CN106342211B - Spacecraft Material long-term vacuum-ultraviolet irradiation simulation test device and test method thereof - Google Patents
Spacecraft Material long-term vacuum-ultraviolet irradiation simulation test device and test method thereofInfo
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- CN106342211B CN106342211B CN201110015129.6A CN201110015129A CN106342211B CN 106342211 B CN106342211 B CN 106342211B CN 201110015129 A CN201110015129 A CN 201110015129A CN 106342211 B CN106342211 B CN 106342211B
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Abstract
The present invention relates to the long-term vacuum-ultraviolet irradiation of a kind of Spacecraft Material simulation test device, this device is made up of analog light source unit (1), vacuum control unit (2), in site measurement unit (3) and industrial computer automatic control unit (4), and analog light source unit (1) carries out solar simulation illumination to the sample in vacuum control unit (2); In site measurement unit (3) provides each wave band light source to vacuum control unit (2), and catches collected specimens signal by ultraviolet/Vis/NIR Spectroscopy optical fiber spectrograph fiber spectrometer (31) or infrared optical fiber spectrometer (32); Analog light source unit (1) is separate with in site measurement unit (3); Industrial computer automatic control unit (4) carries out automation mechanized operation to analog light source unit (1), vacuum control unit (2) and in site measurement unit (3) respectively by signal of communication. The invention still further relates to and use afore-mentioned test device to carry out the test method of long-term vacuum-ultraviolet irradiation simulated test.
Description
Technical field
The invention belongs to spacecraft heat control material performance measurement and examination technical field, be specifically related to a kind of space flightDevice material vacuum-ultraviolet irradiation simulation test device; In addition, the invention still further relates to a kind of space flight equipmentExpect long-term vacuum-ultraviolet irradiation simulation experiment method.
Background technology
Spacecraft heat control material is the important component part of spacecraft thermal control units, and they directly expose conventionallyIn spacecraft surface, to bear the irradiation of the various adverse circumstances in space and degrade, its thermal control performance is in space environmentIrradiation stability directly have influence on service life and the reliability of spacecraft. Therefore, any thermal control materialMaterial, all must be through a series of space environment simulation test of ground before for Spacecraft Launch. DomesticOuter spacecraft development departments has all been made relevant regulations to the anti-Space Particle irradiation behaviour of thermal control coating, to itTesting arrangement has proposed strict demand.
For the irradiation test that carries out ultraviolet rays, need meeting spatial condition of high vacuum degree, simulated environment needs to protectHold long-term by 1.3 × 10-3High vacuum more than Pa; For simulation ray, require ultraviolet rays spectrum to meet space tooThe feature of sunlight spectrum; For irradiation intensity, should meet the material behavior requirement of simulated acceleration test; Irradiation agentAmount should meet the material examination dosage that spacecraft thermal design department requires. Heat control material expert is by right both at home and abroadThe interpretation of result of simulated test, flight test, the solar absorptance that draws thermal control coating is to weigh thermal control coatingThe main parameter of performance degradation in space environment irradiation scientific experimentation both at home and abroad, is also by examination at presentThis index is evaluated the degraded performance of thermal control coating. But the optics producing through irradiation due to most of materials declinesMove back effect, have memory phenomenon having contacted after the oxygen in atmosphere, therefore require to use in site measurementTechnology.
Normally albedometry of the method for testing of solar absorptance, first measures surface to solar radiationReflectivity ρ s, for this class opaque material of thermal control coating, solar absorptance α s:
αs＝1-ρs。 (1)
Therefore, α s in the time utilizing spectral reflectivity measurement device, first measures surface to different wave length radiationSpectral reflectivity, then calculate solar reflectivity ρ s
S in formulaλ-be incident upon lip-deep solar spectrum radiant illumination Wm-2·μm-1；
λ-wavelength μ m.
At present, in the research and research institute of China's spacecraft heat control material, the sun of ultraviolet irradiation sample is inhaledReceive and mainly contain following two kinds than measuring technology, one is that this invention unit was once sent out in country's the enforcement period of the ninth five-year planOpen up a kind of " ' original position ' method of testing of Thermal Control Coating Material " (Chinese patent CN1180838A). The partyMethod is that simple sample is sealed in the quartz ampoule vacuumizing and carries out ultraviolet irradiation test again, has solved heat at that timeThis key issue of control coating layer VUV degradation, but that this method can not ensure test tube is true for a long timeReciprocal of duty cycle, and be contained in sample in quartz window and can not carry out vacuum far ultraviolet (wavelength is less than 200nm'sRay) irradiation test, can not meet the long-life new demand of China's thermal control coating.
Another kind is other unit that carries out environmental test, adopts the comprehensive irradiation from external integral inlet in one's early yearsEquipment, is mainly used in combined environment test, and in the time carrying out ultraviolet irradiation simulated test, effective area of irradiationLittle, measure spectrum scope is narrower, and test spectral scope is 350～1100nm, by this section of spectrum at solar spectrumThe shared ratio value of solar absorptance that converts, cannot know that material is in the full wave degeneration of the sun in scopeSituation. Meanwhile, for the space UV irradiation dose of 3～5 years, due to the restriction of speed-up ratio, combine in useWhile closing irradiation apparatus, the time that ground need to be carried out will be 3～5 months, sometimes reach 6～8 months even longer.Because life cycle is long, testing equipment reason, this simulated test cannot realize conventionally completely. Therefore,In the urgent need to a kind of device that is suitable for specially long-term vacuum-ultraviolet irradiation simulated test.
Summary of the invention
For the defect of Chinese patent CN1180838A and aforementioned comprehensive irradiation apparatus existence, the present invention wantsThe technical problem solving is to propose the long-term vacuum-ultraviolet irradiation of a kind of Spacecraft Material simulation test device, andPropose the long-term vacuum-ultraviolet irradiation of a kind of Spacecraft Material simulation experiment method, try with meeting spatial environmental simulationThe requirement of testing.
In order to solve technical problem of the present invention, the long-term vacuum-ultraviolet of Spacecraft Material provided by the invention spokeAutomatic by analog light source unit, vacuum control unit and in site measurement unit, industrial computer according to simulation test deviceControl module composition, analog light source unit carries out solar simulation illumination to the sample in vacuum control unit; FormerPosition measuring unit provides each wave band light source to vacuum control unit, and by the fine spectrum of ultraviolet/Vis/NIR SpectroscopyInstrument fiber spectrometer or infrared optical fiber spectrometer catch collected specimens signal; Analog light source unit and in site measurementUnit is separate; Industrial computer automatic control unit by signal of communication respectively to analog light source unit, vacuumControl module and in site measurement unit carry out automation mechanized operation.
In the present invention, analog light source unit is by separate near ultraviolet sun simulating light source and extreme ultraviolet light sourceComposition, near ultraviolet sun simulating light source is amassed by near ultraviolet solar simulator reflective mirror, power-supply controller of electric, opticsPoint device and mercury xenon lamp composition, power-supply controller of electric excites lamp to light by being added in voltage on mercury xenon lamp, mercury xenonLamp sends near ultraviolet sun simulating light source, forms by near ultraviolet solar simulator reflective mirror and light integratorOptical system after, be introduced into irradiation vacuum chamber sample carried out to ultraviolet irradiation.
In the present invention, vacuum control unit by irradiation vacuum chamber, measure vacuum chamber and the unit of bleeding forms, take outThe vacuum environment into composite demand taken out by irradiation vacuum chamber and measurement vacuum chamber by gas unit, measures vacuum chamber and pass throughVacuum valve is connected with irradiation vacuum chamber, and irradiation vacuum chamber is made up of sample stage and irradiation vacuum chamber cavity,Sample stage is placed in irradiation vacuum chamber inside cavity; Measure vacuum chamber by sample stage, measurement vacuum chamber cavity, machineTool hand and vacuum valve composition; Sample stage is placed in measures vacuum chamber inside cavity, and manipulator is contained in measurement vacuumChamber body left side, vacuum valve is contained in is measuring vacuum chamber cavity right side; Bleed unit by two cryogenic pumps andA dry pump composition.
In the present invention, in site measurement unit by ultraviolet/Vis/NIR Spectroscopy optical fiber spectrograph, infrared optical fiber spectrometer,Composite light source, fibre-optical probe and integrating sphere composition, composite light source provides respectively near ultraviolet/visible/closely red for testThe light source of outer wave band; After the illumination that light source sends is mapped on sample, after integrating sphere multiple attenuation, obtainThe sample signal of homogenization is also adopted by ultraviolet/Vis/NIR Spectroscopy optical fiber spectrograph or the seizure of infrared optical fiber spectrometerCollection, can obtain sample reflectance spectrum, through calculating the numerical value of solar absorptance.
In the present invention, industrial computer automatic control unit is made up of visual interface and communication unit two parts, industry controlMachine automatic control unit is touch display screen operation.
In the present invention, the major function of analog light source unit is the simulation to ultraviolet rays source, offering sample spaceLight source. Wherein extreme ultraviolet light source produces far ultraviolet rays (115nm～200nm), by deuterium lamp and sample are setThe modes such as the distance that product are different and sample fixed point irradiation and moving spider shine, obtain different irradiation intensities, canReach 10～280mw/m2, realize 1～28 times of speed-up ratio. Near ultraviolet sun simulating light source (x) adopts 5000WHigh-pressure mercury xenon lamp virtual space near-ultraviolet spectrum (200nm～400nm), improves power supply by power-supply controller of electricThe adjusting of power and out of focus, can reach 620w/m at this wave band irradiation intensity2, and can be at 50w/m2～620w/m2Adjustable continuously in scope, irradiation profile unevenness≤± 5%, irradiation speed-up ratio maximum reaches 5.4.
In the present invention, the major function of vacuum control unit is that analog light source unit and in site measurement unit are taken outGas is to virtual space vacuum environment state. Radiation chamber unit and the measuring chamber unit of bleeding of bleeding is without oily unitConfiguration, to reduce generation sample contaminant. The long-term vacuum of irradiation vacuum chamber is better than 5.0 × 10-5Pa；The main pump of taking out adopts double copies configuration, and the various accident designs that may occur in irradiation test process are become to capable of dynamicMaintenance, Automatic Control, realize the simulated test of long-term vacuum-ultraviolet irradiation.
In the present invention, the major function of in site measurement unit is the in site measurement to sample solar absorptance. TooThe test of sun absorptance adopts get/sample presentation of two-dimentional machinery hand, can be not destroying under vacuum, to different Irradiation simulatingsThe sun reflectivity of experimental stage sample is carried out in-situ test, has good real-time, in-situ test function.Ultraviolet/Vis/NIR Spectroscopy optical fiber spectrograph and infrared optical fiber spectrometer composition measure spectrum instrument, is characterized in that surveyingThe response range of device covers 250～2500nm, meets the requirement of solar spectrum scope, adopts special internal diameter 8cmIntegrating sphere, meet the test request of full spectrum.
In the present invention, the function of industrial computer automatic control unit be realize to radiation source selection, strength control,Vacuum unit control, get/feeding mechanism, the automatic operating of sample in measurement operation.
The test method of the long-term vacuum-ultraviolet irradiation of Spacecraft Material provided by the invention simulated test, before useState the long-term vacuum-ultraviolet irradiation of Spacecraft Material simulation test device, test process is controlled automatically by industrial computerUnit is controlled automatically, specifically comprises the following steps:
(1) sample is put into irradiation vacuum chamber (21), accepted the irradiation of analog light source;
(2) irradiation vacuum chamber (21) is taken out as simulates real Altitude to irradiation vacuum chamber (21) long-term trueReciprocal of duty cycle is better than 5.0 × 10-5Pa, sample is accepted irradiation;
(3) will measure vacuum chamber (23) and take out as simulates real Altitude, measure the long-term true of vacuum chamber (23)Reciprocal of duty cycle is better than 3.0 × 10-4Pa；
(4) sample enters in site measurement chamber by manipulator, accepts solar absorptance in site measurement.
Final sample enters in site measurement chamber by manipulator, accepts solar absorptance in site measurement. Pass through machineGet successively/sample presentation of tool hand, does not destroy vacuum environment, can carry out the repeatedly circulation of different irradiation degree and measure.
With respect to prior art, embodiment subsequently and comparative example will prove, apparatus of the present invention have following spyPoint: the original position of vacuum system operation chronicity, analog light source intensity controllability, spectral measurement, can meetThe requirement of space environment simulation test. The common sampling test sample diameter 28mm of apparatus of the present invention, simultaneouslyCarry out sample size and reach 24. Because irradiated area is large, diameter can reach 310mm, also can carry out large areaThe irradiation test of material. After irradiation test completes, also can carry out the measurements such as electrical property, emissivity, Yi JicaiMaterial structural analysis. Apparatus of the present invention, can basis in irradiation process owing to adopting two vacuum structures simultaneouslyExperiment needs, regulation experiment scheme, and taking-up, removable parts test specimen, and keep original experiment to connectContinuous carrying out.
Brief description of the drawings
Fig. 1 is the structural representation (front view) of apparatus of the present invention.
Fig. 2 is the vertical profile structural representation of apparatus of the present invention.
Fig. 3 is that the spectral reflectance curve figure of three kinds of heat control material in site measurements (is respectively the song before ultraviolet irradiationLine and the curve after 5000ESH irradiation).
Fig. 3-1 is the spectral reflectance curve figure before and after a kind of high absorption thermal control coating irradiation test.
The spectral reflectance curve figure aluminizing before and after thermal control coating irradiation test for a kind of polyimides in Fig. 3-2.
Fig. 3-3 are the spectral reflectance curve figure before and after a kind of glass mould second surface mirror thermal control coating irradiation test.
Wherein:
1 is analog light source unit, and 11 is ultraviolet solar simulator reflective mirror; 12 is power-supply controller of electric; 13 areLight integrator; 14 is spotlight; 15 is extreme ultraviolet light source;
2 is vacuum chamber and control module; 21 is irradiation vacuum chamber; 22 is the radiation chamber unit of bleeding; 23 areMeasure vacuum chamber; 24 is the measuring chamber unit of bleeding; 25 is sample in measurement mechanism; 26 is automatic control unit;
3 is in site measurement unit, and 31 is ultraviolet/Vis/NIR Spectroscopy optical fiber spectrograph; 32 is infrared optical fiber spectrumInstrument; 33 is composite light source; 34 is fibre-optical probe.
Detailed description of the invention
As shown in Figure 1-2, the long-term vacuum-ultraviolet irradiation of Spacecraft Material that the preferred embodiment of the present invention providesSimulation test device, by analog light source unit 1, vacuum control unit 2 and in site measurement unit 3, industrial computer4 four groundwork unit compositions of automatic control unit, wherein:
Analog light source unit 1 carries out solar simulation illumination to the sample in vacuum control unit 2; In site measurementUnit 3 provides each wave band light source to vacuum control unit 2, and is caught and adopted by fiber spectrometer 31 or 32Collection sample signal; Analog light source unit 1 is separate with in site measurement unit 3; Industrial computer is controlled list automaticallyUnit 4 enters analog light source unit 1, vacuum control unit 2 and in site measurement unit 3 respectively by signal of communicationRow automation mechanized operation.
As shown in Figure 1-2, analog light source unit 1 is by separate near ultraviolet sun simulating light source 11 and far awayUltraviolet source 12 forms. Near ultraviolet sun simulating light source 11 is by near ultraviolet solar simulator reflective mirror 111, electricitySource controller 112, light integrator 113 and 114 4 major part compositions of mercury xenon lamp, wherein:
Power-supply controller of electric 112, by being added in the voltage on mercury xenon lamp 114, exciting lamp and lights, and mercury xenon lamp is sent outGo out near ultraviolet sun simulating light source, long-pending by the near ultraviolet solar simulator reflective mirror 111 and the optics that designAfter the optical system that point device 113 forms, be introduced into irradiation vacuum chamber 21 sample is carried out to ultraviolet irradiation. This realityExecuting routine mercury xenon lamp 114 is high-pressure mercury xenon lamps that peak power reaches 5000W, can launch 200nm～400nmBlack light spectrum. Extreme ultraviolet light source 12 is made up of two 150W high power deuterium lamps, with the distance of sampleAdjustable.
As shown in Figure 1-2, vacuum control unit 2 is by irradiation vacuum chamber 21, measurement vacuum chamber 23, the list of bleedingUnit's 22 3 major parts composition, bleed unit 22 by irradiation vacuum chamber 21 and measure vacuum chamber 23 take out intoSatisfactory vacuum environment, measures vacuum chamber 23 and is connected with irradiation vacuum chamber 21 by vacuum valve.
Irradiation vacuum chamber 21 is made up of sample stage and irradiation vacuum chamber cavity, and sample stage is placed in irradiation vacuum chamberBody inside. Measuring vacuum chamber 23 is made up of sample stage, measurement vacuum chamber cavity, manipulator and vacuum valve.Sample stage is placed in measures vacuum chamber inside cavity, and manipulator is contained in measures vacuum chamber cavity left side, vacuum valveBe contained in and measuring vacuum chamber cavity right side. Bleed unit 22 by two cryogenic pumps 221 and a dry pump 222Composition. In the present embodiment, cryogenic pump continuous operation for a long time, end vacuum is 10-7Pa, working vacuumBe 10-6Pa, two cryogenic pump alternations, the requirement of long-term high vacuum can meet experiment time.
As shown in Figure 1-2, in site measurement unit 3 is by ultraviolet/Vis/NIR Spectroscopy optical fiber spectrograph 31, infrared lightFour main portions of optical fiber spectrograph 32, composite light source 33, fibre-optical probe 34 and integrating sphere (not indicating in figure)Be grouped into, composite light source 33 is for testing the light source that near ultraviolet/visible/near infrared wave band is provided respectively; Light source is sent outAfter the illumination going out is mapped on sample, after integrating sphere multiple attenuation, obtain sample signal the quilt of homogenizationUltraviolet/Vis/NIR Spectroscopy optical fiber spectrograph 31 or infrared optical fiber spectrometer 32 catch and gather, and can obtain sampleReflectance spectrum, through calculating the numerical value of solar absorptance.
As shown in Figure 1-2, industrial computer automatic control unit 4 is made up of visual interface and communication unit two parts.Industrial computer automatic control unit 4 operates by touch display screen.
Long-term vacuum-the ultraviolet irradiation of the Spacecraft Material simulated test dress providing by aforementioned preferred embodiments belowPut and carry out the test of heat control material solar absorptance.
Comparative example 1:
Carry out sample irradiation test according to patent CN1180838A method.
Begin first testing equipment to be carried out to self-correcting, contrast print adopts spectrophotometer measurement, then puts into band windowIn the test glass tube of mouth. Prepare irradiation sample by Chinese patent CN1180838A method, measure initialAfter the signal of telecommunication, put into irradiation test cabinet, light high-pressure sodium lamp, reach after corresponding requirements irradiation dose, closeBlack out source, carries out electric signal measurement again by Chinese patent CN1180838A method, and carries out with contrast printRelatively, carry out measurement data correction and processing. Table 1 is the measurement result of three kinds of thermal control coating solar absorptances:
The measurement result of three kinds of thermal control coating solar absorptances of table 1
Embodiment 1:
Use experimental rig of the present invention to carry out the irradiation of three kinds of thermal control coatings (every kind of each 5 samples of sample)Test increases a kind of test specimen in irradiation process.
First carry out the self-correcting of experimental rig function, and complete after unit pollutant measurement, Irradiation simulating device light sourceIntensity calibration.
The vacuum of measuring chamber, radiation chamber is evacuated to 5.0 × 10-4More than Pa, measure the reverberation of testing sampleSpectral curve, and calculate corresponding solar absorptance. Close the vacuum lock that connects two chambers, open ultraviolet tooSun simulator, is adjusted to three space ultraviolet sun intensity (3UVSC) and starts timing, carries out 80 continuously altogetherMy god. With normal cell sheet monitoring irradiation intensity, regulate by simulator control system if any deviation every day during this timeTo prescribed strength. In the time that light source decay can not meet requirement of strength, change high-pressure mercury xenon lamp. Work as irradiation doseReach 200,700,1200,1700,2500,3500, when 5000ESH, first (measure with reference to sampleWhite reference) be placed on reference sample manipulator, then open associated pump system, the vacuum of measuring chamber is taken outTo 5.0 × 10-4More than Pa, open test light spectrometer, according to the operating sequence of spectrometer, sample top mechanism,Be placed on integrating sphere with reference to standard sample and measure mouth, the reflectance spectrum curve of witness mark standard sample, as surveyThe baseline of examination. Then open vacuum lock, use manipulator that irradiation sample is taken out and delivers to measuring chamber from radiation chamber,By sample overhead integrating sphere mouth, use fiber spectrometer to carry out the measurement of sample spectra reflectivity by top flat mechanism,Measurement finishes rear sample and sends original position back to, and each sample carries out the surveying work of repetition.
In the present embodiment, in the time that irradiation carries out 1200ESH, (name is called one directly will newly to add samplePolyimides plating germanium thermal control coating) put on sample disc room, for as added replacing sample, first will needReplacing sample takes out. Concrete operations: first confirm that the vacuum lock in the middle of radiation chamber and measuring chamber is closed condition,Then measuring chamber is recovered to atmosphere, in transfer robots, put sample, close the sample gate of measuring chamber, openOpen pump machanism, be evacuated to 5.0 × 10-4More than Pa, measure and newly add the sample curve of spectrum, then open vacuum lock,Sample is sent to radiation chamber by manipulator, is put into sample position, returns manipulator to measuring chamber, closes vacuumLock, recovers measuring chamber vacuum to atmospheric condition, opens measuring chamber door, puts into another sample, repeatsState setting-out step. Changing sample can be not related to and close simulator.
Finally, after irradiated sample reaches required 5000ESH, close simulator, complete above-mentioned all samplesThe measurement of product, according to the formula in background technology (1), formula (2), calculates the solar absorptance of each sample.Table 2 is the measurement result of four kinds of thermal control coating solar absorptances. The irradiation dose that newly adds sample has been counted again.Fig. 3 is the full spectral reflectance curves of three kinds of samples after predose. Use experimental rig of the present invention, noThe data that only can obtain material solar absorptance, can also obtain the curve of spectrum, by the analysis to curve,Can learn every kind of sample, after ultraviolet irradiation test, at which wave band is degenerated serious, thereby analyze degeneration machineSystem, provides valuable help to the improvement of material development.
The measurement result of several thermal control coating solar absorptances of table 2.
Claims (15)
1. the long-term vacuum-ultraviolet irradiation of a Spacecraft Material simulation test device, is characterized in that, by mouldIntend light source cell (1), vacuum control unit (2), in site measurement unit (3) and industrial computer and automatically control listUnit (4) composition, analog light source unit (1) carries out solar simulation to the sample in vacuum control unit (2)Illumination; In site measurement unit (3) give vacuum control unit (2) each wave band light source is provided, and by ultraviolet/Vis/NIR Spectroscopy optical fiber spectrograph (31) or infrared optical fiber spectrometer (32) catch collected specimens signal; SimulationLight source cell (1) is separate with in site measurement unit (3); Industrial computer automatic control unit (4) is by communicationSignal carries out certainly analog light source unit (1), vacuum control unit (2) and in site measurement unit (3) respectivelyMovingization operation.
2. the long-term vacuum-ultraviolet irradiation of Spacecraft Material according to claim 1 simulation test device,It is characterized in that, analog light source unit (1) is by separate near ultraviolet sun simulating light source (11) and far awayUltraviolet source (12) composition.
3. the long-term vacuum-ultraviolet irradiation of Spacecraft Material according to claim 2 simulation test device,It is characterized in that, described near ultraviolet sun simulating light source (11) by near ultraviolet solar simulator reflective mirror (111),Power-supply controller of electric (112), light integrator (113) and mercury xenon lamp (114) composition, power-supply controller of electric (112)Lamp is excited light by being added in voltage on mercury xenon lamp (114), mercury xenon lamp (114) sends near ultraviolet tooThe light that sun analog light source forms by near ultraviolet solar simulator reflective mirror (111) and light integrator (113)After system, be introduced into irradiation vacuum chamber (21) sample is carried out to ultraviolet irradiation.
4. the long-term vacuum-ultraviolet irradiation of Spacecraft Material according to claim 3 simulation test device,It is characterized in that, the peak power of described mercury xenon lamp (114) is 5000W, can launch 200nm～400nmBlack light spectrum.
5. the long-term vacuum-ultraviolet irradiation of Spacecraft Material according to claim 2 simulation test device,It is characterized in that, described extreme ultraviolet light source (12) is made up of two 150W high power deuterium lamps, with sampleDistance adjustable.
6. the long-term vacuum-ultraviolet irradiation of Spacecraft Material according to claim 1 simulation test device,It is characterized in that, described vacuum control unit (2) is by irradiation vacuum chamber (21), measurement vacuum chamber (23)With the unit of bleeding (22) composition, wherein: the unit of bleeding (22) are by irradiation vacuum chamber (21) and measure trueTake out as satisfactory vacuum environment empty chamber (23), measures vacuum chamber (23) by vacuum valve and irradiationVacuum chamber (21) is connected.
7. the long-term vacuum-ultraviolet irradiation of Spacecraft Material according to claim 6 simulation test device,It is characterized in that, described irradiation vacuum chamber (21) is made up of sample stage and irradiation vacuum chamber cavity, samplePlatform is placed in irradiation vacuum chamber inside cavity.
8. the long-term vacuum-ultraviolet irradiation of Spacecraft Material according to claim 6 simulation test device,It is characterized in that, described measurement vacuum chamber (23) by sample stage, measure vacuum chamber cavity, manipulator andVacuum valve composition, sample stage is placed in measures vacuum chamber inside cavity, and manipulator is contained in measures vacuum chamber cavityLeft side, vacuum valve is contained in measures vacuum chamber cavity right side.
9. the long-term vacuum-ultraviolet irradiation of Spacecraft Material according to claim 6 simulation test device,It is characterized in that, the described unit of bleeding (22) is by two cryogenic pumps (221) and a dry pump (222)Composition.
10. the long-term vacuum-ultraviolet irradiation of Spacecraft Material according to claim 9 simulation test device,It is characterized in that, the end vacuum of described cryogenic pump is 10-7Pa, working vacuum is 10-6Pa, two lowTemperature pump replaces long-term continuous operation.
The long-term vacuum one ultraviolet irradiation simulated test of 11. Spacecraft Material according to claim 1Device, is characterized in that, described in site measurement unit (3) is by the fine spectrum of ultraviolet/Vis/NIR SpectroscopyInstrument (31), infrared optical fiber spectrometer (32), composite light source (33), fibre-optical probe (34) and integrating sphere composition,Wherein:
Composite light source (33) is for testing the light source that near ultraviolet/visible/near infrared wave band is provided respectively, and light source sendsIllumination be mapped on sample after, after integrating sphere multiple attenuation, obtain the sample signal of homogenization and by purpleOutward/Vis/NIR Spectroscopy optical fiber spectrograph (31) or infrared optical fiber spectrometer (32) catch and gather, and can obtainSample reflectance spectrum, through calculating the numerical value of solar absorptance.
Long-term vacuum-the ultraviolet irradiation of 12. Spacecraft Material according to claim 1 simulation test device,It is characterized in that, described industrial computer automatic control unit (4) is by visual interface and communication unit two parts groupBecome.
13. a kind of material vacuum-ultraviolet irradiation simulation test devices according to claim 1,It is characterized in that, described industrial computer automatic control unit (4) operates by touch display screen.
The 14. 1 kinds of long-term vacuum-ultraviolet irradiation of Spacecraft Material simulation experiment methods, is characterized in that the right to useProfit requires the long-term vacuum-ultraviolet irradiation of the Spacecraft Material described in any one simulated test in 1 to 13Device, test process is controlled automatically by industrial computer automatic control unit (4), comprises the following steps:
(1) sample is put into irradiation vacuum chamber (21), accepted the irradiation of analog light source;
(2) irradiation vacuum chamber (21) is taken out as simulates real Altitude to irradiation vacuum chamber (21) long-term trueReciprocal of duty cycle is better than 5.0 × 10-5Pa, sample is accepted irradiation;
(3) will measure vacuum chamber (23) and take out as simulates real Altitude, measure the long-term true of vacuum chamber (23)Reciprocal of duty cycle is better than 3.0 × 10-4Pa；
(4) sample enters in site measurement chamber by manipulator, accepts solar absorptance in site measurement.
Long-term vacuum-the ultraviolet irradiation of 15. Spacecraft Material according to claim 14 simulation experiment method,It is characterized in that, in step (4), described in site measurement, by get successively/sample presentation of manipulator, does not destroyVacuum environment, carries out the repeatedly circulation of different irradiation degree and measures.
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