CN107657079A - A kind of satellite charged effect induced malfunction and environments match analysis method - Google Patents
A kind of satellite charged effect induced malfunction and environments match analysis method Download PDFInfo
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- CN107657079A CN107657079A CN201710756555.2A CN201710756555A CN107657079A CN 107657079 A CN107657079 A CN 107657079A CN 201710756555 A CN201710756555 A CN 201710756555A CN 107657079 A CN107657079 A CN 107657079A
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Abstract
The invention discloses a kind of satellite charged effect induced malfunction and environments match analysis method, the analysis method determines failure, the failure that the failure is divided into the failure of surface charged effect induction and interior charged effect induces based on the environmental condition that generation charged effect needs to meet.The present invention can provide a kind of method that the matching analysis is carried out using environmental factor for satellite, for carrying out failure reason analysis and judgement to the satellite electron system soft mistake type fault occurred is repeated several times, the blank induced due to which kind of charged effect can not be directly distinguished when compensate for satellite failure.
Description
Technical field
The present invention relates to design of satellites field, and in particular to satellite charged effect induced malfunction and environments match analysis side
Method.
Background technology
Satellite charging and discharging effects, also known as satellite charged effect, refer to satellite and space plasma, high energy electron, earth magnetism
And the environmental interaction such as solar radiation and the accumulation of electrostatic charge occurred and process of releasing.Influenceed by charging and discharging effects, I
The many types of military satellite on-orbit fault of state takes place frequently, and charging and discharging effects turn into the important bottleneck for restricting the in-orbit safe operation of China's satellite
One of problem.
Satellite charged effect is according to the environmental factor of induction and discharge position occurs can be divided into surface charged effect and interior again
Charged effect, it is surface charged effect by being influenceed and being occurred in satellite surface by space plasma and illumination condition, by sky
Between high energy electron environment influence and occur inside satellite micro- interior charged effect, the two occur mechanism there is essential distinction,
The safeguard procedures of use are also not quite similar, but it is generation static discharge that it, which causes result, and failure common at present is mainly
Because EMP Coupling caused by static discharge enters soft error caused by satellite circuit, such failure only relies on phenomenon of the failure
It there is no method directly to distinguish the reason for such failure occurs for satellite with existing detection means, subsequent satellites design improvement caused to be stranded
It is difficult.
The content of the invention
In view of this, the invention provides a kind of satellite charged effect induced malfunction and environments match analysis method, this point
Analysis method provides a kind of method that the matching analysis is carried out using environmental factor for satellite, for the satellite occurred electricity is repeated several times
Subsystem soft error type fault carries out failure reason analysis and judgement.
Specific embodiments of the present invention are as follows：
A kind of satellite charged effect induced malfunction and environments match analysis method, the analysis method are based on that charged effect occurs
The environmental condition for needing to meet determines failure, and the failure is divided into failure and the induction of interior charged effect that surface charged effect induces
Failure.
Further, the environmental condition is as follows：
The environmental condition that surface charged effect occurs is made for no light or GEO substorm and solar windstorm diastrous weather
Occur into space plasma concentration and electron energy abnormal；
The environmental condition of charged effect is that satellite meets average in continuous 24 hours of 2MeV high energy electrical flux in generation
Flux density is more than 3.0 × 106/cm2·day·sr。
Further, when the failure had both been not belonging to the failure that surface charged effect induces, interior charged effect is not belonging to again
The failure of induction, and can reappear, then the failure induced for single particle effect.
Further, specific analytical method is as follows：
Step 1: when determining the locality that the soft error type fault occurred on same satellite occurs and residing track position
Put；
Step 2: according to during the locality of satellite failure and residing orbital position, judge whether satellite is in non-illumination
Area, step 3 is then performed in this way, such as otherwise perform step 4；
Step 3: according to space plasma environment Monitoring Data, judge whether to occur when failure occurs GEO substorm or
Solar windstorm diastrous weather, then this time failure is the failure that surface charged effect induces in this way, such as otherwise performs step 4；
Step 4: according to space high energy electron Monitoring Data, in 24 hours, judge that energy is more than 2MeV before failure generation
High energy electrical flux average flux density, if average flux density is more than 3.0 × 106/cm2Daysr, then such event
Hinder the failure induced for interior charged effect, as average flux density is less than or equal to 3.0 × 106/cm2Daysr, then perform
Step 5；
Step 5: single particle effect analysis and experiment are carried out to the satellite to break down, if reappearing the failure then to be single
The failure that particle effect induces.
Beneficial effect：
1st, the environmental condition that the present invention needs to meet using charged effect occurs is judged induced malfunction, can be to defending
Star is repeated several times the satellite electron system soft mistake type fault occurred and carries out failure reason analysis and judgement, compensate for satellite hair
The blank induced due to which kind of charged effect can not be directly distinguished during raw failure.
2nd, present invention determine that process is simple, quickly satellite can be repeated several times using specific environmental condition and data value
The satellite electron system soft mistake type fault of generation carries out failure reason analysis and judgement, improves and is pointed out mainly for design of satellites
Direction, suit the remedy to the case, reduce time and the cost of ground zero analysis and experiment.
Brief description of the drawings
Fig. 1 is the inventive method flow chart；
Fig. 2 is doubtful discharge and recharge number and high energy in the present embodiment typical time period (2013.05.28-2013.06.15)
Electron flux.
Embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
The invention provides a kind of satellite charged effect induced malfunction and environments match analysis method, general principle is foundation
The environmental condition that charged effect needs to meet occurs for satellite, i.e., surface is powered needs to meet two conditions：A. no light；b.
GEO substorm or solar windstorm diastrous weather cause space plasma concentration and electron energy that exception occurs；And satellite occurs
Average flux density is more than 3.0 × 10 in continuous 24 hours of the interior powered high energy electrical flux for needing to meet 2MeV6/cm2·
day·sr。
Step 1: when determining the locality that the soft error type fault occurred on same satellite occurs and residing track position
Put；
Step 2: according to during the locality of satellite failure and residing orbital position, judge whether satellite is in non-illumination
Area, step 3 is then performed in this way, such as otherwise perform step 4；
Step 3: according to space plasma environment Monitoring Data, judge whether to occur when failure occurs GEO substorm or
Solar windstorm diastrous weather, then this time failure is the failure that surface charged effect induces in this way, such as otherwise performs step 4；
Step 4: according to space high energy electron Monitoring Data, in 24 hours, judge that energy is more than 2MeV before failure generation
High energy electrical flux average flux density, if average flux density is more than 3.0 × 106/cm2Daysr, then such event
Hinder the failure induced for interior charged effect, as average flux density is less than or equal to 3.0 × 106/cm2Daysr, then perform
Step 5；
Step 5: single particle effect analysis and experiment are carried out to the satellite unit to break down, if reappearing the failure then
The failure induced for single particle effect.
First, step 1 and step 2 are performed, surface charged effect is quickly judged using illumination condition.Such as satellite
In non-area of illumination then can according to disclosed in enviromental monitoring equipment or U.S.'s GOES satellites that satellite carries in itself etc. in-orbit prison
Data are surveyed, are further analyzed, if the diastrous weathers such as GEO substorm or solar windstorm do not occur, satellite will not also be sent out
Raw surface charged effect.
Secondly, the powered induced malfunction in surface is being not belonging to by judgement, the environmental monitoring that can be carried in itself according to satellite is set
In-orbit Monitoring Data disclosed in standby or U.S.'s GOES satellites etc., the 2MeV of 24 hours high energy is electric before counting down time
Sub- flux, the average flux density in computing interval, current internationally recognized interior powered occurring conditions lower limit are 3.0 × 106/
cm2Daysr, such as it is less than this standard, it is possible to determine that interior charged effect does not occur.
Finally, if after premenstrual four steps of the failure, charged effect occurrence condition is unsatisfactory for, then performs step
Five, confirm whether it may be induced by single particle effect.
One satellite failure meets Step 2: the probability very little of three, four decision conditions, this is due to the powered shape in surface simultaneously
Into time it is very short, substantially in the several seconds to tens of second-times, and interior charged effect needs the high energy electricity up to tens of hours
Sub- cumulative process, satellite in orbit during, can meet that the situation of three decision conditions is very rare simultaneously.
Illustrated below with example, since 2013 put into operation, its certain core missions load occurs mutually similar certain satellite
The anomalous event of type is up to up to a hundred times, and on May 18th, 2013 is similar abnormal to 6 times during June 15, occur altogether, wherein 5 foundations
Step 1 is judged to four:It runs on area of illumination, is more than 2MeV high energy electrical flux before abnormal generation in 24 hours
Density is more than 3.0 × 106/cm2Daysr, as shown in Fig. 2 can determine that as interior powered induction satellite failure.And May 19 was sent out
Raw similar failure, it is determined as that single-particle induces satellite failure through this method, carries out checking test by ground, reappeared the event
Barrier.
Using this method judge certain satellite by it is interior it is powered induce such failure up to 42 times, tested by analysing in depth, most
Interior powered generation position is determined eventually, is improved in subsequent satellites design, achieves good result, 1-10 in 2016
Month, under same environmental conditions, the such failure of certain satellite generation 37 times, the satellite after improvement only occurs 4 times.This shows the present invention
Decision method there is higher accuracy.
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., it should be included in the present invention's
Within protection domain.
Claims (4)
1. a kind of satellite charged effect induced malfunction and environments match analysis method, it is characterised in that the analysis method is based on hair
The environmental condition that green tape electrical effect needs to meet determines failure, and the failure is divided into failure and the interior band that surface charged effect induces
The failure that electrical effect induces.
2. satellite charged effect induced malfunction as claimed in claim 1 and environments match analysis method, it is characterised in that described
Environmental condition is as follows：
The environmental condition that surface charged effect occurs causes sky for no light or GEO substorm and solar windstorm diastrous weather
Between plasma density and electron energy occur it is abnormal；
The environmental condition of charged effect is that satellite meets average flux in continuous 24 hours of 2MeV high energy electrical flux in generation
Density is more than 3.0 × 106/cm2·day·sr。
3. satellite charged effect induced malfunction as claimed in claim 1 and environments match analysis method, it is characterised in that work as institute
State failure and be both not belonging to the failure that surface charged effect induces, be not belonging to the failure that interior charged effect induces again, and can answer
It is existing, then the failure induced for single particle effect.
4. satellite charged effect induced malfunction as claimed in claim 3 and environments match analysis method, it is characterised in that specific
Analysis method is as follows：
Step 1: when determining the locality that the soft error type fault that occurs occurs on same satellite and residing orbital position；
Step 2: according to during the locality of satellite failure and residing orbital position, judge whether satellite is in non-area of illumination, such as
It is to perform step 3, such as otherwise performs step 4；
Step 3: according to space plasma environment Monitoring Data, judge GEO substorm or the sun whether occur when failure occurs
Storm disaster weather, then this time failure is the failure that surface charged effect induces in this way, such as otherwise performs step 4；
Step 4: according to space high energy electron Monitoring Data, before failure generation in 24 hours, judge that energy is more than 2MeV height
The average flux density of energy electron flux, if average flux density is more than 3.0 × 106/cm2Daysr, then such failure be
The failure that interior charged effect induces, as average flux density is less than or equal to 3.0 × 106/cm2Daysr, then perform step
Five；
Step 5: single particle effect analysis and experiment are carried out to the satellite to break down, if it is then single-particle to reappear the failure
The failure that effect induces.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111703593A (en) * | 2020-06-28 | 2020-09-25 | 国家卫星气象中心(国家空间天气监测预警中心) | Early warning method and early warning system for surface charging effect of geosynchronous orbit satellite |
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Application publication date: 20180202 |