CN101876613B - Method for monitoring sensitive low-temperature surface pollution of spacecrafts - Google Patents
Method for monitoring sensitive low-temperature surface pollution of spacecrafts Download PDFInfo
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- CN101876613B CN101876613B CN2009102593496A CN200910259349A CN101876613B CN 101876613 B CN101876613 B CN 101876613B CN 2009102593496 A CN2009102593496 A CN 2009102593496A CN 200910259349 A CN200910259349 A CN 200910259349A CN 101876613 B CN101876613 B CN 101876613B
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Abstract
The invention relates to a method for monitoring sensitive low-temperature surface pollution of spacecrafts, in particular to a method for monitoring sensitive low-temperature surface pollution of spacecrafts by utilizing a quartz crystal microbalance, belonging to the technical field of aerospace. The method is directly applied to monitoring surface pollution of infrared low-temperature remote sensors and other low-temperature space probes. The method is characterized by utilizing a liquid nitrogen refrigeration system and quartz wafers to simulate the sensitive low-temperature surfaces of the spacecrafts; lowering the surface temperature of the quartz crystal by the liquid nitrogen refrigeration system to ensure the quartz crystal to work under the worst temperature on the spacecraft orbit; heating non-metal materials or ensuring an engine to ignite to ensure the non-metal materials or the engine to effuse or jet pollutants; carrying out online in-situ monitoring on the frequency and temperature of the quartz crystal microbalance and storing the frequency and temperature; and closing a test system. The method is high in sensitivity (1.10*10<-9>-4.42*10<-9>), stable and reliable in test process, good in repeatability and suitable for large-scale test.
Description
Technical field
The present invention relates to a kind of monitoring method of sensitive low-temperature surface pollution of spacecrafts; Particularly adopt the method for quartz crystal microbalance monitoring spacecraft low-temperature sensitive surface contamination; Belong to field of aerospace technology, directly be applied in infrared low temperature remote sensing and other space flight low temperature detector surface monitorings.
Background technology
There is many sensing units (like optical lens, view window, solar cell lid, thermal control coating, relay contact, waveguide inwall etc.) surface to need pollution monitoring and control on the spacecraft.Although these sensing surfaces are at the assembling of part manufacturing, subsystem, the existing certain pollution control measures of total process of assembling, but still might spacecraft ground thermal vacuum test and spacecraft in orbit process suffer pollution in various degree.Lubricated and the thermally conductive grease that the most significant example is lubricated or heat conduction is used can be overflowed the surface and arrive sensing surface with molecular forms.
Refuse, waste liquid that the pinniform column of smoke, fuel cell ejecta and the spacecraft work chamber of the ejection of attitude engine are discharged can form tangible particle pollution; The nonmetallic materials of spacecraft itself can be given vent to anger under the heating state in a vacuum, and they evaporate, distil, decompose effusion with monomolecular form, then are deposited on the low temperature exposed surface with at random mode, form molecular contamination etc.The consequence of polluting is very serious.For example: U.S.'s Gemini manned spaceship view window owing to do not add protective cover, receives serious plumage smoke pollution.
When No. 8 airships of Apollo carried out around-the-moon flight, because silicone rubber O-ring has polluted main view window, photograph and bat TV have to be transferred to temporarily and pollute less survey view window.No. 14 airship hermetic motor of Apollo switch lost efficacy during flying; Its reason is that room curing silicon rubber decomposites the low-molecular-weight gas-phase silicon when motor operation; Gas-phase silicon forms carbon granules with oil-based lubricant under the brush arcing effect, increased the brush resistance rate and caused motor failure.In general, the source of molecular contamination is that the oil that spacecraft powers on elastic insulated thing, the vacuum sealing material of heat, insulation system material, adhesive, hydraulic oil, thermal control coating oozes aqueous vapor and other compound, the cleaning solvent etc. that absorb in volatile matter, printing ink, the air.
In a word, if if the pollutant volatility is high, successive,, direction visible near, the visual field of sensing surface is low over against, the big sensing surface temperature of absorption probability, polluting then can be very serious, even can be accumulated to the degree of visible dirt dropping liquid.
Summary of the invention
The objective of the invention is for solve the spacecraft thermal vacuum test and in orbit during; The existing spacecraft of China uses nonmetallic materials to give vent to anger thing or plume jet sediment in the problem that low-temperature sensitive surface deposition amount can't characterize, and the nonmetal outgassing pollution thing on a kind of in-situ monitoring spacecraft low-temperature sensitive surface or the method for spacecraft plume contamination thing are provided.
The monitoring device of a kind of sensitive low-temperature surface pollution of spacecrafts of the present invention comprises: test rack, vacuum-pumping system, vacuum storehouse, thermal control sample stage, liquid nitrogen refrigerating system, quartz crystal microbalance detector, computing machine and calculating rack; Its annexation is: the vacuum bin device is installed on test unit cabinet, is connected with vacuum-pumping system through sealing pipeline; It is inner that vacuum-pumping system and liquid nitrogen refrigerating system are installed on test unit cabinet; Place quartz crystal microbalance detector and thermal control sample stage in the vacuum storehouse, its visual angle is 180 °; TT&C system with control thermal control sample stage temperature, is measured material outgassing pollution in the vacuum through cable and quartz crystal microbalance detector and thermal control sample stage; TT&C system work is accomplished through quartz crystal microbalance detector software and thermal control sample stage temperature Control Software.
The objective of the invention is to realize through following technical scheme.
The monitoring method of a kind of sensitive low-temperature surface pollution of spacecrafts of the present invention, its practical implementation step is following:
1) quartz crystal microbalance detector, liquid nitrogen refrigerating system and thermal control sample stage are installed, wherein the visual angle of quartz crystal microbalance detector and thermal control sample stage gas outlet is 180 °; Adopt the responsive low-temperature surface of wafer Simulated Spacecraft, the quartz crystal in the quartz crystal microbalance is placed in the vacuum storehouse, in the quartz crystal microbalance visual range, place nonmetallic materials or engine nozzle;
2) start vacuum system, make the vacuum storehouse be operated in the molecular flow duty;
3) through liquid nitrogen refrigerating system, reduce the quartz crystal surface temperature, it is operated under the severe temperatures condition of spacecraft orbit, and adjustment quartz crystal microbalance zero point;
4) heating nonmetal material or make engine ignition makes its effusion or sprays pollutant;
5) the various parameters of online in-situ monitoring quartz crystal microbalance mainly comprise frequency and temperature, preserve various parameters and various data recording;
6) close quartz crystal microbalance detector test macro, close liquid nitrogen refrigerating system, close vacuum system, reply testing equipment to testing original state.
The eigenfrequency of quartz crystal microbalance is 10MHz, 15MHz, 20MHz or higher frequency in the said step 1); Liquid nitrogen refrigerating system freezes the plane of crystal temperature to 80K; Vacuum storehouse air pressure is less than 1 * 10
-3Pa;
Said step 2) vacuum system is an oil-free vacuum system in, vacuum pump start by sequence cold-trap, mechanical pump and molecular pump; Start molecular pump initial vacuum degree less than 1 * 10
-1Pa, the air pressure of vacuum system is less than 1 * 10
-3Pa after 30 minutes, opens liquid nitrogen refrigerating system;
The liquid nitrogen refrigerating system rate of temperature fall is no more than 10K/min in the said step 3), when temperature drops to 80K, stablizes 30～60min;
The temperature of heating nonmetal material is 125 ℃ in the said step 4), and the time is 24～48h, and the engine constant ignition time is 30～60min;
Said step 5) medium frequency and temperature monitoring data rate are greater than 1 time/min;
Close quartz crystal microbalance detector test macro, liquid nitrogen refrigerating system and vacuum system in the said step 6) in order, finally make whole test system return to normal temperature, atmospheric pressure state.
Beneficial effect
(1) because volatile matter still can not can coagulate by in-situ monitoring spacecraft material outgassing in present China; This method provides the nonmetallic materials outgassing pollution thing on a kind of in-situ monitoring spacecraft low-temperature sensitive surface or the method for spacecraft plume contamination thing; This method is under the Simulated Spacecraft orbital environment; Improve China spacecraft material outgassing and can coagulate that volatile matter is selected and the sensitivity of engine spray pollutant monitoring, reached 1.10 * 10
-9～4.42 * 10
-9
(2) use of oil-free vacuum system in a kind of sensitive low-temperature surface pollution of spacecrafts monitoring method; For this method provides thin atmosphere and clean environment condition; Increase the accuracy of measurement data in the process of the test greatly, reduced the risk in the spacecraft materials used.
(3) use of liquid nitrogen refrigerating system in a kind of sensitive low-temperature surface pollution of spacecrafts monitoring method, better controlling the temperature of measuring equipment, process of the test is reliable and stable, repdocutbility is good.
(4) have the characteristic that adapts to the various material outgassing condensable material tests of spacecraft, and adaptation and large-scale industrialization test.
Description of drawings
Fig. 1 is the monitoring device synoptic diagram of a kind of sensitive low-temperature surface pollution of spacecrafts of the present invention;
Wherein, 1-test rack, 2-vacuum-pumping system, 3-vacuum storehouse, 4-thermal control sample stage, 5-liquid nitrogen refrigerating system, 6-quartz crystal microbalance detector, 7-computing machine and 8-calculate rack.
Embodiment
Like Fig. 1 is the monitoring device synoptic diagram of a kind of sensitive low-temperature surface pollution of spacecrafts of the present invention; Wherein, 1-test rack, 2-vacuum-pumping system, 3-vacuum storehouse, 4-thermal control sample stage, 5-liquid nitrogen refrigerating system, 6-quartz crystal microbalance detector, 7-computing machine and 8-calculate rack.
Embodiment
1) test specimen is the space grade silastic material that spacecraft often uses; It is prepared into the graininess of 1mm * 1mm * 1mm; The 100g thermal control sample stage 4 of packing into, adjustment quartz crystal microbalance detector 6 becomes 180 ° with the sample visual angle, the connection water, electricity, gas utility appliance of being correlated with; The communication of adjustment balance, and shut vacuum storehouse 3;
2) open vacuum extract system by starting cold-trap, starts mechanical pump, and the mode that starts molecular pump is carried out, until the system vacuum degree less than 1 * 10
-3Pa;
3) liquid nitrogen refrigerating system 5 is opened, monitoring quartz crystal microbalance temperature variation is 80K until the quartz crystal microbalance surface temperature;
4) by computing machine 7 control thermal control sample stage 4, the space grade silastic material is heated to 125 ℃ continues 24 hours, and record quartz crystal microbalance change of frequency, test back change of frequency 33233Hz;
5) close quartz crystal microbalance test macro 7, close liquid nitrogen refrigerating system 5, close vacuum system 2, make whole test system return to normal temperature, atmospheric pressure state.
Claims (7)
1. the monitoring method of a sensitive low-temperature surface pollution of spacecrafts is characterized in that:
1) quartz crystal microbalance detector, liquid nitrogen refrigerating system and thermal control sample stage are installed, wherein the visual angle of quartz crystal microbalance detector and thermal control sample stage gas outlet is 180 °; Adopt the responsive low-temperature surface of quartz crystal Simulated Spacecraft, the quartz crystal in the quartz crystal microbalance is placed in the vacuum storehouse, in the quartz crystal microbalance visual range, place nonmetallic materials or engine nozzle;
2) start vacuum system, make the vacuum storehouse be operated in the molecular flow duty;
3) through liquid nitrogen refrigerating system, reduce the quartz crystal surface temperature, it is operated under the severe temperatures condition of spacecraft orbit, and adjustment quartz crystal microbalance zero point;
4) heating nonmetal material or make engine ignition makes its effusion or sprays pollutant;
5) the various parameters of online in-situ monitoring quartz crystal microbalance mainly comprise frequency and temperature, preserve various parameters and various data recording;
6) close quartz crystal microbalance detector test macro, close liquid nitrogen refrigerating system, close vacuum system, reply testing equipment to testing original state.
2. the monitoring method of a kind of sensitive low-temperature surface pollution of spacecrafts according to claim 1, it is characterized in that: the eigenfrequency of quartz crystal microbalance is 10MHz, 15MHz, 20MHz or higher frequency in the step 1); Liquid nitrogen refrigerating system freezes the plane of crystal temperature to 80K; Vacuum storehouse air pressure is less than 1 * 10
-3Pa.
3. the monitoring method of a kind of sensitive low-temperature surface pollution of spacecrafts according to claim 1 is characterized in that: step 2) in vacuum system be oil-free vacuum system, vacuum pump start by sequence cold-trap, mechanical pump and molecular pump; Air pressure is less than 1 * 10 before starting molecular pump
-1Pa, the air pressure of vacuum system is less than 1 * 10
-3Pa after 30 minutes, opens liquid nitrogen refrigerating system.
4. the monitoring method of a kind of sensitive low-temperature surface pollution of spacecrafts according to claim 1, it is characterized in that: the liquid nitrogen refrigerating system rate of temperature fall is no more than 10K/min in the step 3), when temperature drops to 80K, stablizes 30～60min.
5. the monitoring method of a kind of sensitive low-temperature surface pollution of spacecrafts according to claim 1, it is characterized in that: the temperature of heating nonmetal material is 125 ℃ in the step 4), and the time is 24～48h, and the engine constant ignition time is 30～60min.
6. the monitoring method of a kind of sensitive low-temperature surface pollution of spacecrafts according to claim 1, it is characterized in that: step 5) medium frequency and temperature monitoring data rate are greater than 1 time/min.
7. the monitoring method of a kind of sensitive low-temperature surface pollution of spacecrafts according to claim 1 is characterized in that: close quartz crystal microbalance detector test macro, liquid nitrogen refrigerating system and vacuum system in the step 6) in order.
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| CN2009102593496A CN101876613B (en) | 2009-12-17 | 2009-12-17 | Method for monitoring sensitive low-temperature surface pollution of spacecrafts |
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| CN101876613B true CN101876613B (en) | 2012-02-08 |
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102507864B (en) * | 2011-10-20 | 2014-04-02 | 中国航天科技集团公司第五研究院第五一〇研究所 | Device and method for detecting material outgassing product under space living environment |
| CN102944493B (en) * | 2012-11-20 | 2015-01-07 | 中国航天科技集团公司第五研究院第五一〇研究所 | Device and method for detecting charged pollutants in vacuum |
| CN103612776B (en) * | 2013-11-27 | 2016-06-22 | 北京卫星环境工程研究所 | A kind of Spray-type nitrogen thermolator |
| CN106556618B (en) * | 2016-10-20 | 2019-06-28 | 中国空间技术研究院 | A kind of vacuum bakeout test method of spacecraft cable system |
| CN107703258B (en) * | 2017-09-05 | 2020-01-10 | 兰州空间技术物理研究所 | Method for determining average analytic chemical energy of adhesive outgassing pollutants in vacuum environment |
| CN107677563A (en) * | 2017-10-11 | 2018-02-09 | 北京航空航天大学 | Quartz crystal temperature probe, quartz crystal microbalance and its application method |
| CN111766240A (en) * | 2020-07-02 | 2020-10-13 | 北京卫星环境工程研究所 | In-situ real-time testing method and device for pollution influence of emissivity of material |
| CN117191959A (en) * | 2023-08-03 | 2023-12-08 | 哈尔滨工业大学 | Pollutant release and adsorption device and method in simulated space environment |
| CN117191924B (en) * | 2023-08-03 | 2024-04-05 | 哈尔滨工业大学 | Molecular pollutant in-situ analysis detection device with high-efficiency separation and dynamic characterization |
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