CN106644907A - Ground-based simulation test method for comprehensive space environment effect of exposure materials for low-earth orbit spacecrafts - Google Patents
Ground-based simulation test method for comprehensive space environment effect of exposure materials for low-earth orbit spacecrafts Download PDFInfo
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- CN106644907A CN106644907A CN201610911406.4A CN201610911406A CN106644907A CN 106644907 A CN106644907 A CN 106644907A CN 201610911406 A CN201610911406 A CN 201610911406A CN 106644907 A CN106644907 A CN 106644907A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N17/00—Investigating resistance of materials to the weather, to corrosion, or to light
Abstract
The invention discloses a ground-based simulation test method for comprehensive space environment effect of exposure materials for low-earth orbit spacecrafts and relates to the field of space environment effect, aiming at solving the problem that an existing ground-based simulation test method of exposure materials for low-earth orbit spacecrafts fails to implement studies on the comprehensive space environment effect of the exposure materials comprehensively. The ground-based simulation test method includes disposing samples to be tested in a sealed cavity, subjecting the samples to be tested to a dust simulation test prior to atomic oxygen environment and ultraviolet environment tests, vacuumizing the sealed cavity, conducting heat cycle tests, selecting energy of incident electrons and protons according to the thicknesses t of the samples to be tested, subjecting the samples to be tested to a charged particle radiation test, and subjecting the exposure materials for the low-earth orbit spacecrafts to performance testing. The ground-based simulation test method is applicable to space environment effect researches and anti-irradiation strengthening technologies.
Description
Technical field
The invention belongs to space environment effect field, more particularly to Low Earth Orbit spacecraft exposed material spatial synthesis
Environmental effect ground simulation test.
Background technology
Low Earth Orbit, apart from ground 100km～1000km, is earth observation satellite, meteorological satellite, manned spaceship, space
Stand, the primary trace of the spacecraft such as space shuttle.The main spatial environmentss in low orbit area include the earth neutrality upper atmosphere, etc. from
Daughter (ionosphere and sedimentation plasma), earth's magnetic field, the radiation belt of the earth, galactic comic ray, solar cosmic ray, sun electromagnetism spoke
Penetrate, the environment such as meteoric body and fragment.Because low earth orbital environment is very severe, its impact to spacecraft is closed always by people
Note.Practice Space shows：Spatial environmentss are the one of the main reasons for inducing Spacecraft malfunction and exception.Satellite failure both domestic and external
Statistical analysiss show that the failure of spatial environmentss induction accounts for the 40% of total failare.Elemental oxygen in Low Earth Orbit is to material list
The corrosion in face can cause the degeneration of material property, space radiation to make organic material performance degradation, thermal cycle cause scantling
Unstable and mechanical performance declines, and the shock of micrometeroroid and space junk causes material mechanical to damage or even destroy, and superelevation
Vacuum can then cause organic material to decompose transformation, deflate.It should be noted that these factors often synergism, accelerates material
The destruction of material, produces many unexpected results.The Low earth orbit environment effect of research material, exploitation meets spacecraft
The material that can be required and have well adapting to property and durability to spatial environmentss has become a hot subject.Spatial environmentss and boat
The interphase interaction of its device occurs in space, and direct experiment research difficulty is big, carries cost needed for test high.Solve problem
Most basic approach be in ground simulation spatial environmentss.By the research of ground simulation test, spatial environmentss and material phase are disclosed
The basic law of interaction, illustrates the basic feature and mechanism of material space environmental effect, and the achievement in research for being obtained is used
In guiding space application.Therefore, it is highly desirable to set up Low Earth Orbit for effectively expansive space material science and technology research
Spacecraft exposed material spatial synthesis environmental effect ground simulation experiment method.
Low Earth Orbit spatial environmentss are very complicated, at present main research be thermal cycle, solar ultraviolet, dust, elemental oxygen,
The impact of space charged particle radiation and fine vacuum to material.At present, the mankind have accumulated low land under many space single factor test environment
Ball Orbital Space Vehicle exposed material ground simulation experiment method, becomes the mankind and explores the important of understanding materials sciences in space problem
Irreplaceable contribution has been made in foundation, the also development for various countries' aerospace industry.But, these researchs fail to realize comprehensively low
The exposed material spatial synthesis environmental effect research of Earth's orbit spacecraft.
The content of the invention
The present invention is can not in order to solve existing Low Earth Orbit spacecraft exposed material ground simulation experiment method
The problem of exposed material spatial synthesis environmental effect research is realized comprehensively, now provides Low Earth Orbit spacecraft exposed material empty
Between comprehensive environmental effects ground simulation experiment method.
Low Earth Orbit spacecraft of the present invention exposed material spatial synthesis environmental effect ground simulation test side
Method includes two schemes：
The first scheme：Low Earth Orbit spacecraft exposed material spatial synthesis environmental effect ground simulation test side
Method, the method is comprised the following steps：
Step one：To treat that laboratory sample is put in seal cavity, treating laboratory sample carries out dust simulation test, then performs
Step 2；
Step 2：Treating laboratory sample carries out atomic oxygen environment and ultraviolet environments test, then execution step three；
Step 3：To seal cavity evacuation, thermal cycling test is carried out, then execution step four；
Step 4：According to the thickness t of sample to be tested, the energy of incident electron and proton is selected so that electronics and proton
Incident depth be more than 2t, treating laboratory sample carries out charged particle irradiation test, when total fluence or accumulated dose of irradiation particle
When reaching the requirement of test, Low Earth Orbit spacecraft exposed material performance test is carried out, complete Low Earth Orbit spacecraft
With exposed material spatial synthesis environmental effect ground simulation test.
Second scheme：Low Earth Orbit spacecraft exposed material spatial synthesis environmental effect ground simulation test side
Method, the method is comprised the following steps：
Step one：To treat that laboratory sample is put in seal cavity, treating laboratory sample carries out dust simulation test, then performs
Step 2；
Step 2：Treating laboratory sample carries out atomic oxygen environment and ultraviolet environments test, then execution step three；
Step 3：To seal cavity evacuation, then execution step four；
Step 4：According to the thickness t of sample to be tested, the energy of incident electron and proton is selected so that electronics and proton
Incident depth be more than 2t；Laboratory sample is treated while carrying out thermal cycling test and charged particle irradiation test, when irradiation particle
Total fluence or accumulated dose when reaching the requirement of test, carry out Low Earth Orbit spacecraft exposed material performance test, complete
Low Earth Orbit spacecraft exposed material spatial synthesis environmental effect ground simulation test.
Above-mentioned Low Earth Orbit spacecraft exposed material spatial synthesis environmental effect ground simulation experiment method, annular seal space
Temperature control equipment is provided with vivo, and the lead of temperature control equipment connects power supply, temperature control by the vacuum plug of annular seal space
The range of accommodation of device is -180 DEG C～150 DEG C.
Above-mentioned Low Earth Orbit spacecraft exposed material spatial synthesis environmental effect ground simulation experiment method, dust mould
In intending test, dust size is 0.01 μm～500 μm, and dust speed is 1km/s～100km/s.
Above-mentioned Low Earth Orbit spacecraft exposed material spatial synthesis environmental effect ground simulation experiment method, elemental oxygen
In environmental test, atom oxygen energy is 3eV～9eV, and atom flux is 1e10atoms/cm2s～1e19atoms/cm2s；
In ultraviolet environments test, ultraviolet wavelength 0nm～400nm, intensity is 0.1suns～10suns.
Above-mentioned Low Earth Orbit spacecraft exposed material spatial synthesis environmental effect ground simulation experiment method, step 3
In, seal cavity evacuation makes the pressure in seal cavity be 10-1Pa～10-5Pa。
Above-mentioned Low Earth Orbit spacecraft exposed material spatial synthesis environmental effect ground simulation experiment method, thermal cycle
In test, heat up and rate of temperature fall is 0.01 DEG C/min～50 DEG C/min, and temperature retention time enables to treat laboratory sample surface
It is identical with the temperature inside laboratory sample is treated.
Above-mentioned Low Earth Orbit spacecraft exposed material spatial synthesis environmental effect ground simulation experiment method, its feature
Be, in charged particle irradiation test, the incident direction of proton perpendicular to treating laboratory sample surface, the incident direction of electronics with treat
The angle of laboratory sample normal direction is within 45° angle；
The irradiation evenness of proton and electronics is more than 10%；
The irradiated area of proton and electronics, and can be complete by sample more than or equal to treating 1.5 times of laboratory sample surface area
Cover.
The present invention is that setting up one kind can simulate Low Earth Orbit space flight based on ground single factor test and multifactor simulated environment
The device ground simulation experiment method of exposed material spatial synthesis environmental effect.The application different type ground single factor test of the present invention
And multifactor environment, step is simple, it is easy to operate.Technological approaches proposed by the invention can be greatly lowered the expense of test
With being significant to Low Earth Orbit spacecraft exposed material space environment effect ground simulation test and research.
Space environment effect is studied with radiation hardened technology application, is had obvious advantage and is widely applied prospect.
Description of the drawings
Schematic diagram when Fig. 1 is the dust shock optical glass that speed is 9km/s, size is 10um；
Fig. 2 is the range curve chart of electronics and proton in Teflon (politef) material, and A represents electronics, and B is represented
Proton；
Fig. 3 is the result of the test curve chart of 5MeV protons, 1MeV electronics and thermal cycle collective effect on Teflon material；
Fig. 4 is the result of the test curve chart of dust, elemental oxygen and 1MeV electronics collective effects on Teflon material.
Specific embodiment
Low Earth Orbit spacecraft exposed material mainly be subject to vacuum, thermal cycle, solar ultraviolet, dust, elemental oxygen and
The impact of the space environment factors such as charged particle irradiation.The present invention based on vacuum, thermal cycle, solar ultraviolet, dust, elemental oxygen,
Electron irradiation and proton irradiation are simultaneously or sequentially acted on, by selecting control vacuum, thermal cycling temperature range interval, the sun purple
Outer intensity, dust size and speed, atom oxygen energy and flux, electron energy and flux, proton energy and flux, and
Control simultaneously or sequentially comprehensive function to reach Low Earth Orbit spacecraft exposed material spatial synthesis environmental effect ground face mould
The purpose of plan.
Specifically, in order to reach above-mentioned technical purpose, this specific embodiment is using method in detail below：
Low Earth Orbit spacecraft described in present embodiment is tried with the ground simulation of exposed material spatial synthesis environmental effect
Proved recipe method, the method is comprised the following steps：
Step S1：Temperature control equipment is placed on into sealing intracavity, temperature control equipment lead utilizes the vacuum of annular seal space
Plug is attached；Adjust temperature range is to required scope：- 180 DEG C～+150 DEG C；
Step S2：The thickness t of sample to be tested is accurately tested, and tests its initial performance parameter, then carry out dust mould
Intend test, dust be sized to 0.01 μm～500 μm, speed be 1km/s～100km/s；
Step S3：Carry out atomic oxygen environment and ultraviolet environments test.Atom oxygen energy is 3eV～9eV, atom flux is
1e10atoms/cm2s～1e19atoms/cm2s；Ultraviolet wavelength 0nm～400nm, intensity is 0.1suns～10suns；
Step S4：After completing the test, sample is fixed on into temperature control sample bench.According to thickness of sample t, based on Geant4
With the emulation of SRIM computed in software, selecting the selection of the energy of incident electron and proton, particle energy makes its incident depth be more than 2t；
Step S5：The incident direction of proton should be perpendicular to sample surfaces, the incident direction of electronics and the angle of sample normal direction
Should be within 45° angle.Also, the irradiation nonuniformity of proton and electronics should be less than 10%；The irradiated area of proton and electronics should
At least 1.5 times of sample area, and sample can be covered all；
Step S6：Seal cavity is carried out into evacuation, pressure size is 10-1Pa～10-5Pa, starts thermal cycling test.Heat
Circulation sample heats up and rate of temperature fall is：0.01～50 DEG C/min；Temperature retention time should ensure that the temperature phase of sample surfaces and inside
Together；
Step S7：After completing the thermal cycle of different number of times, can original position carry out irradiation test；Or carrying out thermal cycling test
While, carry out charged particle irradiation test；
Step S8：During charged particle irradiation test, can be based on electronics and proton while irradiation carries out spatial synthesis radiation ring
Border experimental study, or combined radiation environment experimental study is carried out by electronics and the test of proton sequential irradiation.When irradiation particle
Total fluence (or accumulated dose) when reaching the requirement of test, carry out the exposure of the Low Earth Orbit spacecraft after combined environment test
Material properties test.
In order to realize spatial synthesis environment and Low Earth Orbit spacecraft exposed material Rationale in science
And technique study, disclose under spatial synthesis environment the Low Earth Orbit spacecraft basic law of exposed material performance degradation with it is each
The physical essence of spatial environmentss comprehensive effect is planted, Low Earth Orbit spacecraft exposed material ground under spatial synthesis environment is set up
The method of simulation test.
Comprehensive environmental effects ground simulation experiment method involved by present embodiment, can be in Low Earth Orbit spacecraft
With in exposed material produce spatial synthesis environmental effect test method, its application include all kinds of Low Earth Orbit spacecrafts
Use exposed material.Present embodiment is based on selection control vacuum, thermal cycling temperature range interval, solar ultraviolet intensity, dust
Size and speed, atom oxygen energy and flux, electron energy and flux, proton energy and flux, and control each environment
The order of action of factor, can produce identical damage effect to Low Earth Orbit spacecraft exposed material, reach low land ball rail
The exposed material spatial synthesis environmental effect ground simulation of road spacecraft.
For the energy of the synthesis of above-mentioned environment, dust size and speed, electronics and proton selects particularly critical.Cause
If for space dust enable to material surface occur damage or rupture, the effect of other space environment factors can be produced to
Close important impact.Furthermore, it is desirable to electronics and proton can completely penetrate through Low Earth Orbit spacecraft exposed material sample.This
Outward, need to ensure electronics and proton irradiation, damaged with generation in exposed material sample is uniform in Low Earth Orbit spacecraft.For
This, needs to select suitable electronics and proton energy so as to which it is thick that range exceedes Low Earth Orbit spacecraft exposed material sample
More than 2 times of degree.Schematic diagram when speed is 9km/s, size clashes into optical glass for the dust of 10um, as shown in Figure 1.Electronics
And curve of the proton in Teflon material is as shown in Figure 2.
In order to further illustrate the well-formedness of aforesaid way, by sample select be Teflon material, its thickness be 100 μm,
Area is 1cm × 3cm.Experimental condition is that vacuum is 10-3Pa under vacuum condition.Fig. 3 gives 5MeV protons, 1MeV electronics
And the coefficient result of the test of thermal cycle.Thermal cycle conditions are in Fig. 3：Temperature range is -100 DEG C～+50 DEG C, cycle-index
For 200 times, 5 DEG C/min of temperature rate.Radiation parameter is：1MeV electron irradiation flux 1e10e/cm2s, irradiated area 20cm
× 50cm, irradiation nonuniformity are less than 5%；5MeV proton irradiation flux 1e8p/cm2s, irradiated area 2cm × 20cm, irradiation are not
The uniformity is less than 5%.Electronics and proton take sequential irradiation mode, and with thermal cycle using order and while model of action.By
No matter Fig. 3 can be seen that sequential action or act on simultaneously, the degree of injury caused to polymeric material is identical.
Fig. 4 gives dust, elemental oxygen and the coefficient result of the test of 1MeV electronics.In figure, the condition of 1MeV electronics
It is identical with Fig. 3；Dust material is Al balls, and its a diameter of 30 μm, speed is 8km/s；Atom oxygen energy is 5eV, and fluence is
1e15atoms/cm2s.Dust, elemental oxygen and 1MeV electronics take the mode of sequential action.As seen from the figure, dust and elemental oxygen
After effect, then when carrying out electron irradiation, the damage caused by electron irradiation can be aggravated.Aggravation, and proton can be caused to take order
Radiation mode, and with thermal cycle using order and while model of action.Also, with first atomic oxygen environment test dust atmosphere examination again
Test and compare, first dust atmosphere test is carried out again after atomic oxygen environment test, carries out caused degree of injury during electron irradiation bigger.
Claims (8)
1. Low Earth Orbit spacecraft exposed material spatial synthesis environmental effect ground simulation experiment method, it is characterised in that
The method is comprised the following steps：
Step one：To treat that laboratory sample is put in seal cavity, treating laboratory sample carries out dust simulation test, then execution step
Two；
Step 2：Treating laboratory sample carries out atomic oxygen environment and ultraviolet environments test, then execution step three；
Step 3：To seal cavity evacuation, thermal cycling test is carried out, then execution step four；
Step 4：According to the thickness t of sample to be tested, the energy of incident electron and proton is selected so that electronics and proton enter
Depth is penetrated more than 2t, treating laboratory sample carries out charged particle irradiation test, when total fluence or accumulated dose of irradiation particle reach
During the requirement of test, Low Earth Orbit spacecraft exposed material performance test is carried out, complete Low Earth Orbit spacecraft with cruelly
Dew material space comprehensive environmental effects ground simulation test.
2. Low Earth Orbit spacecraft exposed material spatial synthesis environmental effect ground simulation experiment method, it is characterised in that
The method is comprised the following steps：
Step one：To treat that laboratory sample is put in seal cavity, treating laboratory sample carries out dust simulation test, then execution step
Two；
Step 2：Treating laboratory sample carries out atomic oxygen environment and ultraviolet environments test, then execution step three；
Step 3：To seal cavity evacuation, then execution step four；
Step 4：According to the thickness t of sample to be tested, the energy of incident electron and proton is selected so that electronics and proton enter
Depth is penetrated more than 2t；Laboratory sample is treated while carrying out thermal cycling test and charged particle irradiation test, it is total when irradiation particle
When fluence or accumulated dose reach the requirement of test, Low Earth Orbit spacecraft exposed material performance test is carried out, complete low land
Ball Orbital Space Vehicle exposed material spatial synthesis environmental effect ground simulation test.
3. Low Earth Orbit spacecraft according to claim 1 and 2 with exposed material spatial synthesis environmental effect ground face mould
Intend test method, it is characterised in that temperature control equipment is provided with seal cavity, the lead of temperature control equipment passes through annular seal space
Vacuum plug connection power supply, the range of accommodation of temperature control equipment is -180 DEG C～150 DEG C.
4. Low Earth Orbit spacecraft according to claim 1 and 2 with exposed material spatial synthesis environmental effect ground face mould
Intend test method, it is characterised in that in dust simulation test, dust size is 0.01 μm～500 μm, dust speed is 1km/s
～100km/s.
5. Low Earth Orbit spacecraft according to claim 1 and 2 with exposed material spatial synthesis environmental effect ground face mould
Intend test method, it is characterised in that in atomic oxygen environment test, atom oxygen energy is 3eV～9eV, and atom flux is
1e10atoms/cm2s～1e19atoms/cm2s；
In ultraviolet environments test, ultraviolet wavelength 0nm～400nm, intensity is 0.1suns～10suns.
6. Low Earth Orbit spacecraft according to claim 1 and 2 with exposed material spatial synthesis environmental effect ground face mould
Intend test method, it is characterised in that in step 3, seal cavity evacuation makes the pressure in seal cavity be 10-1Pa～10- 5Pa。
7. Low Earth Orbit spacecraft according to claim 1 and 2 with exposed material spatial synthesis environmental effect ground face mould
Intend test method, it is characterised in that in thermal cycling test, heat up and rate of temperature fall is 0.01 DEG C/min～50 DEG C/min, and protect
The warm time enables to treat that laboratory sample surface is identical with the temperature inside laboratory sample is treated.
8. Low Earth Orbit spacecraft according to claim 1 and 2 with exposed material spatial synthesis environmental effect ground face mould
Intend test method, it is characterised in that in charged particle irradiation test, the incident direction of proton perpendicular to treating laboratory sample surface,
The incident direction of electronics with treat the angle of laboratory sample normal direction within 45° angle；
The irradiated area of proton and electronics can be completely covered in sample more than or equal to treating 1.5 times of laboratory sample surface area
Firmly.
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| 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 |
| CN113933233A (en) * | 2021-09-29 | 2022-01-14 | 中国电子产品可靠性与环境试验研究所（（工业和信息化部电子第五研究所）（中国赛宝实验室）） | Method and system for testing solar radiation of aerial equipment |
| CN113933233B (en) * | 2021-09-29 | 2024-01-05 | 中国电子产品可靠性与环境试验研究所（（工业和信息化部电子第五研究所）（中国赛宝实验室）） | Method and system for testing solar radiation of aerial equipment |
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