CN110824049A - Pollution monitoring system and method for spacecraft vacuum thermal test - Google Patents
Pollution monitoring system and method for spacecraft vacuum thermal test Download PDFInfo
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- CN110824049A CN110824049A CN201911113414.4A CN201911113414A CN110824049A CN 110824049 A CN110824049 A CN 110824049A CN 201911113414 A CN201911113414 A CN 201911113414A CN 110824049 A CN110824049 A CN 110824049A
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Abstract
The invention provides a pollution monitoring system for a spacecraft vacuum thermal test, which is characterized by comprising the following components: the device comprises a vacuum tank (1), a spacecraft (2), a pollution sampling probe (3), a chromatographic analysis module (7), a mass spectrometry module (8), a vacuum module (9) and a remote measurement and control unit (10); the spacecraft (2) and the pollution sampling probe (3) are arranged in the vacuum tank (1); the vacuum tank (1) is connected with a chromatographic analysis module (7); the chromatographic analysis module (7) is connected with the mass spectrometry module (8); the mass spectrometry module (8) is connected with the vacuum module (9); the vacuum module (9) is connected with the remote measurement and control unit (10). The pollution monitoring system can carry out multi-channel synchronous real-time dynamic monitoring on pollution in the vacuum thermal test process of the spacecraft, realizes real-time monitoring and component judgment on the outgassing products of the sensitive parts of the spacecraft, and has the advantages of good real-time performance, high precision, convenient operation and the like.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a pollution monitoring system and method for a spacecraft vacuum thermal test.
Background
Contamination is a serious problem in the operation of spacecraft, and the life of the spacecraft can be affected by contamination deposited on sensitive surfaces of the spacecraft, such as optical lenses, solar cell arrays, temperature control layers and the like. During ground space environment simulation, the pollution problem is more complex, and the pollution of condensable Volatile Compounds (VCM) caused by various materials and components of a vacuum exhaust system, a simulation chamber and a simulated object seriously influences the service life and the reliability of the spacecraft, so that the pollution detection and control requirements in the vacuum thermal test process of the spacecraft are very strict. A conventional method for monitoring plume contamination of an attitude control engine of a spacecraft, as disclosed in patent document CN101876615A, includes: the device comprises an inner vacuum bin observation window, a vacuum bin, a quartz crystal microbalance detector, an engine nozzle, a movable support, a quartz crystal microbalance detector, a computer, an ignition control cabinet, a vacuum air pumping system, an air supply bottle and a data acquisition system; a monitoring device for plume pollution of a spacecraft attitude control engine is characterized in that a set of quartz crystal microbalance detector is arranged on a sliding track of the existing space electric propulsion ground simulation test equipment, and two sets of quartz crystal microbalance detectors are arranged behind an engine nozzle on the surface of a vacuum chamber.
In the current stage of pollution monitoring in a spacecraft vacuum thermal test, a test method of Quartz Crystal Microbalance (QCM) and a pollution slide is mainly adopted. Although the total amount of pollution in a vacuum tank can be monitored in real time, the amount and distribution of pollutant emission of sensitive parts of a satellite cannot be accurately measured, and chemical components of pollutants of the sensitive parts of the satellite cannot be judged, so that reliable scientific data cannot be provided for judging pollution sources. Although the method for the contaminated slide glass can accurately determine the chemical components of the contaminants by analyzing the residues of the slide glass after the test is finished, the method cannot realize real-time monitoring in the test process and cannot accurately determine the source and the gas release amount of the contaminants, so that the problem analysis difficulty is high and the accuracy of the contamination tracing is low. Therefore, the existing monitoring means and monitoring method can not realize real-time qualitative and quantitative analysis of pollutants in the process of spacecraft vacuum thermal test.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a system and a method for monitoring pollution of a spacecraft vacuum thermal test.
The invention provides a pollution monitoring system for a spacecraft vacuum thermal test, which comprises: the system comprises a vacuum tank 1, a spacecraft 2, a pollution sampling probe 3, a chromatographic analysis module 7, a mass spectrometry module 8, a vacuum module 9 and a remote measurement and control unit 10;
the spacecraft 2 and the pollution sampling probe 3 are arranged in the vacuum tank 1;
the vacuum tank 1 is connected with a chromatographic analysis module 7;
the chromatographic analysis module 7 is connected with the mass spectrometry module 8;
the mass spectrometry module 8 is connected with the vacuum module 9;
the vacuum module 9 is connected with a remote measurement and control unit 10.
Preferably, a standard flange interface 5 is arranged on the vacuum tank 1.
Preferably, the chromatographic module 7 comprises: a carrier gas unit 71, a second electromagnetic cut-off valve 72, a transition chamber 73, a third electromagnetic cut-off valve 74, and a separation quantifying unit 75;
the carrier gas unit 71, the transition cavity 73 and the separation quantitative unit 75 are connected in sequence;
a second electromagnetic stop valve 72 is arranged between the carrier gas unit 71 and the transition cavity 73;
a third electromagnetic shut-off valve 74 is arranged between the transition chamber 73 and the separate dosing unit 75.
Preferably, the mass spectrometry module 8 comprises: a sample introduction system 81, an ion source 82, a mass analyzer 83, and a detector 84;
the sample introduction system 81, the ion source 82, the mass analyzer 83 and the detector 84 are connected in sequence.
Preferably, the vacuum module 9 comprises: a fourth electromagnetic cutoff valve 91, a high vacuum pump 92, and a backing pump 93;
the fourth electromagnetic cutoff valve 91, the high vacuum pump 92, and the backing pump 93 are connected in this order.
Preferably, a first electromagnetic stop valve 6 is arranged between the vacuum tank 1 and the chromatographic module 7.
Preferably, the contamination sampling probe 3 is plural.
Preferably, the sample injection system 81 comprises: metal capillary and polydimethylsiloxane film; the metal capillary is mounted with a polydimethylsiloxane membrane.
Preferably, the method further comprises the following steps: a gas transmission line 4;
the vacuum tank 1 is connected with the chromatographic analysis module 7 through a gas transmission pipeline 4;
the chromatographic analysis module 7 is connected with the mass spectrometry module 8 through a gas transmission pipeline 4;
the mass spectrometry module 8 is connected with the vacuum module 9 through the gas transmission pipeline 4.
The invention provides a pollution monitoring method for a spacecraft vacuum thermal test, which comprises the following steps:
step 1, pollution sampling: closing the first electromagnetic stop valve 6 and the second electromagnetic stop valve 72, and starting the vacuum pump to ensure that the transition cavity 73 is in a vacuum state and the vacuum degree is higher than that in the vacuum tank 1; closing the third electromagnetic stop valve 74, opening the first electromagnetic stop valve 6, and enabling the volatile matters in the sampled gas to enter the transition cavity 73 through the pollution sampling probe 3, wherein the balance time is about 5 to 10 minutes, so that the components in the tank and the transition cavity are kept consistent; after the balance state is finished, closing the first electromagnetic stop valve 6, the second electromagnetic stop valve 72 and the third electromagnetic stop valve 74 to finish pollution sampling;
step 3, mass spectrometry: after the chromatographic analysis is completed, the components flow out of the chromatographic column, are introduced into the ion source 82 through the sample introduction system 81, complete the ionization process in the ion source 82, become charged ions, enter the mass analyzer 83 through the processes of focusing, transmission, acceleration and the like of the ion transmission device, separate the ions with different mass-to-charge ratios in the mass analyzer through the mass analysis process, and are detected by the detector 84;
and 4, data acquisition and analysis process: weak current signals are collected through a detector 84, are subjected to signal amplification and A/D conversion through a measurement and control system conversion circuit, and are fed back to a computer through the measurement and control system for collection and analysis processing, so that required mass spectrogram information can be obtained; and finally, comparing the data base to realize qualitative analysis of the pollutants.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention monitors the pollution in the spacecraft vacuum thermal test tank based on a gas chromatography-mass spectrometry detection method, and can solve the problem that the pollution test in the conventional spacecraft vacuum thermal test is asynchronous in quantitative analysis and qualitative analysis and cannot be qualitatively analyzed in real time.
2. The pollution monitoring system can carry out multi-channel synchronous real-time dynamic monitoring on pollution in the vacuum thermal test process of the spacecraft, realizes real-time monitoring and component judgment on the outgassing products of the sensitive parts of the spacecraft, and has the advantages of good real-time performance, high precision, convenient operation and the like.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic structural diagram of an overall pollution monitoring system for a spacecraft vacuum thermal test provided by the invention.
The figures show that:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, the contamination monitoring system for the spacecraft vacuum thermal test provided by the invention comprises: the system comprises a vacuum tank 1, a spacecraft 2, a pollution sampling probe 3, a chromatographic analysis module 7, a mass spectrometry module 8, a vacuum module 9 and a remote measurement and control unit 10; the spacecraft 2 and the pollution sampling probe 3 are arranged in the vacuum tank 1; the vacuum tank 1 is connected with a chromatographic analysis module 7; the chromatographic analysis module 7 is connected with the mass spectrometry module 8; the mass spectrometry module 8 is connected with the vacuum module 9; the vacuum module 9 is connected with a remote measurement and control unit 10. And a standard flange interface 5 is arranged on the vacuum tank 1. In a preferred embodiment, the contamination monitoring system for the spacecraft vacuum thermal test comprises: the device comprises an in-tank pollution sampling unit, a multi-channel valve system, a chromatographic analysis module, a mass spectrometry module, a vacuum module and a remote measurement and control unit; the in-tank pollution sampling unit mainly comprises a pollution sampling probe and a gas transmission pipeline; the remote measurement and control unit mainly comprises a remote monitoring computer, a control cabinet, monitoring software, a database and the like.
Further, the chromatography module 7 includes: a carrier gas unit 71, a second electromagnetic cut-off valve 72, a transition chamber 73, a third electromagnetic cut-off valve 74, and a separation quantifying unit 75; the carrier gas unit 71, the transition cavity 73 and the separation quantitative unit 75 are connected in sequence; a second electromagnetic stop valve 72 is arranged between the carrier gas unit 71 and the transition cavity 73; a third electromagnetic stop valve 74 is arranged between the transition cavity 73 and the separation quantitative unit 75; the mass spectrometry module 8 comprises: a sample introduction system 81, an ion source 82, a mass analyzer 83, and a detector 84; the sample introduction system 81, the ion source 82, the mass analyzer 83 and the detector 84 are connected in sequence; the vacuum module 9 includes: a fourth electromagnetic cutoff valve 91, a high vacuum pump 92, and a backing pump 93; the fourth electromagnetic cutoff valve 91, the high vacuum pump 92, and the backing pump 93 are connected in this order. In a preferred embodiment, the vacuum degree of the vacuum tank environment is better than 1 multiplied by 10 < -3 > Pa, and the working temperature is-70 ℃ to 150 ℃; the number of the pollution sampling probes can be one or more, the pollution sampling probes are arranged near the sensitive part of the spacecraft and control sampling through a multi-channel valve system; the multi-channel valve system mainly comprises 3 electric control valves and 1 transition cavity, and the vacuum environment state in the vacuum tank is extracted by controlling the opening and closing states of the valves, so that the influence of a pollution monitoring system on the vacuum tank is avoided;
furthermore, a first electromagnetic stop valve 6 is arranged between the vacuum tank 1 and the chromatographic analysis module 7; the number of the pollution sampling probes 3 is multiple; the sample introduction system 81 includes: metal capillary and polydimethylsiloxane film; the metal capillary is mounted with a polydimethylsiloxane membrane. Further comprising: a gas transmission line 4; the vacuum tank 1 is connected with the chromatographic analysis module 7 through a gas transmission pipeline 4; the chromatographic analysis module 7 is connected with the mass spectrometry module 8 through a gas transmission pipeline 4; the mass spectrometry module 8 is connected with the vacuum module 9 through the gas transmission pipeline 4. In a preferred embodiment, the pressure control precision of the chromatographic analysis module is 0.01psi, and the quantitative concentration is better than 1 ppm; the mass spectrometry module detects that the molecular weight range of gas molecules is 1 amu-500 amu, and the resolution is superior to 1 amu; the sampling system for selecting the sampling system adopts a mode of combining a metal capillary and a polydimethylsiloxane film, an EI source is selected as an ion source, and a linear ion trap is selected as a mass analyzer; the signal amplification factor of the detector is up to 107 times, and the resolution of the analog-to-digital conversion circuit is 16 bits.
The invention provides a pollution monitoring method for a spacecraft vacuum thermal test, which comprises the following steps:
step 1, pollution sampling: closing the first electromagnetic stop valve 6 and the second electromagnetic stop valve 72, and starting the vacuum pump to ensure that the transition cavity 73 is in a vacuum state and the vacuum degree is higher than that in the vacuum tank 1; closing the third electromagnetic stop valve 74, opening the first electromagnetic stop valve 6, and enabling the volatile matters in the sampled gas to enter the transition cavity 73 through the pollution sampling probe 3, wherein the balance time is about 5 to 10 minutes, so that the components in the tank and the transition cavity are kept consistent; after the balance state is finished, closing the first electromagnetic stop valve 6, the second electromagnetic stop valve 72 and the third electromagnetic stop valve 74 to finish pollution sampling;
step 3, mass spectrometry: after the chromatographic analysis is completed, the components flow out of the chromatographic column, are introduced into the ion source 82 through the sample introduction system 81, complete the ionization process in the ion source 82, become charged ions, enter the mass analyzer 83 through the processes of focusing, transmission, acceleration and the like of the ion transmission device, separate the ions with different mass-to-charge ratios in the mass analyzer through the mass analysis process, and are detected by the detector 84;
and 4, data acquisition and analysis process: weak current signals are collected through a detector 84, are subjected to signal amplification and A/D conversion through a measurement and control system conversion circuit, and are fed back to a computer through the measurement and control system for collection and analysis processing, so that required mass spectrogram information can be obtained; and finally, comparing the data base to realize qualitative analysis of the pollutants.
Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, units provided by the present invention as pure computer readable program code, the system and its various devices, modules, units provided by the present invention can be fully implemented by logically programming method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units included in the system for realizing various functions can also be regarded as structures in the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A spacecraft vacuum thermal test pollution monitoring system is characterized by comprising: the device comprises a vacuum tank (1), a spacecraft (2), a pollution sampling probe (3), a chromatographic analysis module (7), a mass spectrometry module (8), a vacuum module (9) and a remote measurement and control unit (10);
the spacecraft (2) and the pollution sampling probe (3) are arranged in the vacuum tank (1);
the vacuum tank (1) is connected with a chromatographic analysis module (7);
the chromatographic analysis module (7) is connected with the mass spectrometry module (8);
the mass spectrometry module (8) is connected with the vacuum module (9);
the vacuum module (9) is connected with the remote measurement and control unit (10).
2. A spacecraft vacuum thermal test contamination monitoring system according to claim 1, characterized in that a standard flange interface (5) is provided on the vacuum tank (1).
3. Spacecraft thermogravimetric test contamination monitoring system according to claim 1, characterized in that said chromatographic module (7) comprises: the device comprises a carrier gas unit (71), a second electromagnetic stop valve (72), a transition cavity (73), a third electromagnetic stop valve (74) and a separation quantitative unit (75);
the carrier gas unit (71), the transition cavity (73) and the separation quantitative unit (75) are connected in sequence;
a second electromagnetic stop valve (72) is arranged between the carrier gas unit (71) and the transition cavity (73);
and a third electromagnetic stop valve (74) is arranged between the transition cavity (73) and the separation quantitative unit (75).
4. A spacecraft vacuum thermal test contamination monitoring system according to claim 1, wherein the mass spectrometry module (8) comprises: a sample introduction system (81), an ion source (82), a mass analyzer (83), and a detector (84);
the sample introduction system (81), the ion source (82), the mass analyzer (83) and the detector (84) are connected in sequence.
5. Spacecraft thermopneumatic test contamination monitoring system according to claim 1, characterized in that the vacuum module (9) comprises: a fourth electromagnetic stop valve (91), a high-vacuum pump (92) and a backing pump (93);
and the fourth electromagnetic stop valve (91), the high-vacuum pump (92) and the backing pump (93) are connected in sequence.
6. Spacecraft photothermal test contamination monitoring system according to claim 1, characterized in that a first electromagnetic shut-off valve (6) is arranged between the vacuum tank (1) and the chromatography module (7).
7. A spacecraft vacuum thermal test contamination monitoring system according to claim 1, wherein the contamination sampling probe (3) is plural.
8. A spacecraft Vacuothermic test contamination monitoring system according to claim 4, wherein the sample injection system (81) comprises: metal capillary and polydimethylsiloxane film; the metal capillary is mounted with a polydimethylsiloxane membrane.
9. The spacecraft vacuum thermal test contamination monitoring system of claim 1, further comprising: a gas transmission line (4);
the vacuum tank (1) is connected with the chromatographic analysis module (7) through a gas transmission pipeline (4);
the chromatographic analysis module (7) is connected with the mass spectrometry module (8) through a gas transmission pipeline (4);
the mass spectrometry module (8) is connected with the vacuum module (9) through a gas transmission pipeline (4).
10. A pollution monitoring method for a spacecraft vacuum thermal test is characterized by comprising the following steps:
step 1, pollution sampling: closing the first electromagnetic stop valve (6) and the second electromagnetic stop valve (72), starting a vacuum pump, and ensuring that the transition cavity (73) is in a vacuum state and the vacuum degree is higher than that in the vacuum tank (1); closing the third electromagnetic stop valve (74), opening the first electromagnetic stop valve (6), and enabling the volatile matters of the sampling gas to enter the transition cavity (73) through the pollution sampling probe (3), wherein the balance time is about 5-10 minutes, so that the components in the tank and the transition cavity are kept consistent; after the balance state is finished, closing the first electromagnetic stop valve (6), the second electromagnetic stop valve (72) and the third electromagnetic stop valve (74) to finish pollution sampling;
step 2, chromatographic quantitative analysis process: opening a second electromagnetic stop valve (72) and a third electromagnetic stop valve (74), opening a carrier gas unit (71), leading a sample to be analyzed in a transition cavity (73) to be carried into a separation quantitative unit (75) by carrier gas, and realizing the chromatographic analysis process of the mixed gas sample by utilizing the difference of the boiling point, the polarity and the adsorption property of substances;
step 3, mass spectrometry: after the chromatographic analysis is finished, the components flow out of the chromatographic column, are introduced into an ion source (82) through a sample introduction system (81), are ionized in the ion source (82) to become charged ions, enter a mass analyzer (83) through the processes of focusing, transmission, acceleration and the like of an ion transmission device, and are separated in the mass analyzer through the mass analysis process, and are detected by a detector (84);
and 4, data acquisition and analysis process: weak current signals are collected through a detector (84), are subjected to signal amplification and A/D conversion through a conversion circuit of a measurement and control system, and are fed back to a computer by the measurement and control system for collection and analysis processing, so that required mass spectrogram information can be obtained; and finally, comparing the data base to realize qualitative analysis of the pollutants.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112114067A (en) * | 2020-09-16 | 2020-12-22 | 上海裕达实业有限公司 | Coating gas evolution component detection mass spectrum system and method |
| CN113405773A (en) * | 2021-06-02 | 2021-09-17 | 中国科学院长春光学精密机械与物理研究所 | Space optical load outgassing test device and test method |
| CN113758947A (en) * | 2021-08-11 | 2021-12-07 | 中国科学院上海光学精密机械研究所 | Test device and method for inducing molecular pollution in spacecraft cabin by total ionization dose |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101303330A (en) * | 2007-05-09 | 2008-11-12 | 中国科学院大连化学物理研究所 | Film sample introduction sample enriching apparatus in on-line gas analysis mass spectrogram |
| CN102539479A (en) * | 2011-12-19 | 2012-07-04 | 北京卫星环境工程研究所 | Spacecraft in-cabin pollution load testing device |
| CN108362801A (en) * | 2018-05-15 | 2018-08-03 | 苏州铭谱源分析仪器有限公司 | It is a kind of can in qualitative and quantitative analysis vacuum system residue device and method |
| CN109799227A (en) * | 2019-03-14 | 2019-05-24 | 北京卫星环境工程研究所 | Vacuum thermal test space capsule gas-sample analysis system and analysis method |
-
2019
- 2019-11-14 CN CN201911113414.4A patent/CN110824049A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101303330A (en) * | 2007-05-09 | 2008-11-12 | 中国科学院大连化学物理研究所 | Film sample introduction sample enriching apparatus in on-line gas analysis mass spectrogram |
| CN102539479A (en) * | 2011-12-19 | 2012-07-04 | 北京卫星环境工程研究所 | Spacecraft in-cabin pollution load testing device |
| CN108362801A (en) * | 2018-05-15 | 2018-08-03 | 苏州铭谱源分析仪器有限公司 | It is a kind of can in qualitative and quantitative analysis vacuum system residue device and method |
| CN109799227A (en) * | 2019-03-14 | 2019-05-24 | 北京卫星环境工程研究所 | Vacuum thermal test space capsule gas-sample analysis system and analysis method |
Non-Patent Citations (8)
| Title |
|---|
| 侯可勇 等: "快速测量挥发性有机物的膜进样-飞行时间质谱仪的设计和应用", 《高等学校化学学报》 * |
| 朱艳: "《材料化学》", 31 October 2018 * |
| 焦子龙 等: "利用色质谱方法检测卫星真空热试验污染物成分", 《中国空间科学技术》 * |
| 窦仁超 等: "气体传感器在国外航天器上的应用", 《仪器仪表学报》 * |
| 范力 等: "大气挥发性有机物自动监测技术现状", 《四川环境》 * |
| 霍蕾 等: "高灵敏VOCs在线真空紫外单光子电离飞行时间质谱仪的研制", 《质谱学报》 * |
| 韩喜江: "《固体材料常用表征技术》", 31 January 2011 * |
| 龙希伟 等: "在线测量挥发性有机物的膜进样装置-四极质谱仪的设计和应用", 《舰船科学技术》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112114067A (en) * | 2020-09-16 | 2020-12-22 | 上海裕达实业有限公司 | Coating gas evolution component detection mass spectrum system and method |
| CN113405773A (en) * | 2021-06-02 | 2021-09-17 | 中国科学院长春光学精密机械与物理研究所 | Space optical load outgassing test device and test method |
| CN113758947A (en) * | 2021-08-11 | 2021-12-07 | 中国科学院上海光学精密机械研究所 | Test device and method for inducing molecular pollution in spacecraft cabin by total ionization dose |
| CN113758947B (en) * | 2021-08-11 | 2022-10-11 | 中国科学院上海光学精密机械研究所 | Test device and method for inducing molecular pollution in spacecraft cabin by total ionization dose |
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