CN110472331A - Reduce the layout optimization method of sensitive single machine dose of radiation in satellite capsule - Google Patents
Reduce the layout optimization method of sensitive single machine dose of radiation in satellite capsule Download PDFInfo
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Abstract
The present invention provides a kind of layout optimization methods of sensitive single machine dose of radiation in reduction satellite capsule, comprising: S1, building satellite in orbit dose of radiation depth curve；S2, obtain space environmental monitor actual measurement satellite x, y and z to total radiation dosage value；S3, the total radiation dosage simulation model for establishing satellite in orbit；S4, fining emulation is carried out to satellite in orbit；S5, total radiation dosage region division is carried out to satellite mounting plate；S6, just successive step is carried out to single machine layout on mounting plate；S7, the contiguous range of core single machine mass center is scanned for, the mass center of core single machine is adjusted to total radiation dosage lowest position；S8, position adjustment is carried out according to the method for step S7 to the multiple cores single machine of satellite in orbit；S9, for the core single machine for not reaching anti-total radiation dosage index, the adjustment of weight low dosage position such as carry out.Layout optimization method of the invention can reduce single machine dose of radiation, reduce the in-orbit risk of electronic component, improve in-orbit reliability.
Description
Technical field
The present invention relates to satellite equipment technical fields, and in particular, to sensitive single machine radiation agent in a kind of reduction satellite capsule
The layout optimization method of amount.
Background technique
Satellite in orbit during, various high energy charged particles can be met with, can be to satellite surface material, integrated circuit system
System, optical window, temperature control surface etc. generate radiation injury, cause satellite performance degradation and functional fault, influence satellite task
It completes, wherein influencing that the serious is component total dose damages on star, it is therefore desirable to the emphasis single machine in-orbit longevity in a kind of reduction star
Life phase dose of radiation, weakens the layout optimization method of in-orbit risk.
By the retrieval to the prior art, application No. is 201410438577.0 patents of invention to disclose a kind of satellite area
The method of domain layout, is arranged in service module dashboard for stand-alone device；Calculate with dashboard stand-alone device connecting cable weight and
Dashboard mass property is distributed stand-alone device heat consumption on the contribution of satellite platform mass property, dashboard, using interference checking
Dashboard general assembly situation i.e. northern dashboard folding in mode Analysis Service cabin is easy, cable-to-cable connector plug implementation cost is small, cable
It is enough to move towards space；Calculated result is compared analysis according to the constraint condition in satellite stand-alone device layout principles, if
It is unsatisfactory for constraint condition, then position of return step (1) the adjustment stand-alone device on northern dashboard, repeats step (2), until full
Constraint condition requirement in sufficient satellite stand-alone device layout principles.The technical solution, which mainly solves satellite layout, to be effectively decoupled
The problem of, and emphasis single machine in-orbit life-span phase dose of radiation in star can not be reduced, in-orbit risk cannot be weakened.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide single machine radiation agents sensitive in a kind of reduction satellite capsule
The layout optimization method of amount.
The layout optimization method of sensitive single machine dose of radiation in a kind of reduction satellite capsule provided according to the present invention, including with
Lower step:
Dose of radiation depth curve in S1, building satellite in orbit lifetime；
S2, obtain the satellite in orbit x of space environmental monitor actual measurement to, y to z to total radiation dosage value；
S3, the total radiation dosage simulation model for establishing satellite in orbit；
S4, the total radiation dosage simulation model established according to the dose of radiation depth curve and step S3 of step S1 building,
Fining emulation is carried out to satellite in orbit；
S5, total radiation dosage region division is carried out to satellite mounting plate according to the fining simulation result of step S4；
S6, the satellite in orbit x obtained according to step S2 to, y to z to total radiation dosage value combination step S5 obtain
It is overall to obtain whole star single machine as a result, to the first successive step of single machine layout progress on mounting plate for mounting plate total radiation dosage region division
Just layout；
S7, on the basis of whole star single machine that step S6 is obtained overall just layout, to the contiguous range of core single machine mass center
It scans for, the mass center of core single machine is adjusted to total radiation dosage lowest position；
S8, position adjustment is carried out according to the method for step S7 to the multiple cores single machine of satellite in orbit；
S9, for the core single machine for not reaching anti-total radiation dosage index, then need former according to equal weight low radiation dose
Then readjust the position of core single machine.
Further, in the step S1, according to the launch date of satellite in orbit, track six roots of sensation number, solar cycle,
In-orbit mission bit stream utilizes the dose of radiation depth curve in environment geometric modeling satellite in orbit lifetime.
Further, the radiation agent magnitude in the dose of radiation depth curve is that Si material is inhaled under Equivalent A l shielding thickness
The dose of radiation of receipts.
Further, in the step S3, the construction method of total radiation dosage simulation model is as follows: by the three of satellite in orbit
Dimension module imports in SRET software, after simplifying processing, is penetrated centered on designated analysis point by the solid angle theaomni-directional transmission of setting
Line calculates point of the crossing length and shielding thickness of the threedimensional model of ray and all satellites in each solid angle direction
Cloth, the total radiation dosage for the analysis site to be calculated is the summation of the dose of radiation of each covering of the fan section, to complete global radiation
The building of dosage simulation model and the calculating of total radiation dosage.
Further, in the step S4, it is as follows that fining emulation mode is carried out to satellite in orbit:
S41, using a certain single machine as simulation objectives, choose single machine mounting plate on an angle point as calculate initial position,
Along diagonal line options n positions of mounting plate, the complicated lower total radiation dosage value D (x, y) of shielding in star is calculated；
S42, in total radiation dosage simulation model, set single machine casing thickness value, total spoke done to the positions n of selection
Dosage simulation calculation is penetrated, n total radiation dosage value is obtained；
S43, change second of calculating of single machine casing thickness progress, obtain n total radiation dosage value of single machine under the thickness；
And so on, change single machine casing thickness and carry out n-th calculating, obtains the total radiation dosage value of single machine under respective thickness.
Further, in the step S4, n=6, N=3.
Further, in the step S5, according to the fining simulation result of step S4, satellite in orbit mounting plate is divided
For accumulated dose region, the low accumulated dose region of core in the high accumulated dose region in outside, sublevel.
Further, in the step S6, in star on mounting plate, according to the region that step S5 is divided, radiation outside is high
The low accumulated dose region of accumulated dose region > core in accumulated dose region > sublevel carries out component rational deployment according to significance level,
That is different degree ICore> ISublevel> IOutside；Insensitive and bulky single machine is mounted on around partition to block internal layer as far as possible simultaneously
Sensitive core single machine.
Further, step S7's specific steps are as follows: centered on the centroid position of core single machine, at it
M positions of setting in contiguous range, the core single machine total radiation dosage value of simulation calculation m positions of difference, according to result
Centroid position is adjusted to total radiation dosage value lowest position, and with the minimum priority principle of shift in position.
Further, step S9's specific steps are as follows: core that will not reach anti-total radiation dosage index
Heart single machine is close with other volume weights, the lower another core single machine of total radiation dose required value carries out position exchange, repeats
Operation, until core single machines all in star all meet anti-total radiation dosage index.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, layout method of the present invention comprehensively considers satellite launch date, in-orbit life-span, in-orbit space environment, typical first device
Part capability of resistance to radiation blocks effect, the actual measurement direction the xyz agent of satellite spatial environment monitor to high energy particle in conjunction with satellite covering
The single machine mounting plate that magnitude, installation partition obtain ground location, the anti-radiation grade of component, fining emulation relative to satellite
Dose of radiation region segmentation, single machine centroid position optimal location neighborhood search etc., dose of radiation angle carries out cabin out of lifetime
Interior emphasis single machine layout optimization reduces single machine dose of radiation, reduces the in-orbit risk of electronic component, improves in-orbit reliability.
2, compared to the resistant to total dose protection design of existing satellite excessively rely on people experience and in-orbit flight test result,
Layout method of the present invention is practiced in conjunction with satellite engineering, from system-level angle, is formd for the reinforcing of satellite resistant to total dose
The complete set method of layout optimization, operability are strong with realizability.
3, layout method of the present invention operates in the satellite of severe orbital environment for subsequent may emit, such as satellite
It operates in repeatedly for a long time by the severe track at inner radiation belt center, this method can be applied directly, to severe orbital environment
The layout of lower satellite optimizes, and improves satellite system resistant to total dose ability, has directly effective satellite engineering practice
Meaning.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is dose of radiation depth curve (2017-2025) in low orbit (LEO) satellite in orbit lifetime
Fig. 2 is dose of radiation depth curve (2018-2026) in geostationary orbit (GEO) lifetime of satellite phase
Fig. 3 is the 2014-2017+y of low orbit (LEO) satellite spatial environment supervision instrument acquisition, the direction+z accumulated dose
Value；
Fig. 4 is that the 2016-2017 x, y, z direction that geostationary orbit (GEO) satellite spatial environment monitor obtains is total
Dose value；
Fig. 5 is the construction method flow chart of satellite total radiation dosage simulation model；
Fig. 6 is mobile schematic layout pattern of the target single machine on a mounting board based on fining emulation mode；
Fig. 7 is simulated dose result under 6 point difference casing thickness of single machine linear search；
Fig. 8 is mounting plate total radiation dosage region segmentation figure；
Fig. 9 is the neighborhood search optimization method schematic diagram of single machine centroid position；
Figure 10 is 5 simulated dose results of emphasis single machine neighborhood search.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
The present invention provides a kind of in-orbit actual measurement x, y, z of combination satellite spatial environment monitor respectively to dose of radiation, satellite capsule
Interior each single machine total radiation dose refines simulation value, reduces the layout optimization adjustment side of sensitive single machine total radiation dose in satellite capsule
Method.Satellite in orbit is obtained first and surveys x to, y to, z to accumulated dose value, is directly met in conjunction with satellite earth observation demand and windward side
By High energy particles Radiation, to sensitive single machine along distributing adjustment at the beginning of whole star xyz to progress；According to single machine position on mounting plate in star
Accumulated dose fining emulation, carries out accumulated dose region segmentation to mounting plate, carries out fine cloth to sensitivity single machine important on mounting plate
Office's adjustment；The constraints such as mechanical environment, thermal control, electromagnetic compatibility and single machine position change are not generated meeting the installation of satellite single machine
It influences under constraint to a certain degree, the neighborhood search of mass center is carried out to core single machine, found in the mass center neighborhood of single machine and resist total agent
Measure optimal location；The adjustment that weight low dosage position is carried out etc. to the core single machine for being still unsatisfactory for resistant to total dose index demand, goes forward side by side
The corresponding counterweight of row.
The layout optimization method of sensitive single machine dose of radiation in a kind of reduction satellite capsule provided according to the present invention, including with
Lower step:
S1, according to launch date, the track of low orbit (LEO) satellite in orbit and geostationary orbit (GEO) satellite in orbit
Six roots of sensation number, solar cycle period parameters, in-orbit mission bit stream etc., using in semi-infinite slab model construction satellite in orbit lifetime
Dose of radiation depth curve f1, radiation agent magnitude therein is the dose of radiation that Si material absorbs under Equivalent A l shielding thickness,
As shown in Figure 1, 2；
Calculate the composite material and combined material Equivalent A l shielding thickness of low orbit satellite, satellite, it is contemplated that can
2-5 times of error can be introduced, star material Equivalent A l shielding thickness is obtained:
1 star of table material Equivalent A l shielding thickness
| Serial number | Material | Equivalent aluminium shielding thickness |
| 1. | The aluminum honeycomb panel of 0.3mm carbon fiber face sheets | 0.5mm |
| 2. | The aluminum honeycomb panel of 0.3mm aluminum deck | 0.7mm |
| 3. | Al covering cellular board | 1.6mm |
| 4. | C covering cellular board | 1mm |
| 5. | Satellite covering | 0.6mm |
。
S2, the direction+the y ,+z accumulated dose value D for obtaining the actual measurement of LEO satellite space environmental monitor+y、D+z, LEO satellite actual measurement
Dosage D+y>D+z；GEO satellite+x ,+x deflect 30 ° ,-x deflection 30 °, the direction+y ,-y ,-z accumulated dose value D+x、D+x30、D-x30、D+y、
D-y、D-z；GEO satellite surveys dosage D+x30>D-x30>D+x>D-z>D+y>D-y；As shown in Figure 3,4, wherein 6 of GEO satellite pop one's head in
Installation direction and shielding thickness are as shown in table 2:
The 6 probe installation directions and shielding thickness of certain the GEO meteorological satellite of table 2
| Probe | Installation direction | Shielding thickness |
| A | -Z | 1mm |
| C | +Y | 1mm |
| E | +X 30° | 1mm |
| F | -X 30° | 1mm |
| G | +X | 1mm |
| H | -Y | 1mm |
。
S3, satellite proe structural model is established, as shown in figure 5, defining geometry material, model simplification is handled, is imported into
In SRET software, satellite accumulated dose simulation model is obtained；The construction method of total radiation dosage simulation model is as follows: by satellite in orbit
Threedimensional model import SRET software in, simplify processing after, centered on designated analysis point by setting solid angle omnidirectional hair
Ray, the crossing length and shielding thickness for calculating the threedimensional model of ray and all satellites are in each solid angle direction
Distribution, the total radiation dosage for the analysis site to be calculated is the summation of the dose of radiation of each covering of the fan section, to complete total
The building of dose of radiation simulation model and the calculating of total radiation dosage.
S4, the total radiation dosage simulation model established according to the dose of radiation depth curve and step S3 of step S1 building,
Fining emulation is carried out to satellite in orbit；It is as follows to refine emulation mode:
S41, as shown in fig. 6, in satellite total radiation dosage simulation model, using a certain single machine as simulation objectives, choose single
" O " point on machine mounting plate, along 6 positions of the diagonal line options of mounting plate, calculates in LEO, GEO star as initial position is calculated
Complexity shields lower total radiation dose value D (x, y) value；
S42, diagonally 6 points of line selection do accumulated dose simulation calculation, for the first time calculate, set single machine casing thickness as
D1, i.e. 1mm, simulation calculation obtain the 1st point D1mm(x1,y1), the 2nd point D1mm(x2,y2), the 3rd point D1mm(x3,y3), the 4th
Point D1mm(x4,y4), the 5th point D1mm(x5,y5), the 6th point D1mm(x6,y6)；
S43, change second of calculating of single machine casing thickness progress, single machine casing thickness d2, i.e. 2mm, simulation calculation are set
1st point D2mm(x1,y1), the 2nd point D2mm(x2,y2), the 3rd point D2mm(x3,y3), the 4th point D2mm(x4,y4), the 5th point
D2mm(x5,y5), the 6th point D2mm(x6,y6)；The casing thickness for changing single machine again, is taken as d3, i.e. 3mm, it is total to calculate 6 points
Dose value D3mm(x1,y1)、D3mm(x2,y2)、D3mm(x3,y3)、D3mm(x4,y4)、D3mm(x5,y5)、D3mm(x6,y6)。
S5, such as Fig. 7 (abscissa L: and the distance value of initial position O point.Unit is mm, indicates opposite position in threedimensional model
Set) result it is found that according to the fining simulation result of step S4, obtains target single machine and diagonally puts down from initial position 1
Moving to a little 6, the total radiation dosage of mounting plate can be carried out region segmentation by the changing rule of accumulated dose position on a mounting board,
It is specifically divided into the high accumulated dose region in outside, accumulated dose region, the low accumulated dose region of core in sublevel, the high accumulated dose area in radiation outside
The low accumulated dose region of accumulated dose region > core in domain > sublevel, as shown in Figure 8.
S6, the satellite in orbit x obtained according to step S2 to, y to z to total radiation dosage value, i.e. LEO satellite surveys agent
Measure D+y>D+z, GEO satellite survey dosage D+x30>D-x30>D+x>D-z>D+y>D-y, the mounting plate global radiation agent that is obtained in conjunction with step S5
Region division is measured as a result, carrying out component rational deployment in star on mounting plate according to significance level, considering satellite earth observation
Core load is mounted on to ground +Z direction by demand, and windward side is directly by High energy particles Radiation, therefore in LEO satellite sensitivity
When single machine is installed, quantity term meets n+z> n+y> n+xMeet I with different degree+z> I+y> I+x；Pacify in GEO satellite sensitivity single machine
When dress, quantity term meets n+z> n-y> n+y> n+x> n-zMeet I with different degree+z> I-y> I+y> I+x> I-z；Pacify in star
In loading board, due to the low accumulated dose region of accumulated dose region > core in the high accumulated dose region > sublevel in radiation outside, so can be according to
Significance level carries out single machine rational deployment, i.e. different degree ICore> ISublevel> IOutside；Simultaneously as far as possible by insensitive and bulky single machine
It is mounted on around partition to block internal layer sensitive core single machine；After above-mentioned just successive step, the overall just cloth of whole star single machine is obtained
Office；
S7, on the basis of whole star single machine that step S6 is obtained overall just layout, carry out core single machine adjustment: core single machine
In the δ contiguous range of mass center, is adjusted with not influencing mechanical property, the Electro Magnetic Compatibility etc. of satellite layout, carry out the total agent of neighborhood
Optimal location search is measured, δ can use in 10cm, 20cm circle.As shown in figure 9, specifically: during the centroid position with core single machine is
M positions are arranged in the heart in its contiguous range, it is assumed that m takes 5,5 point 3mmAl of simulation calculation to shield global radiation agent in lower star
Magnitude D (a), D (b), D (c), D (d), D (e), the results are shown in Figure 10；Centroid position is adjusted to global radiation agent according to result
At magnitude extreme lower position d, and with the minimum priority principle of shift in position；
S8, according to the method for step S7, optimal location search is carried out in δ neighborhood to the multiple cores single machine of satellite in orbit,
Seek optimal solution, carries out position adjustment；
If a certain core single machine of S9, satellite does not reach estimated resistant to total dose index request, need to readjust
The position of core single machine；Specifically: according to equal weight low radiation dose principle, it will not reach the core of anti-total radiation dosage index
Single machine is close with other volume weights, the lower another core single machine of total radiation dose required value carries out position exchange, and carries out
Reasonable counterweight.Above-mentioned single machine layout adjustment method is repeated, until core single machines all in star all meet anti-total radiation dosage index.
In the description of the present application, it is to be understood that term " on ", "front", "rear", "left", "right", " is erected at "lower"
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is orientation based on the figure or position
Relationship is set, description the application is merely for convenience of and simplifies description, rather than the device or element of indication or suggestion meaning are necessary
It with specific orientation, is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. a kind of layout optimization method for reducing sensitive single machine dose of radiation in satellite capsule, which comprises the following steps:
Dose of radiation depth curve in S1, building satellite in orbit lifetime；
S2, obtain the satellite in orbit x of space environmental monitor actual measurement to, y to z to total radiation dosage value；
S3, the total radiation dosage simulation model for establishing satellite in orbit；
S4, according to step S1 building dose of radiation depth curve and step S3 establish total radiation dosage simulation model, to
Rail satellite carries out fining emulation；
S5, total radiation dosage region division is carried out to satellite mounting plate according to the fining simulation result of step S4；
S6, the satellite in orbit x obtained according to step S2 to, y to z to the obtained installation of total radiation dosage value combination step S5
Plate total radiation dosage region division obtains the overall just cloth of whole star single machine as a result, to the first successive step of single machine layout progress on mounting plate
Office；
S7, contiguous range progress on the basis of the whole star single machine that step S6 is obtained overall just layout, to core single machine mass center
Search, is adjusted to total radiation dosage lowest position for the mass center of core single machine；
S8, position adjustment is carried out according to the method for step S7 to the multiple cores single machine of satellite in orbit；
S9, for the core single machine for not reaching anti-total radiation dosage index, then need according to equal weight low radiation dose principle weight
The position of new adjustment core single machine.
2. the layout optimization method according to claim 1 for reducing sensitive single machine dose of radiation in satellite capsule, feature exist
In, in the step S1, according to the launch date of satellite in orbit, track six roots of sensation number, solar cycle, in-orbit mission bit stream,
Utilize the dose of radiation depth curve in environment geometric modeling satellite in orbit lifetime.
3. the layout optimization method according to claim 2 for reducing sensitive single machine dose of radiation in satellite capsule, feature exist
In the radiation agent magnitude in the dose of radiation depth curve is the dose of radiation that Si material absorbs under Equivalent A l shielding thickness.
4. the layout optimization method according to claim 1 for reducing sensitive single machine dose of radiation in satellite capsule, feature exist
In in the step S3, the construction method of total radiation dosage simulation model is as follows: the threedimensional model of satellite in orbit is imported SRET
In software, after simplifying processing, by the solid angle theaomni-directional transmission ray of setting centered on designated analysis point, ray and institute are calculated
There is the distribution of the crossing length and shielding thickness of the threedimensional model of satellite in each solid angle direction, point to be calculated
The total radiation dosage of analysis point is the summation of the dose of radiation of each covering of the fan section, to complete the structure of total radiation dosage simulation model
Build the calculating with total radiation dosage.
5. the layout optimization method according to claim 1 for reducing sensitive single machine dose of radiation in satellite capsule, feature exist
In, in the step S4, to satellite in orbit carry out fining emulation mode it is as follows:
S41, using a certain single machine as simulation objectives, choose single machine mounting plate on an angle point as calculate initial position, along peace
Diagonal line options n positions of loading board；
S42, in total radiation dosage simulation model, set single machine casing thickness value, global radiation agent done to the positions n of selection
Simulation calculation is measured, n total radiation dosage value is obtained；
S43, change second of calculating of single machine casing thickness progress, obtain n total radiation dosage value of single machine under the thickness；With this
Analogize, changes single machine casing thickness and carry out n-th calculating, obtain the total radiation dosage value of single machine under respective thickness.
6. the layout optimization method according to claim 5 for reducing sensitive single machine dose of radiation in satellite capsule, feature exist
In, in the step S4, n=6, N=3.
7. the layout optimization method according to claim 1 for reducing sensitive single machine dose of radiation in satellite capsule, feature exist
According to the fining simulation result of step S4, satellite in orbit mounting plate is divided into the high accumulated dose in outside in the step S5
Accumulated dose region, the low accumulated dose region of core in region, sublevel.
8. the layout optimization method according to claim 1 for reducing sensitive single machine dose of radiation in satellite capsule, feature exist
In in the step S6, in star on mounting plate, according to the region that step S5 is divided, the high accumulated dose region > sublevel in radiation outside
The low accumulated dose region of middle accumulated dose region > core carries out component rational deployment, i.e. different degree I according to significance levelCore> ISublevel
> IOutside；Insensitive and bulky single machine is mounted on around partition as far as possible to block internal layer sensitive core single machine simultaneously.
9. the layout optimization method according to claim 1 for reducing sensitive single machine dose of radiation in satellite capsule, feature exist
In, step S7's specific steps are as follows: centered on the centroid position of core single machine, it is arranged in its contiguous range
M positions, the core single machine total radiation dosage value of simulation calculation m positions, adjusts centroid position according to result respectively
To total radiation dosage value lowest position, and with the minimum priority principle of shift in position.
10. the layout optimization method according to claim 1 for reducing sensitive single machine dose of radiation in satellite capsule, feature exist
In, step S9's specific steps are as follows: will not reach the core single machine and other bodies of anti-total radiation dosage index
The lower another core single machine of product similar weight, total radiation dose required value carries out position exchange, repetitive operation, until institute in star
There is core single machine all to meet anti-total radiation dosage index.
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| CN111339676A (en) * | 2020-03-10 | 2020-06-26 | 中国科学院国家空间科学中心 | Near-earth space environment comprehensive data analysis system |
| CN113543615A (en) * | 2021-06-29 | 2021-10-22 | 中国科学院长春光学精密机械与物理研究所 | Irradiation protection method for space electronic equipment |
| CN114655472A (en) * | 2022-03-09 | 2022-06-24 | 中国科学院微小卫星创新研究院 | Composite protection method for total irradiation dose of middle rail track space |
| CN115438559A (en) * | 2022-10-14 | 2022-12-06 | 北京空间飞行器总体设计部 | Ground irradiation test method for simulating on-orbit dose distribution of star surface material |
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| CN114655472A (en) * | 2022-03-09 | 2022-06-24 | 中国科学院微小卫星创新研究院 | Composite protection method for total irradiation dose of middle rail track space |
| CN115438559A (en) * | 2022-10-14 | 2022-12-06 | 北京空间飞行器总体设计部 | Ground irradiation test method for simulating on-orbit dose distribution of star surface material |
| CN115438559B (en) * | 2022-10-14 | 2023-03-10 | 北京空间飞行器总体设计部 | Ground irradiation test method for simulating on-orbit dose distribution of star surface material |
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