CN114858689A - In-situ and semi-in-situ test shielding device for space comprehensive environment and test shielding method thereof - Google Patents
In-situ and semi-in-situ test shielding device for space comprehensive environment and test shielding method thereof Download PDFInfo
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- 239000000523 sample Substances 0.000 claims abstract description 59
- 239000002245 particle Substances 0.000 claims abstract description 19
- 230000005855 radiation Effects 0.000 claims abstract description 16
- 230000000149 penetrating effect Effects 0.000 claims description 21
- 238000011056 performance test Methods 0.000 claims description 6
- 238000004458 analytical method Methods 0.000 claims description 4
- 230000003287 optical effect Effects 0.000 claims description 4
- 238000001069 Raman spectroscopy Methods 0.000 claims description 3
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
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- 239000011449 brick Substances 0.000 claims description 3
- 238000004891 communication Methods 0.000 claims description 3
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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
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Abstract
The invention relates to a space comprehensive environment in-situ and semi-in-situ test shielding device and a test shielding method thereof. The invention relates to the technical field of space environment simulation and test, and the device comprises: the test device comprises a test device, a driving mechanism and a remote control system, wherein the driving mechanism is loaded with the test device, and the remote control system controls the driving mechanism; the test equipment comprises a test equipment host, a test equipment probe and a test equipment cabin-penetrating cable, and the test equipment cabin-penetrating cable is connected with the test equipment host and the test equipment probe; the test equipment host is positioned in the comprehensive cabin container, and a radiation protection structure is arranged on the periphery of the test equipment host; the invention can carry out in-situ and semi-in-situ test on the sample in the test by facing to space extreme environment factors such as vacuum, high and low temperature, solar irradiation, ultraviolet irradiation, charged particle irradiation and the like simulated on the ground.
Description
Technical Field
The invention relates to the technical field of space environment simulation and test, in particular to a shielding device for in-situ and semi-in-situ test of a space comprehensive environment and a test shielding method thereof.
Background
In order to timely and accurately master the evolution law of materials, devices and system component modules in extreme comprehensive environments such as vacuum, high and low temperature, irradiation (solar, ultraviolet, charged particles and the like), the test analysis must be carried out on the conditions of unchanged position and environment (in-situ) and the conditions of changeable position and environment (semi-in-situ). At present, the test aiming at the aspect mainly stays in a laboratory state, and instruments and equipment work in a conventional environment and cannot meet the in-situ/semi-in-situ test requirements.
Disclosure of Invention
The invention relates to space extreme environment factors such as vacuum, high and low temperature, solar irradiation, ultraviolet irradiation, charged particle irradiation and the like facing ground simulation, and can carry out in-situ and semi-in-situ test on a sample in a test, so the invention provides a shielding device for in-situ and semi-in-situ test of a space comprehensive environment and a test shielding method thereof, and the invention provides the following technical scheme:
a spatially integrated environment in-situ and semi-in-situ test shielding apparatus, the apparatus comprising: the test device comprises a test device, a driving mechanism and a remote control system, wherein the driving mechanism is loaded with the test device, and the remote control system controls the driving mechanism;
the test equipment comprises a test equipment host, a test equipment probe and a test equipment cabin-penetrating cable, and the test equipment cabin-penetrating cable is connected with the test equipment host and the test equipment probe; the test equipment host is positioned in the comprehensive cabin container, and a radiation protection structure is arranged on the periphery of the test equipment host;
the driving mechanism comprises an in-situ test equipment driving mechanism and a semi-in-situ test equipment driving mechanism; the in-situ test equipment driving mechanism is integrated on the sample table, and the semi-in-situ test equipment driving mechanism is arranged in the in-situ auxiliary cabin.
Preferably, the device further comprises a test equipment driving mechanism cabin penetrating cable, wherein the test equipment driving mechanism cabin penetrating cable comprises an in-situ test equipment driving mechanism cabin penetrating cable and a semi-in-situ test equipment driving mechanism cabin penetrating cable;
the driving mechanism is connected with the remote control system through a cabin penetrating cable of the in-situ test equipment driving mechanism and a cabin penetrating cable of the semi-in-situ test equipment driving mechanism for transmission communication.
Preferably, the test equipment probes comprise probes of in-situ test equipment and probes of semi-in-situ test equipment;
the in-situ test equipment is used for resisting particle irradiation, comprises a discharge pulse tester and is used for carrying out electrical performance test in the irradiation process;
the probe of the semi-in-situ test equipment is used for the tests which are not resistant or have weak resistance to the particle irradiation, comprises a Raman spectrometer, a fluorescence spectrometer and an optical performance tester and needs to be carried out in the irradiation intermittent stage.
Preferably, the radiation protection structure is provided with a radiation-proof door for test and equipment maintenance personnel to enter and exit.
Preferably, the in-situ test equipment driving mechanism comprises a folding component, a Y-direction moving component and an X/Z-direction moving component, drives the in-situ test equipment probe to move in X, Y, Z three directions, has multi-point test capability, and can be folded and folded after the test is finished.
Preferably, semi-normal position test equipment actuating mechanism includes that one-level extends subassembly, second grade and extends subassembly and rotating assembly, and one-level extends the subassembly and is the coarse adjustment mechanism of big stroke, and second grade extends the subassembly and is short stroke fine tuning mechanism, and the rotating assembly can carry on probe quantity and be no less than 3, when carrying out appointed performance test, with the probe to the position that corresponds with the sample test face.
Preferably, the radiation protection structure includes skeleton and shielding layer, the skeleton adopts steel frame construction, the shielding layer adopts aluminum plate and lead brick to build and forms.
An in-situ and semi-in-situ test shielding method for a space comprehensive environment comprises the following steps:
step 1: clamping a sample to be tested on a sample table, wherein a probe of in-situ test equipment is arranged on a driving mechanism of the in-situ test equipment, and a probe of semi-in-situ test equipment is arranged on the driving mechanism of the semi-in-situ test equipment;
step 2: a tester enters the radiation protection structure to start the test equipment host and set parameters, so that the test equipment host can acquire signals through the cabin-penetrating cable of the test equipment; after the preparation is finished, closing the cabin door to start the test;
and step 3: after the test is finished, the tester enters the radiation protection structure again, and the test data is exported through the test equipment host for subsequent processing and analysis.
Preferably, during the test, the particle irradiation dose rate in the in-situ auxiliary chamber is generally far lower than that in the main chamber, and the temperature is close to the room temperature.
Preferably, the in-situ test stably works in an electron irradiation source with vacuum magnitude of 10 & lt-3 & gt Pa, high and low temperature of 100K-473K, solar irradiation of 0.5-2 solar constants, ultraviolet irradiation of 0-3.5 vacuum ultraviolet constants and charged particle irradiation environment of 1.2 MeV.
The invention has the following beneficial effects:
the in-situ/semi-in-situ test system has optical and electrical test functions; the in-situ test system can stably and reliably work in vacuum (10-3Pa magnitude), high and low temperature (100K-473K), solar irradiation (0.5-2 solar constants), ultraviolet irradiation (0-3.5 vacuum ultraviolet constants) and charged particle irradiation environment (1.2MeV electron irradiation source, the highest electron energy is more than or equal to 1.2MeV, the highest current intensity is more than or equal to 10mA @1.0MeV, 200keV electron irradiation source, the highest electron energy is more than or equal to 200keV, the highest current intensity is more than or equal to 50mA @200keV, proton irradiation source, terminal voltage is 0.1-2 MV, proton beam intensity is more than or equal to 100 muA @ all proton energy ranges); the test equipment driving mechanism has the capability of simultaneously mounting a plurality of probes. The tested sample is arranged on a sample table and subjected to space extreme environment examination such as simulated vacuum, high and low temperature, solar irradiation, ultraviolet irradiation, charged particle irradiation and the like in the comprehensive cabin container, and in-situ/semi-in-situ test is carried out by the test system in the test process.
The invention provides an in-situ/semi-in-situ test method for a space comprehensive irradiation environment, which can be used for carrying out in-situ and semi-in-situ tests on a sample in a test by aiming at space extreme environment factors such as vacuum, high and low temperature, solar irradiation, ultraviolet irradiation, charged particle irradiation and the like simulated on the ground,
drawings
FIG. 1 is a schematic diagram of a spatial integrated irradiation environment in-situ/semi-in-situ test system;
FIG. 2 is a schematic view of the driving mechanism of the in-situ test apparatus mounted on the sample stage;
FIG. 3 is a schematic view of the driving mechanism of the semi-in-situ test apparatus installed in the in-situ sub-chamber;
fig. 4 instrument shield diagram.
Detailed Description
The present invention will be described in detail with reference to specific examples.
The first embodiment is as follows:
as shown in fig. 1 to 4, the specific optimized technical solution adopted to solve the above technical problems of the present invention is: the invention relates to an in-situ and semi-in-situ test shielding device for a space comprehensive environment and a test shielding method thereof.
A spatially integrated environment in-situ and semi-in-situ test shielding apparatus, the apparatus comprising: the device comprises a test device, a driving mechanism and a remote control system 10, wherein the test device is carried on the driving mechanism, and the remote control system controls the driving mechanism;
the test equipment comprises a test equipment host 2, a test equipment probe 3 and a test equipment cabin penetrating cable 4, wherein the test equipment cabin penetrating cable 4 is connected with the test equipment host 2 and the test equipment probe 3; the test equipment main machine 2 is positioned in the comprehensive cabin container, and the periphery of the test equipment main machine 2 is provided with a radiation protection structure 7;
the driving mechanism comprises an in-situ test equipment driving mechanism 5 and a semi-in-situ test equipment driving mechanism 6; the in-situ test equipment driving mechanism 5 is integrated on the sample table 1-1, and the semi-in-situ test equipment driving mechanism 6 is arranged in the in-situ auxiliary cabin 1-2.
The device also comprises a test equipment driving mechanism cabin penetrating cable, wherein the test equipment driving mechanism cabin penetrating cable comprises an in-situ test equipment driving mechanism cabin penetrating cable 8 and a semi-in-situ test equipment driving mechanism cabin penetrating cable 9;
the driving mechanism is connected with the remote control system through a cabin penetrating cable 8 of the in-situ test equipment driving mechanism and a cabin penetrating cable 9 of the semi-in-situ test equipment driving mechanism for transmission communication.
The tested sample is arranged on the sample table 1-1, and is subjected to space extreme environment examination such as simulated vacuum, high and low temperature, solar irradiation, ultraviolet irradiation, charged particle irradiation and the like in the comprehensive cabin container 1, and in-situ/semi-in-situ test is carried out by the test system in the test process.
The probe 3 of the test equipment comprises a probe 3-1 of in-situ test equipment and a probe 3-2 of semi-in-situ test equipment;
the in-situ test equipment is used for resisting particle irradiation, comprises a discharge pulse tester and is used for carrying out electrical performance test in the irradiation process;
the probe of the semi-in-situ test equipment is used for the tests which are not resistant or have weak resistance to the particle irradiation, comprises a Raman spectrometer, a fluorescence spectrometer and an optical performance tester and needs to be carried out in the irradiation intermittent stage.
And a radiation-proof door is arranged on the radiation protection structure 7 and is used for test and equipment maintenance personnel to enter and exit.
The in-situ test equipment driving mechanism 5 comprises a folding assembly 5-1, a Y-direction moving assembly 5-2 and an X/Z-direction moving assembly 5-3, can drive the probe of the in-situ test equipment to move in X, Y, Z three directions, has multi-point test capability, can be folded and folded after the test is finished, and reduces the occupied space.
The semi-in-situ test equipment driving mechanism 6 comprises a first-stage extension assembly 6-1, a second-stage extension assembly 6-2 and a rotating assembly 6-3, wherein the first-stage extension assembly is a large-stroke coarse adjustment mechanism and can drive a probe (3-2) to rapidly extend out of an in-situ auxiliary cabin, the second-stage extension assembly is a short-stroke fine adjustment mechanism and is used for finely adjusting the distance between the probe and a sample, the number of probes which can be carried by the rotating assembly is not less than 3, and when a specified performance test is carried out, the probe is rotated to a position corresponding to a sample test surface.
The radiation protection structure 7 comprises a framework 7-1 and a shielding layer 7-2, the framework is of a steel frame structure, and the shielding layer is built by aluminum plates and lead bricks.
An in-situ and semi-in-situ test shielding method for a space comprehensive environment comprises the following steps:
step 1: clamping a sample to be tested on a sample table, wherein a probe of in-situ test equipment is arranged on a driving mechanism of the in-situ test equipment, and a probe of semi-in-situ test equipment is arranged on the driving mechanism of the semi-in-situ test equipment;
step 2: a tester enters the radiation protection structure to start a test equipment host and set parameters, so that the test equipment host can acquire signals through the cabin penetrating cable of the test equipment; after the preparation is finished, closing the cabin door to start the test;
and step 3: after the test is finished, the tester enters the radiation protection structure again, and the test data is exported through the test equipment host for subsequent processing and analysis.
During the test, the particle irradiation dose rate in the in-situ auxiliary chamber is usually far lower than that in the main chamber, and the temperature is close to the room temperature.
The in-situ test stably works in a vacuum 10 & lt-3 & gt Pa magnitude, high and low temperature 100K & lt-473 & gt K & lt, 0.5-2 solar constants of solar irradiation, 0-3.5 vacuum ultraviolet constants of ultraviolet irradiation and a charged particle irradiation environment 1.2MeV electron irradiation source.
The above description is only a preferred embodiment of the in-situ and semi-in-situ testing shielding device for the comprehensive space environment and the testing shielding method thereof, and the protection scope of the in-situ and semi-in-situ testing shielding device for the comprehensive space environment and the testing shielding method thereof is not limited to the above embodiments, and all technical schemes belonging to the idea belong to the protection scope of the invention. It should be noted that modifications and variations which do not depart from the gist of the invention will be those skilled in the art to which the invention pertains and which are intended to be within the scope of the invention.
Claims (10)
1. The utility model provides a space integrated environment normal position and half normal position test shield assembly which characterized by: the device comprises: the test device comprises a test device, a driving mechanism and a remote control system, wherein the driving mechanism is loaded with the test device, and the remote control system controls the driving mechanism;
the test equipment comprises a test equipment host, a test equipment probe and a test equipment cabin-penetrating cable, and the test equipment cabin-penetrating cable is connected with the test equipment host and the test equipment probe; the test equipment host is positioned in the comprehensive cabin container, and a radiation protection structure is arranged on the periphery of the test equipment host;
the driving mechanism comprises an in-situ test equipment driving mechanism and a semi-in-situ test equipment driving mechanism; the in-situ test equipment driving mechanism is integrated on the sample table, and the semi-in-situ test equipment driving mechanism is arranged in the in-situ auxiliary cabin.
2. The in-situ and semi-in-situ test shielding device for the integrated environment of space of claim 1, wherein: the device also comprises a test equipment driving mechanism cabin penetrating cable, wherein the test equipment driving mechanism cabin penetrating cable comprises an in-situ test equipment driving mechanism cabin penetrating cable and a semi-in-situ test equipment driving mechanism cabin penetrating cable;
the driving mechanism is connected with the remote control system through a cabin penetrating cable of the in-situ test equipment driving mechanism and a cabin penetrating cable of the semi-in-situ test equipment driving mechanism for transmission communication.
3. The in-situ and semi-in-situ test shielding device for the space integrated environment as claimed in claim 2, wherein: the test equipment probe comprises a probe of in-situ test equipment and a probe of semi-in-situ test equipment;
the in-situ test equipment is used for resisting particle irradiation, comprises a discharge pulse tester and is used for carrying out electrical performance test in the irradiation process;
the probe of the semi-in-situ test equipment is used for the tests which are not resistant or have weak resistance to the particle irradiation, comprises a Raman spectrometer, a fluorescence spectrometer and an optical performance tester and needs to be carried out in the irradiation intermittent stage.
4. The in-situ and semi-in-situ test shielding device for the integrated environment in space of claim 3, wherein: and the radiation protection structure is provided with a radiation-proof door for test and equipment maintenance personnel to enter and exit.
5. The in-situ and semi-in-situ test shielding device for the integrated environment in space of claim 2, wherein: the in-situ test equipment driving mechanism comprises a folding assembly, a Y-direction moving assembly and an X/Z-direction moving assembly, drives the probe of the in-situ test equipment to move in X, Y, Z three directions, has multipoint test capability, and can be folded and folded after the test is finished.
6. The in-situ and semi-in-situ test shielding device for the integrated environment in space of claim 2, wherein: half normal position test equipment actuating mechanism includes that one-level extends subassembly, second grade and extends subassembly and runner assembly, and the one-level extends the subassembly and is the coarse adjustment mechanism of big stroke, and the second grade extends the subassembly and be short stroke fine tuning mechanism, and 3 can be no less than to runner assembly carry on probe quantity, when carrying out appointed performance test, with the probe to the position that corresponds with the sample test face.
7. The in-situ and semi-in-situ test shielding device for the integrated environment in space of claim 4, wherein: the radiation protection structure comprises a framework and a shielding layer, the framework is of a steel frame structure, and the shielding layer is formed by building aluminum plates and lead bricks.
8. A space comprehensive environment in-situ and semi-in-situ test shielding method is characterized by comprising the following steps: the method comprises the following steps:
step 1: clamping a sample to be tested on a sample table, wherein a probe of in-situ test equipment is arranged on a driving mechanism of the in-situ test equipment, and a probe of semi-in-situ test equipment is arranged on the driving mechanism of the semi-in-situ test equipment;
step 2: a tester enters the radiation protection structure to start the test equipment host and set parameters, so that the test equipment host can acquire signals through the cabin-penetrating cable of the test equipment; after the preparation is finished, closing the cabin door to start the test;
and step 3: after the test is finished, the tester enters the radiation protection structure again, and the test data is exported through the test equipment host for subsequent processing and analysis.
9. The in-situ and semi-in-situ test shielding method for the integrated environment in space of claim 8, wherein: during the test, the particle irradiation dose rate in the in-situ auxiliary chamber is usually far lower than that in the main chamber, and the temperature is close to the room temperature.
10. The in-situ and semi-in-situ test shielding method for the integrated space environment as claimed in claim 9, wherein: the in-situ test stably works in a vacuum 10 & lt-3 & gt Pa magnitude, high and low temperature 100K & lt-473 & gt K & lt, 0.5-2 solar constants of solar irradiation, 0-3.5 vacuum ultraviolet constants of ultraviolet irradiation and a charged particle irradiation environment 1.2MeV electron irradiation source.
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