CN104155878B - Space radiation environment reliability index formulating method based on DPM - Google Patents
Space radiation environment reliability index formulating method based on DPM Download PDFInfo
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Abstract
A kind of space radiation environment reliability index formulating method based on DPM, described method includes: S1: presetting satellite task index, described satellite task index includes the control ratio of the availability of satellite, survival probability and space radiation environment reliability;S2: determine mission requirements index R of space radiation environment reliability index according to described satellite task indexSPEC;S3: according to RSPECCalculate the design capacity RDM that satellite devices is correspondingreal, and compare RDMrealReceptible risk RDM of mission reliability is met with satellite devicesSPEC;Work as RDMrealMore than RDMSPEC, then by RDMrealMeet task index requirement RSPEC;S4: using satellite task index now as the space radiation environment reliability index of device.The present invention determines space radiation environment index calculating method by relying on task, it is ensured that the space radiation environment reliability requirement of task.
Description
Technical field
The present invention relates to space radiation field, particularly to a kind of space radiation ring based on DPM
Border reliability index formulating method.
Background technology
The spatial environments that satellite experiences at space tasks track is severe, earth acquisition band, sun thing
Dynamic under the influence of the background environments such as part particle, galactic cosmic rays and periodically solar activity
The high energy particle (including heavy ion, proton, electronics etc.) of environment can induce device in satellite and send out
Raw charging and discharging effects, single particle effect, total dose effect, displacement damage effect, cause satellite
Fault.Accordingly, it is determined that effective space radiation environment reliability index system is to ensure that satellite is empty
Between the key factor of environmental reliability.
The satellite spatial radiation environment reliability index single index of many employings of China is carried out about at present
Bundle, such as single-particle inversion threshold value 37MeV cm2/ mg, single event latch-up threshold value
75MeV·cm2/mg。
But satellite spatial radiation environment reliability is affected by many factors, if simply rule
Order one index, then under the influence of other factors not determined, the space radiation environment of satellite
Reliability there is also the biggest difference.Such as Single event upset effecf, affect single event upset rate
Factor include sensitive objects type, single-particle inversion threshold value, sensitive volume, saturated cross section,
Existing safeguard procedures etc..When reliability index only specifies that single-particle inversion threshold value is
37MeV·cm2During/mg, being only because the difference of saturated cross section and sensitive volume, its upset rate is just
Have the difference of several order of magnitude.The formulation of the most single index is not sufficient to ensure that the space of satellite
Radiation reliability.
Summary of the invention
(1) solve the technical problem that
Present invention solves the technical problem that it is to be determined by space radiation environment reliability index to formulate
Method, forms a set of space radiation environment index system with index algorithm as core.
(2) technical scheme
The present invention provides a kind of space radiation environment reliability index formulating method based on DPM,
Described method includes:
S1: preset satellite task index, described satellite task index include satellite availability,
The control ratio of survival probability and space radiation environment reliability;
S2: determine the task of space radiation environment reliability index according to described satellite task index
Require index RSPEC;
S3: according to RSPECCalculate the design capacity RDM that satellite devices is correspondingreal, and compare
RDMrealReceptible risk RDM of mission reliability is met with satellite devicesSPEC;When
RDMrealMore than RDMSPEC, then by RDMrealMeet task index requirement RSPEC;
S4: using satellite task index now as the space radiation environment reliability index of device.
Preferably, also include after step S1: according to step S1 Satellite availability A, with
And the break period Controlling model DPM of satellite is calculated according to formula (1)Satellite,
DPMSatellite=(1-A)×106(1)
Wherein, A is availability of satellites.
Preferably, according to the break period Controlling model DPM of described satelliteSatellite, and according to public affairs
Formula (2) calculates the break period Controlling model DPM of satellite spatial radiation environmentSatellite-radiation,
DPMSatellite-radiation=ω×DPMSatellite(2)
Wherein, ω is the space radiation environment contribution proportion to satellite reliability.
Preferably, ω is 0.1.
Preferably, according to the break period Controlling model DPM of satellite spatial radiation environmentSatellite-radiation,
And the break period Controlling model DPM according to formula (3) calculating device space radiation environmentDevice Part-radiation,
DPMDevice-radiation=DPMSatellite-radiation/ n (3)
Wherein, n is Sensitive Apparatus sum, sensitive by satellite devices carries out Space Radiation Effects
Analyze and obtain.
Preferably, mission requirements index R of space radiation environment reliability indexSPECAccording to formula
(4) determine with (5),
RSPEC=1/λDevice-radiation(5)
Wherein, tDevice-radiationFor the device break period, it is to be divided by system design analysis and mission requirements
Analysis determines.
Preferably, the design capacity RDM that satellite devices described in step S3 is correspondingrealBy formula
(6) determine,
Wherein, RMFFor the actual capability of resistance to radiation of device, it is to utilize existing historical empirical data true
Fixed.
Preferably, satellite devices described in step S3 meets the receptible risk of mission reliability
RDMSPECIt is to utilize theoretical calculation method and existing historical empirical data to determine.
Preferably, in step S3,
Work as RDMrealLess than RDMSPECTime, then reappraise device after taking safeguard procedures
Actual capability of resistance to radiation, repeat step S3;If RDM cannot be made by safeguard proceduresreal
Meet task index requirement RSPEC, then change device, repeat step S1 to S4, until RDMreal
Meet task index requirement RSPEC。
(3) beneficial effect
The present invention determines space radiation environment reliability index formulating method by relying on task,
The space radiation environment reliability requirement of guarantee task.
Accompanying drawing explanation
Fig. 1 is the method flow diagram that the present invention provides.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, to the technical side in the embodiment of the present invention
Case is clearly and completely described.
The invention provides a kind of space radiation environment reliability index formulation side based on DPM
Method, as it is shown in figure 1, described method includes:
S1: preset satellite task index, described satellite task index include satellite availability,
The control ratio of survival probability and space radiation environment reliability;
According to step S1 Satellite availability A, and calculate in satellite according to formula (1)
Break time Controlling model DPMSatellite,
DPMSatellite=(1-A)×106(1)
Wherein, A is availability of satellites.
Failure modes according to satellite carries out control of classifying, and as shown in table 1, ω is space radiation
The environment contribution proportion to satellite reliability, according to the break period Controlling model of described satellite
DPMSatellite, and the break period control of satellite spatial radiation environment is calculated according to formula (2)
Model DPMSatellite-radiation,
DPMSatellite-radiation=ω×DPMSatellite(2)
Table 1
According to upper table, ω is 0.1.
Break period Controlling model DPM according to satellite spatial radiation environmentSatellite-radiation, Yi Jigen
Break period Controlling model DPM according to formula (3) calculating device space radiation environmentDevice-radiation,
DPMDevice-radiation=DPMSatellite-radiation/ n (3)
Wherein, n is Sensitive Apparatus sum, sensitive by satellite devices carries out Space Radiation Effects
Analyze and obtain.
S2: determine the task of space radiation environment reliability index according to described satellite task index
Require index RSPEC;
Mission requirements index R of space radiation environment reliability indexSPECAccording to formula (4) and
(5) determine,
RSPEC=1/λDevice-radiation(5)
Wherein, tDevice-radiationFor the device break period, it is to be divided by system design analysis and mission requirements
Analysis determines.
S3: according to RSPECCalculate the design capacity RDM that satellite devices is correspondingreal, and compare
RDMrealReceptible risk RDM of mission reliability is met with satellite devicesSPEC;When
RDMrealMore than RDMSPEC, show that satellite devices meets the receptible risk of mission reliability,
Then jump procedure S4;Work as RDMrealLess than RDMSPEC, then show that satellite devices is unsatisfactory for appointing
The business receptible danger of reliability, then jump procedure S1 resets satellite task index, directly
To RDMrealMore than RDMSPEC;
The design capacity RDM that described satellite devices is correspondingrealDetermined by formula (6),
Wherein, RMFMeet, for device, the practical capacity that mission reliability requirement reaches, be to utilize
Some historical empirical data determine.
Described satellite devices meets receptible risk RDM of mission reliabilitySPECIt is to utilize reason
Opinion computational methods and existing historical empirical data determine.
S4: using satellite task index now as the space radiation environment reliability index of device.
Embodiment of above is merely to illustrate the present invention, and not limitation of the present invention, relevant
The those of ordinary skill of technical field, without departing from the spirit and scope of the present invention,
Can also make a variety of changes and modification, the technical scheme of the most all equivalents falls within the present invention
Category, the scope of patent protection of the present invention should be defined by the claims.
Claims (7)
1. a space radiation environment reliability index formulating method based on DPM, its feature
Being, described method includes:
S1: preset satellite task index, described satellite task index include satellite availability,
The control ratio of survival probability and space radiation environment reliability;
S2: determine the task of space radiation environment reliability index according to described satellite task index
Require index RSPEC;
S3: according to RSPECCalculate the design capacity RDM that satellite devices is correspondingreal, and compare
RDMrealReceptible risk RDM of mission reliability is met with satellite devicesSPEC;When
RDMrealMore than RDMSPEC, then by RDMrealMeet task index requirement RSPEC;
S4: using satellite task index now as the space radiation environment reliability index of device;
Mission requirements index R of space radiation environment reliability indexSPECAccording to formula (4) and
(5) determine,
RSPEC=1/ λDevice-radiation (5)
Wherein, tDevice-radiationFor the device break period, it is to be divided by system design analysis and mission requirements
Analysis determines;
The design capacity RDM that satellite devices described in step S3 is correspondingrealDetermined by formula (6),
Wherein, RMFFor the actual capability of resistance to radiation of device, it is to utilize existing historical empirical data true
Fixed.
Method the most according to claim 1, it is characterised in that also wrap after step S1
Include: according to step S1 Satellite availability, and calculate the interruption of satellite according to formula (1)
Time Controlling model DPMSatellite,
DPMSatellite=(1-A) × 106 (1)
Wherein, A is availability of satellites.
Method the most according to claim 2, it is characterised in that according in described satellite
Break time Controlling model DPMSatellite, and calculate satellite spatial radiation environment according to formula (2)
Break period Controlling model DPMSatellite-radiation,
DPMSatellite-radiation=ω × DPMSatellite (2)
Wherein, ω is the space radiation environment contribution proportion to satellite reliability.
Method the most according to claim 3, it is characterised in that ω is 0.1.
Method the most according to claim 3, it is characterised in that radiate according to satellite spatial
The break period Controlling model DPM of environmentSatellite-radiation, and empty according to formula (3) calculating device
Between the break period Controlling model DPM of radiation environmentDevice-radiation,
DPMDevice-radiation=DPMSatellite-radiation/n (3)
Wherein, n is Sensitive Apparatus sum, sensitive by satellite devices carries out Space Radiation Effects
Analyze and obtain.
Method the most according to claim 1, it is characterised in that defend described in step S3
Star device meets receptible risk RDM of mission reliabilitySPECIt is to utilize theoretical calculation method
Determine with existing historical empirical data.
Method the most according to claim 1, it is characterised in that in step S3,
Work as RDMrealLess than RDMSPECTime, then reappraise device after taking safeguard procedures
Actual capability of resistance to radiation, repeat step S3;If RDM cannot be made by safeguard proceduresreal
Meet task index requirement RSPEC, then change device, repeat step S1 to S4, until RDMreal
Meet task index requirement RSPEC。
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CN102928773A (en) * | 2012-09-24 | 2013-02-13 | 北京圣涛平试验工程技术研究院有限责任公司 | Method for testing proton/single event effect resisting capacity of device |
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WO2001061573A2 (en) * | 2000-02-16 | 2001-08-23 | Siemens Aktiengesellschaft | Method and device for calculating a model of a technical system |
CN101887088A (en) * | 2009-05-14 | 2010-11-17 | 北京圣涛平试验工程技术研究院有限责任公司 | Method and system for evaluating single-particle effect index of satellite device |
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