CN104143012A - Hazard identification method for space radiation environment - Google Patents
Hazard identification method for space radiation environment Download PDFInfo
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- CN104143012A CN104143012A CN201310172852.4A CN201310172852A CN104143012A CN 104143012 A CN104143012 A CN 104143012A CN 201310172852 A CN201310172852 A CN 201310172852A CN 104143012 A CN104143012 A CN 104143012A
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Abstract
The invention relates to the field of space environment detection and protection, in particular to a hazard identification method for a space radiation environment. The method comprises steps as follows: S1, performance parameters of an aircraft electronic system and an aircraft device are collected by a data collection system and sent to a data analysis system; S2, the data analysis system performs functionality analysis on the performance parameters, the induced effect of the space radiation environment is concluded; and S3, the hazard degree of an aircraft is positioned in combination of the space radiation environment condition. According to the method, through comprehensive space radiation environment hazard identification of the aircraft, the aircraft design is facilitated, so that the operation reliability and safety of the aircraft are guaranteed, and the cost consumption of engineering application is reduced.
Description
Technical field
The present invention relates to a kind of space environment and detect and protection field, relate in particular to a kind of space radiation environment environmental hazard and know method for distinguishing.
Background technology
At present, spacecraft is affected by space radiation environment and produces single particle effect, total dose effect, displacement damage effect and charging and discharging effects with electronic system and device used thereof, and then causes system to break down, the reliability of serious harm system and security.Domestic spacecraft is known method for distinguishing owing to lacking to space radiation environment environmental hazard with electronic system and device used thereof, causes fault analysis comprehensive not, in design process, can lack enough guidances, the reliability of impact design.
In order to overcome the above problems, the present invention has done useful improvement.
Summary of the invention
(1) technical matters that will solve
The object of this invention is to provide a kind of space radiation environment environmental hazard and know method for distinguishing, the single particle effect that can cause space radiation environment, total dose effect, displacement damage effect and charging and discharging effects provide comprehensive harm identification.
(2) technical scheme
The present invention is achieved by the following technical solutions:
A method for distinguishing is known in space radiation environment environmental hazard, comprises the following steps:
S1. by data acquisition system (DAS), collect the performance parameter of aircraft electronic system and aircraft device, and described performance parameter is sent to data analysis system;
S2. data analysis system carries out functional selection to described performance parameter, infers the response facilitation effect of space radiation environment;
S3. in conjunction with space radiation environment condition, aircraft is carried out to extent of injury location.
Wherein, described step S2 specifically comprises the following steps:
S21. determine the failure mode of aircraft electronic system or bring out particle kind, inferring this failure mode or bring out the response facilitation effect of the space radiation environment that particle kind is corresponding;
S22. determine the failure mode of described aviation or bring out particle kind, then by the mechanism of production of the response facilitation effect of space radiation environment is analyzed, inferring the response facilitation effect of the space radiation environment of the described aviation of impact.
Further, described step S21 concrete grammar is:
From four kinds of response facilitation effects of single particle effect, total dose effect, displacement damage effect and the charging and discharging effects of space radiation environment, according to the failure mode of aircraft electronic system or bring out particle kind respectively with the mechanism of production of described response facilitation effect, infer and draw described one or more response facilitation effects of aircraft electronic system of impact.
Further again, described step 22 concrete grammar is:
From four kinds of response facilitation effects of single particle effect, total dose effect, displacement damage effect and the charging and discharging effects of space radiation environment, according to the failure mode of aviation or bring out particle kind respectively with the mechanism of production of described response facilitation effect, infer one or more response facilitation effects that draw the described aviation of impact.
Wherein, in described step S3, described " space radiation environment condition " specifically comprises aircraft place track condition and solar cycle condition.
(3) beneficial effect
Compare with product with prior art, the present invention has the following advantages:
The present invention, by the comprehensive space radiation environment harm of aircraft identification, contributes to the design of spacecraft, thereby guarantees spacecraft reliability of operation and security, has reduced the cost consumption of engineering application.
Accompanying drawing explanation
Fig. 1 the invention provides FTA Fault Tree Analysis schematic diagram;
Fig. 2 is the method step schematic diagram of space radiation environment environmental hazard identification provided by the invention.
Embodiment
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is made a detailed explanation.
The invention provides and a kind of spacecraft is known to method for distinguishing as the space radiation environment environmental hazard of the place such as communications satellite, space space station.Take communications satellite as example, and as shown in Figure 1, the present invention adopts fault tree FTA analytical approach, and as shown in Figure 2, described space radiation environment environmental hazard is known method for distinguishing and specifically comprised the following steps:
S1. by data acquisition system (DAS), collect the performance parameter of aircraft electronic system and aircraft device, and described performance parameter is sent to data analysis system.Data acquisition system (DAS) comprises and is arranged on spaceborne a plurality of sensor and pick-up unit, the performance parameter sensing or harmfulness sensitive parameter can be collected on aircraft electronic system and aircraft device.On telstar as shown in Figure 1, as the signal interruption of telstar, can to the performance parameter on telstar, gather by data acquisition system (DAS), then performance parameter or harmfulness sensitive parameter are sent to data analysis system.。
S2. data analysis system carries out functional selection to described performance parameter, infers the response facilitation effect of space radiation environment.Data analysis system comprises computer system, effectively performance parameter is analyzed, and according to the response facilitation effect pattern of the space radiation environment of setting in computer system, infers accordingly the response facilitation effect of space radiation environment.This step specifically comprises following two steps:
S21. determine the failure mode of aircraft electronic system or bring out particle kind, inferring this failure mode or bring out the response facilitation effect of the space radiation environment that particle kind is corresponding;
The response facilitation effect of space radiation environment is the foundation of the Scheme Choice at system initial stage to the identification of Spacecraft Electronic harm to the system.Specifically, from four kinds of response facilitation effects of single particle effect, total dose effect, displacement damage effect and the charging and discharging effects of space radiation environment, according to the failure mode of avionics system or bring out particle kind respectively with the mechanism of production analysis of described response facilitation effect, infer and draw described one or more response facilitation effects of aircraft electronic system of impact.
Space radiation environment effect must occur, space radiation environment mainly brings out spacecraft and produces four kinds of damage effects such as single particle effect, total dose effect, displacement damage effect and charging and discharging effects with electronic system and device used thereof, and meeting initiating system, assembly and components and parts produce all kinds of transient states and (or) permanent damage etc.Space radiation Harm Type and the corresponding table that brings out particle kind can be used as the corresponding mechanism of production of bringing out particle kind and radiation space response facilitation effect, as shown in the table:
| Space radiation environment Harm Type | Bring out particle kind | Main source |
| Total dose effect | >100keVe-,H+ | TRE、SPE |
| Single particle effect | > 10MeV/amuH+ heavy ion | GCR、SPE |
| Displacement damage effect | > 10MeVH+ secondary neutron | TRE、SPE |
| Surface charging | 0.01-100keVe- | Plasma |
| Deep layer charging | 100keV-10MeVe- | SPE |
For example, as shown in Figure 1, interrupting appears in the communication function of certain communications satellite, by sensor, communication equipment fault and communication antenna fault detected, take fault harm to analyze the passable failure mode that draws aircraft, as afunction and data exception, thereby according to data analysis system, infer the Space Radiation Effects type that produces fault, be that afunction correspondence total dose effect, data exception correspondence single particle effect simultaneously.
Respectively four of the single particle effect of radiation space, total dose effect, displacement damage effect and charging and discharging effects kinds of harm recognition modes corresponding to response facilitation effect are described below:
1) harm of total dose effect to system
Functional selection: total dose effect can cause the harm such as the performance degradations such as electronic equipment and control system, web member organic material or afunction;
Main failure mode: parameter drift and disabler.
2) harm of displacement damage effect to system
Functional selection: displacement damage effect can cause solar cell, electro-optical system performance degradation or afunction;
Main Patterns: parameter drift and disabler.
3) harm of single particle effect to system
Functional selection: single particle effect can cause electronic equipment and control system is destructive and non-destructive harm;
Main failure mode: functional mistake, easily ruining property mistake, mortality mistake.
4) harm of charging and discharging effects to system
Functional selection: charging and discharging effects can cause electronic equipment and the destructive harm of electrical system of spacecraft;
Main failure mode: functional inefficacy, physical property are destroyed.
S22. determine the failure mode of described aviation or bring out particle kind, then by the mechanism of production of the response facilitation effect of space radiation environment is analyzed, inferring the response facilitation effect of the space radiation environment of the described aviation of impact.Particularly, from four kinds of response facilitation effects of single particle effect, total dose effect, displacement damage effect and the charging and discharging effects of space radiation environment, according to the failure mode of aviation or bring out particle kind respectively with the harm identification module of described response facilitation effect, infer and draw one or more response facilitation effects corresponding with described aviation failure mode.
Space radiation environment directly produces harm to spacecraft device, therefore can analyze each Space Radiation Effects by the mechanism of production of space radiation environment effect affects the harm of device, illustrates each effect of space radiation below for device harm, failure mode and mechanism of production.
1) harm of total dose effect to device
Tatal ionizing dose effects is mainly that charged particle (as electronics, proton etc.), γ, X ray and matter interaction produce electron-hole pair in semiconductor devices, at device inside diverse location produce series of physical process, thereby affect the electrical property of device thereafter.By the analysis of element total dose effect mechanism of production, known space environment total dose effect is as shown in the table to the failure mode of device:
2) harm of displacement damage effect to device
Displacement damage effect is mainly high energy particle (neutron, proton, electronics, heavy ion) incident device, bumps with the atom in lattice, makes lattice atoms leave normal lattice position, forms defect.These defects can cause device electrical parameter to change.By the analysis of device displacement damage effect mechanism of production, the failure mode of known space environment displacement damage effect to device
As shown in the table:
3) harm of single particle effect to device
Space single particle effect is mainly to bring out generation by heavy ion and high energy proton.Space heavy ion generally brings out single particle effect by the mode of direct ionization, along the ionization of incident rail footpath, produce a large amount of electron-hole pairs, the electron-hole being excited is collected under voltage effect, and when the charge number being collected is greater than critical charge, the state of circuit will be freeed change.By the analysis of device single particle effect mechanism of production, known space environment single particle effect is as shown in the table to the failure mode of device:
4) harm of charging and discharging effects to device
Space radiation charging and discharging effects has damaging effect to device, when design, materials and devices is carried out to prudent selection, mistake! Do not find Reference source.For considering Space Radiation Effects, during spacecraft design, should avoid the coating material using.
S3. in conjunction with space radiation environment condition, aircraft is carried out to extent of injury location.Described " space radiation environment condition " specifically comprises aircraft place track condition and solar cycle condition.
Four kinds of response facilitation effects below in conjunction with single particle effect, total dose effect, displacement damage effect and the charging and discharging effects of space radiation environment, illustrate respectively the extent of injury localization method to aircraft electronic system:
1) extent of injury of total dose effect location:
-the extent of injury of co-orbital total dose effect is not different;
Under-same application condition, in duty cycle, the accumulated dose of MEO track accumulation is maximum, and IGSO track is minimum;
-sun active period and outbreak period, little on the impact of accumulation total dose effect.
2) displacement damage effect extent of injury location:
The extent of injury of-GEO, IGSO, MEO orbital module intrinsic displacement damage effect is substantially suitable;
-sun active period and outbreak period, little on the impact of accumulation displacement damage effect.
3) single particle effect extent of injury location:
The extent of injury of the single particle effect of-different tracks, different solar cycles is different;
-the sun pediocratic, GEO, IGSO, MEO track are substantially suitable;
-sun active period and outbreak period, it is the most serious that GEO track brings out single particle effect;
-solar burst the phase (in the most bad situation), single particle effect probability of happening is higher 2 to 3 orders of magnitude than pediocratic.
4) extent of injury of charging and discharging effects location:
The extent of injury of the charging and discharging effects of-different tracks, different solar cycles is different;
The extent of injury of-GEO, IGSO, MEO track charging and discharging effects is different;
-sun active period and outbreak period, spacecraft charging and discharging effects will aggravate.
Along with engineering development stage work is goed deep into, also should progressively identify all potential harm and risk, determine protection Design priority ranking and safeguard procedures.By to the comprehensive space radiation environment harm of aircraft identification, contribute to refer to the design of spacecraft, thereby guarantee spacecraft reliability of operation and security, reduced the cost consumption of engineering application.
Above embodiment is only for illustrating the present invention; and be not limitation of the present invention; the those of ordinary skill in relevant technologies field; without departing from the spirit and scope of the present invention; can also make a variety of changes and modification; therefore all technical schemes that are equal to also belong to category of the present invention, and scope of patent protection of the present invention should be defined by the claims.
Claims (5)
1. a method for distinguishing is known in space radiation environment environmental hazard, it is characterized in that, comprises the following steps:
S1. by data acquisition system (DAS), collect the performance parameter of aircraft electronic system and aircraft device, and described performance parameter is sent to data analysis system;
S2. data analysis system carries out functional selection to described performance parameter, infers the response facilitation effect of space radiation environment;
S3. in conjunction with space radiation environment condition, aircraft is carried out to extent of injury location.
2. method for distinguishing is known in space radiation environment environmental hazard according to claim 1, it is characterized in that, described step S2 specifically comprises the following steps:
S21. determine the failure mode of aircraft electronic system or bring out particle kind, inferring this failure mode or bring out the response facilitation effect of the space radiation environment that particle kind is corresponding;
S22. determine the failure mode of described aviation or bring out particle kind, then by the mechanism of production of the response facilitation effect of space radiation environment is analyzed, inferring the response facilitation effect of the space radiation environment of the described aviation of impact.
3. method for distinguishing is known in space radiation environment environmental hazard according to claim 2, it is characterized in that, described step S21 concrete grammar is:
From four kinds of response facilitation effects of single particle effect, total dose effect, displacement damage effect and the charging and discharging effects of space radiation environment, according to the failure mode of aircraft electronic system or bring out particle kind respectively with the mechanism of production of described response facilitation effect, infer and draw described one or more response facilitation effects of aircraft electronic system of impact.
4. method for distinguishing is known in space radiation environment environmental hazard according to claim 2, it is characterized in that, described step 22 concrete grammar is:
From four kinds of response facilitation effects of single particle effect, total dose effect, displacement damage effect and the charging and discharging effects of space radiation environment, according to the failure mode of aviation or bring out particle kind respectively with the mechanism of production of described response facilitation effect, infer one or more response facilitation effects that draw the described aviation of impact.
5. method for distinguishing is known in space radiation environment environmental hazard according to claim 2, it is characterized in that, in described step S3, described " space radiation environment condition " specifically comprises aircraft place track condition and solar cycle condition.
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Cited By (5)
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| CN107657079A (en) * | 2017-08-29 | 2018-02-02 | 兰州空间技术物理研究所 | A kind of satellite charged effect induced malfunction and environments match analysis method |
| 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 |
| CN109325693A (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 risk quantification appraisal procedure |
| CN112800573A (en) * | 2019-11-14 | 2021-05-14 | 北京圣涛平试验工程技术研究院有限责任公司 | Reliability analysis method and device |
| CN116562630A (en) * | 2023-07-07 | 2023-08-08 | 数字太空(北京)智能技术研究院有限公司 | Risk assessment method and device for satellite influenced by space environment |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107657079A (en) * | 2017-08-29 | 2018-02-02 | 兰州空间技术物理研究所 | A kind of satellite charged effect induced malfunction and environments match analysis method |
| 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 |
| CN109325693A (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 risk quantification appraisal procedure |
| CN109325693B (en) * | 2018-09-28 | 2021-11-02 | 兰州空间技术物理研究所 | Spacecraft on-orbit surface charging effect risk quantitative evaluation method |
| CN112800573A (en) * | 2019-11-14 | 2021-05-14 | 北京圣涛平试验工程技术研究院有限责任公司 | Reliability analysis method and device |
| CN112800573B (en) * | 2019-11-14 | 2023-11-03 | 北京圣涛平试验工程技术研究院有限责任公司 | Reliability analysis method and device |
| CN116562630A (en) * | 2023-07-07 | 2023-08-08 | 数字太空(北京)智能技术研究院有限公司 | Risk assessment method and device for satellite influenced by space environment |
| CN116562630B (en) * | 2023-07-07 | 2023-09-15 | 数字太空(北京)智能技术研究院有限公司 | Risk assessment method and device for satellite influenced by space environment |
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Application publication date: 20141112 |