CN110108840A - The method for determining the space environment synergistic effect degree of correlation - Google Patents
The method for determining the space environment synergistic effect degree of correlation Download PDFInfo
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- CN110108840A CN110108840A CN201910375011.0A CN201910375011A CN110108840A CN 110108840 A CN110108840 A CN 110108840A CN 201910375011 A CN201910375011 A CN 201910375011A CN 110108840 A CN110108840 A CN 110108840A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/24—Investigating strength properties of solid materials by application of mechanical stress by applying steady shearing forces
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N33/00—Investigating or analysing materials by specific methods not covered by groups G01N1/00 - G01N31/00
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N33/00—Investigating or analysing materials by specific methods not covered by groups G01N1/00 - G01N31/00
- G01N2033/0003—Composite materials
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0025—Shearing
Abstract
The present invention discloses a kind of determination method of space environment synergistic effect degree of correlation, and this method includes determining high/low temperature alternation environment according to in-orbit orbital environment；Composite material is chosen, grouping is subjected to several space environment states；Environmental effect test is completed according to testing program；According to the effect principle of equal effects, when determining atomic oxygen test dosage and testing machine；Formulate thermal cycling test parameter；Two factor environment matrix tests are completed, and the test specimen performance parameter test after being tested；Intersection comparison is carried out to the test data in matrix table, is added property coefficient with the simple adduction ratio of single factor experiment result respectively.The present invention by understanding, processing and the extrapolation of ground single factor test and sequential action test data, probe into, can action effect carries out estimating anticipation, effective room for promotion Research on Environmental Test validity simultaneously to in-orbit space environment factor.
Description
Technical field
The invention belongs to space environments and effect the field of test technology, specifically, the present invention relates to assist under space environment
With the determination method of the effect degree of correlation.
Background technique
Currently, the development of aeronautical and space technology, result in the need for degree of impairment to Spacecraft Material under space environment into
Row research, so that spacecraft can realize aerospace task under secure conditions, but in the spatial loop of Spacecraft Material
Under the simulated conditions of border, need to fully understand correlation effect below.
1) space environment and its effect
Influence and damage of the complicated space environment to space structure material are very important key factors, it can be direct
Spacecraft is influenced normally to run, work and in-orbit service life.Understand space environment and its effect, grasps environment to spacecraft
The influence of structural material performance is the basis for carrying out Spacecraft guidance and control.Space environment factor is varied, mainly includes sun electricity
Magnetic radiation, charged particle radiation, high vacuum, cold darkness environment, atomic oxygen erosion and micrometeor and the shock of space junk etc..
Their influences to spacecraft and its construction package are also different.
2) synergistic property of space environment effect
The study found that the simple superposition of ground single environment factor and the in-orbit true performance degradation result being subjected to of material
It is not fully consistent.
Elemental oxygen and ultraviolet light have a synergism to the damage of material, but for different materials difference.Low rail flies
Variation of the siliceous and fluorine-containing polymer film under space environment is studied in row test, the results showed that, fluorine-containing polymerization
Object corrodes seriously, light transmittance degradation, and siliceous polymer film erosion rate very little, and light transmittance is without significant change.For
Vacuum ultraviolet/elemental oxygen has comparable research to the reciprocation of polymer material both at home and abroad.
The synergistic effect research of elemental oxygen and charged particle irradiation is appeared in the newspapers for elemental oxygen and ultraviolet irradiation
Road is less.The synergistic effect that T.King and Warren Wilson has carried out elemental oxygen and electronics to polysulfone resin material is tested, right
Elemental oxygen under electron bombardment has carried out measurement analysis to material effects product, and with the test result under the conditions of no electron bombardment
It is compared.The result shows that when insulated with material, effect product of the elemental oxygen to polysulfone resin material under the conditions of electron bombardment
It increased significantly.The reason of this phenomenon of author's preliminary analysis generation, it is believed that be that the electrification of material surface caused by electronics generates electricity
Caused by.
Between elemental oxygen and thermal cycle in terms of synergistic effect research, carbon/cyanate based composites development test is selected
Studies have shown that thermal cycle promotes the anti-atomic oxygen ability (mechanical property) of material.
The degree that the synergism of space junk and elemental oxygen is corroded aggravation space material significantly.Less than 1mm's
Space micro-debris will not usually cause catastrophic failure to spacecraft, but the collision probability since quantity is big, with spacecraft
Height, long-term accumulation effect caused by the multiple impact of surface is apparent.Under the shock of minute fragments, space function is anti-
Many pin holes or crackle are generated on cuticula, although these defects are so small that be difficult to find, provided one to elemental oxygen and are entered base
The channel of bottom material is caused elemental oxygen " to dive and lose " under protective layer and is emptied, and causes imitative sheath tearing and falls off, and then causes to prevent
Shield measure failure, the especially planar array antenna to large area slab structure and solar array harm are bigger.
Under charged particle radiation and the synergism of solar electromagnetic radiation, surface layer heat control material and optical device, especially
It is Organic Thermal Control Coating, biggish degeneration or even failure will occur for performance.This is because charged particle radiation may not only be beaten
The chemical valence link of disconnected organic material, and can cause material internal that ionisation effect or displacement effect occurs；And ultraviolet irradiation is not only
Valence link can be caused to be broken or even ionize, and may cause the aggravation of charged particle radiation damage or the reparation of damage.
Solar array is exposed to space, and the probability by impact from space debris is very high.Static discharge must be
Edge occurs, however, ejecta and pollution that ultrahigh speed fragment generates can be easier to induce high pressure sun array compared with static discharge
Secondary arc, the phenomenon have obtained the confirmation of Crawford and Schultz et al. work.
The damage of spacecraft may occur to hit and cause with spacecraft for space junk and micrometeroroid, the type of damage with
Degree depends on the characteristics such as spacecraft size, configuration, working time and micrometeroroid quality, density, speed.This shock damage
Wound include the rupture of pressure vessel, the degeneration of porthole, thermal control coating layer split, the damage of the reduction of thermal protective performance and antenna system
Wound etc..In addition to the accumulation from natural pollution and spacecraft itself volatilization pollution, pollution can also be since spacecraft be by space
The superelevation of fragment and micrometeroroid is hit and is generated.
Thus, on the basis of having understood and grasped single space environment factor influences material property, carry out spatial loop
The synergistic effect research of border factor has a very important significance for correctly estimating the degeneration of Spacecraft Material on-orbit performance,
It is to lay the foundation for the research of multifactor environmental effect ground simulation experiment method.
3) the problem of the research of space environment synergistic effect
By more comprehensive investigation, it will be seen that for space environment, especially low earth orbital environment, state
Inside and outside scholar is studied by means of ground simulation test, space carrying flight test, auxiliary with simulation analysis, has been carried out more
Extensive research has the technical foundation of certain data analysis and analysis anticipation.But to the synergistic property of space environment effect
Research is still in the level of qualitative analysis at present.
This patent proposes the determination method of a kind of pair of space environment synergistic property degree of correlation, the synergism between space environment factor
Property quantization signifying provide it is a kind of according to index.
Summary of the invention
The present invention is based on the ongoing research bases of synergistic property existing between space environment effect and environmental effect field
Plinth.Goal of the invention of the invention is to provide a kind of determination method of quantizating index for characterizing space environment effect synergistic property, use
To characterize the synergistic property of different spaces environmental activity effect.
The purpose of the present invention is be achieved through the following technical solutions:
Based on the ground simulation test Research foundation of current material space environmental effect, followed for space elemental oxygen with heat
Synergistic property between ring environment effect can be used following scheme and carry out preliminary quantitative analysis to synergism correlation.
The determination method of the space environment synergistic effect degree of correlation of the invention, comprising the following steps:
First, according to the orbital environment of the actual task of the quasi- application of material, elemental oxygen examination is calculated using MSISE90 model
Test input condition；According to in-orbit orbital environment, the high/low temperature alternation environment that can suffer from is determined；
Second, test composite material is chosen, Unidirectional Composites are cut into 20mm × 6mm × 2mm test sample
The composite material of each type is divided into 5 groups by product, to be subjected to and characterize 5 kinds of space environment states respectively, comprising: 1) former
Beginning state；2) single atomic oxygen environment (AO)；3) single cycling environments (TC)；4) cycling environments (AO+ after first elemental oxygen
TC)；5) atomic oxygen environment (TC+AO) after first thermal cycle；
Third completes environmental effect test according to testing program, it may be assumed that 1) first group of sample is placed in vacuum ware protects as former state
Deposit, 2) atomic oxygen test carried out to second group, third group sample, 3) the synchronous thermal cycle carried out to the 4th group, the 5th group sample
Test, 4) the third group sample after atomic oxygen test is subjected to thermal cycling test, 5) by the 5th group of sample after thermal cycling test
Carry out atomic oxygen test；
4th, according to the effect principle of equal effects, atomic oxygen beam current density is marked using Kapton H film quality loss method
It is fixed, and when determining atomic oxygen test dosage and testing machine, it is as follows according to formula:
Atomic oxygen beam current density
Elemental oxygen dosage
Wherein: Δ MkDemarcate the mass loss of Kapton print, g；AkKapton demarcates the irradiated area of print, 4cm2；ρk
Kapton demarcates the density of print, 1.42g/cm3；RkKapton demarcates reactivity of the material under the conditions of atomic oxygen environment of space
4.0×10-24cm3/atom；T rating test duration, s；
5th, thermal cycling test parameter is formulated, and the scenario earthquake in record test of mapping；
6th, preparation before test is carried out, and to the performance parameter test of the 1st group of material；
7th, two factor environment matrix tests are completed, and the test specimen performance parameter test after being tested；
8th, the shear strength test data of 5 groups of samples are recorded, the other Ji Suan ⊿ AO , ⊿ TC , ⊿ (AO+TC) of Fen,
Four groups of shear strength variable quantities of ⊿ (TC+AO)；
9th, intersection comparison carried out to the test data in matrix table, and by the test knot after the test of two-way sequential action
Fruit respectively with the ratio of the simple adduction of single factor experiment result, that is, additivity system It is calculated, is named as sequentially test effect and is added property coefficient；
Tenth, according to calculating formulaThe calculating for carrying out the synergistic effect degree of correlation, is named as association
Close relative coefficient K.
Wherein, the performance parameter is cutting performance parameter.
Wherein, the cutting performance parameter is obtained by shearing test, and shearing test uses 3 short beam methods, by per minute
1~2mm/min loading velocity continuously loads sample.
Wherein, the interlaminar shear strength calculation formula of the shearing test is
In above formula, PmaxPeak load (N) when to be broken, ω are Sample Width (mm), and h is thickness of sample (mm), are tested
Journey is executed according to GB/T 30969-2014.
The interactive synergistic effect of material and space environment factor is evaluated in the proposition of quantizating index of the invention,
It is of great significance.
First, the synergistic effect of space environment is evaluated, the product in terms of physical chemistry straight-forward phenomenon is no longer limited only to
It is tired, but by the processing to the quantifiable test result such as Mechanics Performance Testing, obtain to " whether there is synergistic property " and
The quantization signifying (characterization including directionality) of " synergism degree of correlation ".
Second, by the understanding of ground single factor test and sequential action test data, processing and extrapolation, probe into, can to
Action effect carries out estimating anticipation, effective room for promotion Research on Environmental Test validity rail space environment factor simultaneously.
Third, by the synergistic effect data accumulation of extensive types of material and environmental factor, by synergism correlation
Quantization, different materials and environmental effect reciprocation synergistic effect degree of correlation can be ranked up, be spacecraft selection
Foundation is provided.
Detailed description of the invention
Fig. 1 tests layout process's schematic diagram to test the first step of development in method of the invention.
Fig. 2 is thermal cycling test temperature profile in method of the invention.
Specific embodiment
Introduced below is the specific embodiment as content of the present invention, below by specific embodiment to this
The content work of invention further illustrates.Certainly, description following detailed description is only example not Tongfang of the invention
The content in face but should not be understood as the limitation scope of the invention.
Referring to Fig. 1, Fig. 1 tests layout process's schematic diagram to test the first step of development in method of the invention.This hair
The determination method of the bright space environment synergistic effect degree of correlation, including following procedure:
First, by taking the in-orbit 1 year quasi- track task environment being subjected in space station as an example, calculated using MSISE90 model
The elemental oxygen fluence being subjected to during rail is 1.5 × 1020atoms/cm2；According to in-orbit orbital environment, estimating out be can suffer from
High/low temperature alternation environment be [- 150 DEG C ,+150 DEG C] section in 200 times circulation.
Second, choose polymer matrix composites M40/EXP-1, M40/EXP-N3, M40/CYA- of three kinds of fibre reinforceds
80 be test material, and Unidirectional Composites are cut into 20mm × 6mm × 2mm test specimen, by every kind of composite material point
It is 5 groups, to be subjected to and characterize 5 kinds of space environment states respectively, comprising: 1) reset condition；2) single atomic oxygen environment (AO)；
3) single cycling environments (TC)；4) cycling environments (AO+TC) after first elemental oxygen；5) atomic oxygen environment (TC+ after first thermal cycle
AO)。
Laboratory sample environment attribute
Third, according to testing program, draw testing program schematic diagram (attached drawing 1) i.e.: 1) first group of sample is placed in vacuum
Saved as former state in ware, 2) atomic oxygen test carried out to second group, third group sample, 3) synchronous carry out to the 4th group, the 5th group of sample
The thermal cycling test of product, 4) the third group sample after atomic oxygen test is subjected to thermal cycling test, 5) it will be after thermal cycling test
5th group of sample carries out atomic oxygen test.
4th, according to the effect principle of equal effects, atomic oxygen beam current density is marked using Kapton H film quality loss method
Fixed, Kapton film demarcates sample having a size of 2mm × 2mm, atomic oxygen test dosage 1.5 × 1020atoms/cm2, in conjunction with test line
Density, when calculating testing machine.
5th, formulate thermal cycling test parameter, and the scenario earthquake in record test of mapping (see attached drawing 2).
6th, preparation before test is carried out, and test the mechanical property (cutting performance) of the 1st group of material.
7th, two factor environment matrix tests are completed, and the test specimen Mechanics Performance Testing after being tested.
8th, the shear strength test data of 5 groups of samples are recorded, the other Ji Suan ⊿ AO , ⊿ TC , ⊿ (AO+TC) of Fen,
Four groups of shear strength variable quantities of ⊿ (TC+AO).
Interlaminar shear strength variable quantity of 1 material of table under space environment effect
And the simple adduction of single factor experiment result is calculated.
(1) M40/EXP-1 material
It can be obtained by test data
Δ AO+ Δ TC=-2.63+3.10=0.47 > 0
(2) M40/EXP-N3 material
It can be obtained by test data
Δ AO+ Δ TC=-1.5+9.42=7.92 > 0
(3) M40/CYA-80 material
It can be obtained by test data
Δ AO+ Δ TC=-0.90+4.54=3.64 > 0
9th, intersection comparison is carried out to the test data in matrix table.And the test knot after testing two-way sequential action
Fruit respectively with the ratio (being added property coefficient) of the simple adduction of single factor experiment result Row calculates, and is named as addition property coefficient.
(1) M40/EXP-1 material
0 > Δ (AO+TC) of Δ AO+ Δ TC >
Δ TC+ Δ AO > Δ (TC+AO) > 0
(2) M40/EXP-N3 material
0 > Δ (AO+TC) of Δ AO+ Δ TC >
Δ TC+ Δ AO > Δ (TC+AO) > 0
(3) M40/CYA-80 material
0 > Δ (AO+TC) of Δ AO+ Δ TC >
Δ TC+ Δ AO > Δ (TC+AO) > 0
K ≠ 1 shows that two environmental factors interact to the mechanism of material, and there are synergistic effects；And K=1 shows two
There is no synergistic effects between the mechanism of material for environmental factor.
Tenth, according to calculating formulaThe calculating for carrying out the synergistic effect degree of correlation, is named as association
Close relative coefficient K.K value is bigger, then the synergism degree of correlation is bigger.
(1) M40/EXP-1 material
(2) M40/EXP-N3 material
0 > Δ (AO+TC) of Δ AO+ Δ TC >
Δ TC+ Δ AO > Δ (TC+AO) > 0
(3) M40/CYA-80 material
0 > Δ (AO+TC) of Δ AO+ Δ TC >
Δ TC+ Δ AO > Δ (TC+AO) > 0
Although giving detailed description and explanation to the specific design method and thinking of this patent above, it should be noted that
, we can the conception of patent according to the present invention various equivalent changes and modification are carried out to above embodiment, produced
It, should all be within the protection scope of this patent when the spirit that raw function is still covered without departing from specification and attached drawing.
Claims (4)
1. the determination method of the space environment synergistic effect degree of correlation, comprising the following steps:
First, according to the orbital environment of the actual task of the quasi- application of material, atomic oxygen test is calculated using 90 model of MSISE
Input condition；According to in-orbit orbital environment, the high/low temperature alternation environment that can suffer from is determined；
Second, test composite material is chosen, Unidirectional Composites are cut into 20mm × 6mm × 2mm test specimen, it will
The composite material of each type is divided into 5 groups, to be subjected to and characterize 5 kinds of space environment states respectively, comprising: 1) original shape
State；2) single atomic oxygen environment (AO)；3) single cycling environments (TC)；4) cycling environments (AO+TC) after first elemental oxygen；5)
Atomic oxygen environment (TC+AO) after first thermal cycle；
Third completes environmental effect test according to testing program, it may be assumed that and 1) first group of sample is placed in vacuum ware saves as former state,
2) atomic oxygen test carried out to second group, third group sample, 3) synchronous to carry out the thermal cycle to the 4th group, the 5th group sample and try
Test, 4) by after atomic oxygen test third group sample carry out thermal cycling test, 5) by the 5th group of sample after thermal cycling test into
Row atomic oxygen test；
4th, according to the effect principle of equal effects, atomic oxygen beam current density is demarcated using Kapton H film quality loss method, and
It is as follows according to formula when determining atomic oxygen test dosage and testing machine:
Atomic oxygen beam current density
Elemental oxygen dosage
Wherein: Δ MkDemarcate the mass loss of Kapton print, g；AkKapton demarcates the irradiated area of print, 4cm2；ρkKapton demarcates the density of print, 1.42g/cm3；RkKapton demarcates reactivity of the material under the conditions of atomic oxygen environment of space
4.0×10-24cm3/atom；T rating test duration, s；
5th, thermal cycling test parameter is formulated, and the scenario earthquake in record test of mapping；
6th, preparation before test is carried out, and to the performance parameter test of the 1st group of material；
7th, two factor environment matrix tests are completed, and the test specimen performance parameter test after being tested；
8th, the shear strength test data of 5 groups of samples are recorded, the other Ji Suan ⊿ AO , ⊿ TC , ⊿ of Fen (AO+TC) , ⊿
(TC+AO) four groups of shear strength variable quantities；
9th, intersection comparison is carried out to the test data in matrix table, and the test result after the test of two-way sequential action is divided
It is not added property coefficient with the ratio of the simple adduction of single factor experiment result It is calculated, is named as sequentially test effect and is added property coefficient；
Tenth, according to calculating formulaThe calculating for carrying out the synergistic effect degree of correlation, is named as association
Close relative coefficient K.
2. determining method as described in claim 1, wherein the performance parameter is cutting performance parameter.
3. determining method as described in claim 1, wherein the cutting performance parameter is obtained by shearing test, shearing examination
It tests using 3 short beam methods, sample is continuously loaded by 1~2mm/min loading velocity per minute.
4. determining method as described in claim 1, wherein the interlaminar shear strength calculation formula of the shearing test is
In above formula, PmaxPeak load (N) when to be broken, ω are Sample Width (mm), and h is thickness of sample (mm), and test process is pressed
It is executed according to GB/T 30969-2014.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113405976A (en) * | 2021-06-07 | 2021-09-17 | 北京轩宇空间科技有限公司 | Main control polling acquisition transmission method and device for on-orbit irradiation test |
| CN113722916A (en) * | 2021-09-01 | 2021-11-30 | 北京卫星环境工程研究所 | Method for testing action coefficient of atomic oxygen and material |
| CN113740241A (en) * | 2021-09-13 | 2021-12-03 | 北京卫星环境工程研究所 | Space environment synergistic effect cutting method of nonmetallic material for spacecraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5683757A (en) * | 1995-08-25 | 1997-11-04 | Iskanderova; Zelina A. | Surface modification of polymers and carbon-based materials by ion implantation and oxidative conversion |
| CN106442295A (en) * | 2016-10-19 | 2017-02-22 | 哈尔滨工业大学 | Ground simulation test method of a spatial comprehensive environment effect of polymeric material used for spacecraft |
| CN106644907A (en) * | 2016-10-19 | 2017-05-10 | 哈尔滨工业大学 | Ground-based simulation test method for comprehensive space environment effect of exposure materials for low-earth orbit spacecrafts |
| CN106872348A (en) * | 2017-03-30 | 2017-06-20 | 北京卫星环境工程研究所 | The multifactor space environment cooperative effect test method of metal material |
-
2019
- 2019-05-07 CN CN201910375011.0A patent/CN110108840B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5683757A (en) * | 1995-08-25 | 1997-11-04 | Iskanderova; Zelina A. | Surface modification of polymers and carbon-based materials by ion implantation and oxidative conversion |
| CN106442295A (en) * | 2016-10-19 | 2017-02-22 | 哈尔滨工业大学 | Ground simulation test method of a spatial comprehensive environment effect of polymeric material used for spacecraft |
| CN106644907A (en) * | 2016-10-19 | 2017-05-10 | 哈尔滨工业大学 | Ground-based simulation test method for comprehensive space environment effect of exposure materials for low-earth orbit spacecrafts |
| CN106872348A (en) * | 2017-03-30 | 2017-06-20 | 北京卫星环境工程研究所 | The multifactor space environment cooperative effect test method of metal material |
Non-Patent Citations (2)
| Title |
|---|
| 翟睿琼 等: "低轨道紫外、带电粒子、热循环与原子氧协合效应研究进展", 《真空》 * |
| 邱家稳 等: "航天器空间环境协和效应研究", 《航天器工程》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113405976A (en) * | 2021-06-07 | 2021-09-17 | 北京轩宇空间科技有限公司 | Main control polling acquisition transmission method and device for on-orbit irradiation test |
| CN113405976B (en) * | 2021-06-07 | 2023-06-02 | 北京轩宇空间科技有限公司 | Main control polling acquisition and transmission method and device for on-orbit irradiation test |
| CN113722916A (en) * | 2021-09-01 | 2021-11-30 | 北京卫星环境工程研究所 | Method for testing action coefficient of atomic oxygen and material |
| CN113740241A (en) * | 2021-09-13 | 2021-12-03 | 北京卫星环境工程研究所 | Space environment synergistic effect cutting method of nonmetallic material for spacecraft |
| CN113740241B (en) * | 2021-09-13 | 2023-09-19 | 北京卫星环境工程研究所 | Space environment synergistic effect cutting method of nonmetallic material for spacecraft |
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