3)
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| CN110077629A (en) * | 2019-04-12 | 2019-08-02 | 北京空间飞行器总体设计部 | Utilize the method and system of artificial magnetic field shielding spacecraft part low-energy electron environment |
| CN110576984A (en) * | 2019-09-23 | 2019-12-17 | 燕山大学 | High-temperature protection equipment for aircraft |
| CN110579633A (en) * | 2019-07-29 | 2019-12-17 | 西安空间无线电技术研究所 | Space-based platform electronic collection system and method |
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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 |
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| US20040079744A1 (en) * | 2002-10-24 | 2004-04-29 | Bodeau John Michael | Control system for electrostatic discharge mitigation |
| 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 |
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| CN110077629A (en) * | 2019-04-12 | 2019-08-02 | 北京空间飞行器总体设计部 | Utilize the method and system of artificial magnetic field shielding spacecraft part low-energy electron environment |
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