CN104155878B - Space radiation environment reliability index formulating method based on DPM - Google Patents

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 index_SPEC；S3: according to R_SPECCalculate the design capacity RDM that satellite devices is corresponding_real, and compare RDM_realReceptible risk RDM of mission reliability is met with satellite devices_SPEC；Work as RDM_realMore than RDM_SPEC, then by RDM_realMeet task index requirement R_SPEC；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

Space radiation environment reliability index formulating method based on DPM

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 R_SPEC；

S3: according to R_SPECCalculate the design capacity RDM that satellite devices is corresponding_real, and compare RDM_realReceptible risk RDM of mission reliability is met with satellite devices_SPEC；When RDM_realMore than RDM_SPEC, then by RDM_realMeet task index requirement R_SPEC；

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,

DPM_Satellite=(1-A)×10⁶(1)

Wherein, A is availability of satellites.

Preferably, according to the break period Controlling model DPM of described satellite_Satellite, and according to public affairs Formula (2) calculates the break period Controlling model DPM of satellite spatial radiation environment_{Satellite-radiation},

DPM_{Satellite-radiation}=ω×DPM_Satellite(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 environment_{Satellite-radiation}, And the break period Controlling model DPM according to formula (3) calculating device space radiation environment_{Device Part-radiation},

DPM_{Device-radiation}=DPM_{Satellite-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 index_SPECAccording to formula (4) determine with (5),

R_SPEC=1/λ_{Device-radiation}(5)

Wherein, t_{Device-radiation}For 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 corresponding_realBy formula (6) determine,

${\mathrm{RDM}}_{\mathrm{real}}=\frac{R_{\mathrm{MF}}}{R_{\mathrm{SPEC}}}---\left(6\right)$

Wherein, R_MFFor 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 RDM_SPECIt is to utilize theoretical calculation method and existing historical empirical data to determine.

Preferably, in step S3,

Work as RDM_realLess than RDM_SPECTime, then reappraise device after taking safeguard procedures Actual capability of resistance to radiation, repeat step S3；If RDM cannot be made by safeguard procedures_real Meet task index requirement R_SPEC, then change device, repeat step S1 to S4, until RDM_real Meet task index requirement R_SPEC。

(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 DPM_Satellite,

DPM_Satellite=(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 DPM_Satellite, and the break period control of satellite spatial radiation environment is calculated according to formula (2) Model DPM_{Satellite-radiation},

DPM_{Satellite-radiation}=ω×DPM_Satellite(2)

Table 1

According to upper table, ω is 0.1.

Break period Controlling model DPM according to satellite spatial radiation environment_{Satellite-radiation}, Yi Jigen Break period Controlling model DPM according to formula (3) calculating device space radiation environment_{Device-radiation},

DPM_{Device-radiation}=DPM_{Satellite-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 R_SPEC；

Mission requirements index R of space radiation environment reliability index_SPECAccording to formula (4) and (5) determine,

R_SPEC=1/λ_{Device-radiation}(5)

Wherein, t_{Device-radiation}For the device break period, it is to be divided by system design analysis and mission requirements Analysis determines.

S3: according to R_SPECCalculate the design capacity RDM that satellite devices is corresponding_real, and compare RDM_realReceptible risk RDM of mission reliability is met with satellite devices_SPEC；When RDM_realMore than RDM_SPEC, show that satellite devices meets the receptible risk of mission reliability, Then jump procedure S4；Work as RDM_realLess than RDM_SPEC, 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 RDM_realMore than RDM_SPEC；

The design capacity RDM that described satellite devices is corresponding_realDetermined by formula (6),

${\mathrm{RDM}}_{\mathrm{real}}=\frac{R_{\mathrm{MF}}}{R_{\mathrm{SPEC}}}---\left(6\right)$

Wherein, R_MFMeet, 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 reliability_SPECIt 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 R_SPEC；

S3: according to R_SPECCalculate the design capacity RDM that satellite devices is corresponding_real, and compare RDM_realReceptible risk RDM of mission reliability is met with satellite devices_SPEC；When RDM_realMore than RDM_SPEC, then by RDM_realMeet task index requirement R_SPEC；

S4: using satellite task index now as the space radiation environment reliability index of device；

Mission requirements index R of space radiation environment reliability index_SPECAccording to formula (4) and (5) determine,

R_SPEC=1/ λ_{Device-radiation} (5)

Wherein, t_{Device-radiation}For 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 corresponding_realDetermined by formula (6),

${\mathrm{RDM}}_{real}=\frac{R_{MF}}{R_{SPEC}}---\left(6\right)$

Wherein, R_MFFor 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 DPM_Satellite,

DPM_Satellite=(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 DPM_Satellite, and calculate satellite spatial radiation environment according to formula (2) Break period Controlling model DPM_{Satellite-radiation},

DPM_{Satellite-radiation}=ω × DPM_Satellite (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 environment_{Satellite-radiation}, and empty according to formula (3) calculating device Between the break period Controlling model DPM of radiation environment_{Device-radiation},

DPM_{Device-radiation}=DPM_{Satellite-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 reliability_SPECIt 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 RDM_realLess than RDM_SPECTime, then reappraise device after taking safeguard procedures Actual capability of resistance to radiation, repeat step S3；If RDM cannot be made by safeguard procedures_real Meet task index requirement R_SPEC, then change device, repeat step S1 to S4, until RDM_real Meet task index requirement R_SPEC。