CN115228514A - Planetary high-low temperature vacuum environment simulation experiment system - Google Patents
Planetary high-low temperature vacuum environment simulation experiment system Download PDFInfo
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- CN115228514A CN115228514A CN202211022857.4A CN202211022857A CN115228514A CN 115228514 A CN115228514 A CN 115228514A CN 202211022857 A CN202211022857 A CN 202211022857A CN 115228514 A CN115228514 A CN 115228514A
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- 238000004088 simulation Methods 0.000 title claims abstract description 30
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 106
- 239000007788 liquid Substances 0.000 claims abstract description 44
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 43
- 238000002474 experimental method Methods 0.000 claims abstract description 38
- 238000003860 storage Methods 0.000 claims abstract description 24
- 229910001873 dinitrogen Inorganic materials 0.000 claims description 22
- 238000010438 heat treatment Methods 0.000 claims description 15
- 239000007789 gas Substances 0.000 claims description 13
- 239000007791 liquid phase Substances 0.000 claims description 11
- 239000012071 phase Substances 0.000 claims description 11
- 230000001502 supplementing effect Effects 0.000 claims description 11
- 238000005086 pumping Methods 0.000 claims description 3
- 230000005855 radiation Effects 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims 1
- 239000012530 fluid Substances 0.000 description 9
- 238000001802 infusion Methods 0.000 description 9
- 238000012546 transfer Methods 0.000 description 8
- 238000001514 detection method Methods 0.000 description 7
- 238000000034 method Methods 0.000 description 7
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 description 6
- 238000012360 testing method Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 238000011160 research Methods 0.000 description 3
- 241000282414 Homo sapiens Species 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000012613 in situ experiment Methods 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01L—CHEMICAL OR PHYSICAL LABORATORY APPARATUS FOR GENERAL USE
- B01L1/00—Enclosures; Chambers
- B01L1/02—Air-pressure chambers; Air-locks therefor
- B01L1/025—Environmental chambers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01L—CHEMICAL OR PHYSICAL LABORATORY APPARATUS FOR GENERAL USE
- B01L7/00—Heating or cooling apparatus; Heat insulating devices
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01L—CHEMICAL OR PHYSICAL LABORATORY APPARATUS FOR GENERAL USE
- B01L9/00—Supporting devices; Holding devices
- B01L9/06—Test-tube stands; Test-tube holders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01L—CHEMICAL OR PHYSICAL LABORATORY APPARATUS FOR GENERAL USE
- B01L2300/00—Additional constructional details
- B01L2300/04—Closures and closing means
- B01L2300/041—Connecting closures to device or container
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01L—CHEMICAL OR PHYSICAL LABORATORY APPARATUS FOR GENERAL USE
- B01L2300/00—Additional constructional details
- B01L2300/18—Means for temperature control
- B01L2300/1838—Means for temperature control using fluid heat transfer medium
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01L—CHEMICAL OR PHYSICAL LABORATORY APPARATUS FOR GENERAL USE
- B01L2300/00—Additional constructional details
- B01L2300/18—Means for temperature control
- B01L2300/1894—Cooling means; Cryo cooling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
- B64G2007/005—Space simulation vacuum chambers
Abstract
The invention discloses a planetary high-low temperature vacuum environment simulation experiment system, and relates to the technical field of experiment equipment; the device comprises an experimental cabin which is arranged in a sealed mode, wherein a sample table capable of conducting cold or heat is arranged in the experimental cabin, the experimental cabin is externally connected with a vacuumizing device, the bottom of the sample table is provided with a heat exchange device, and the heat exchange device is externally connected with a liquid nitrogen storage device. The planet high-low temperature vacuum environment simulation experiment system provided by the invention has a large simulation temperature range, can simulate a vacuum low-temperature or vacuum high-temperature environment, and is suitable for experiments on samples in various environment states.
Description
Technical Field
The invention relates to the technical field of experimental equipment, in particular to a planetary high-low temperature vacuum environment simulation experiment system.
Background
In recent decades, including implementation and deployment of Chang E engineering in China, apollo program in the United states and the like, human beings have made remarkable recognition and achievement on lunar exploration and deep space exploration. With the rapid development of detection activities, the detection of extraterrestrial celestial bodies by human beings will be changed from the polar regions of near-earth, middle-low latitude to the polar regions of far-distance and high latitude. The current detection plan to be developed faces the severe challenges of poor or missing remote sensing data quality, extreme temperature environments and the like. Based on the current situation, the development of ground verification experimental research in advance has extremely important engineering significance and scientific value.
Taking the moon as an example, the permanent shadow area mainly located in the range of 20 degrees of the north and south poles of the moon has extremely severe temperature conditions, the temperature range is 120-29K, the temperature is low, and the change is small, so that the moon belongs to an extremely low temperature environment; taking the minor planet as an example, although the orbit and the rotation period of the minor planet are different, the whole planet has the characteristic of larger temperature difference and faster rotation period. The high and low temperature state is converted quickly. Extreme temperature environments and environmental states with rapidly changing temperatures bring great obstacles to extraterrestrial moon and deep space exploration.
In order to smoothly carry out an actual detection process and avoid the obstruction of extreme environments such as high and low temperatures to the detection process as much as possible, ground verification experimental research of the extreme environments such as high and low temperatures in a deep space needs to be carried out in advance, the actual vacuum environment and temperature limit environment of other extraterrestrial objects in the universe need to be simulated in the research process, however, the simulation temperature range of the existing experimental device is small, the basic environment of the universe cannot be accurately simulated, and the experimental result is inaccurate.
Disclosure of Invention
The invention aims to provide a planetary high-low temperature vacuum environment simulation experiment system, which solves the problems in the prior art, has a large simulation temperature range, can simulate a vacuum low-temperature environment, and has a wide optional range of experiment environment states.
In order to achieve the purpose, the invention provides the following scheme:
the invention provides a planetary high-low temperature vacuum environment simulation experiment system which comprises an experiment chamber arranged in a closed mode, wherein a sample table capable of conducting cold or heat is arranged in the experiment chamber, the experiment chamber is externally connected with vacuum pumping equipment, the bottom of the sample table is provided with a heat exchange device, and the heat exchange device is externally connected with a liquid nitrogen storage device. The experimental chamber is vacuumized, and after the preset vacuum degree is reached, the heat exchange device is communicated with the liquid nitrogen storage device, and the liquid nitrogen is heated into nitrogen gas to exchange heat with the sample, so that a low-temperature or high-temperature environment is provided for the sample, the simulation of a lunar vacuum low-temperature or high-temperature environment can be realized, and then a sample test under the environment can be carried out.
Optionally, the top of the experiment chamber is connected with a replaceable hatch cover through a flange seal, so that different flange interfaces can be adopted and different instruments can be externally connected to realize in-situ experiment operation/detection on the sample.
Optionally, heat transfer device including set up in the serpentine coil of sample platform bottom portion, the serpentine coil both ends pass through the pipeline with liquid nitrogen storage device connects, serpentine coil with be provided with the valve on the pipeline that liquid nitrogen storage device connects, be used for letting in nitrogen gas or liquid nitrogen in the serpentine coil, serpentine coil's bending structure has prolonged the circulating path of liquid nitrogen or nitrogen gas, has increased heat transfer time, has improved the heat transfer effect, can be quick with sample platform heat transfer, and then provide required low temperature or high temperature environment for sample bench sample.
Optionally, the liquid nitrogen storage device is connected with a liquid phase joint and a gas phase joint respectively, the liquid phase joint is connected with one end of the serpentine coil through a connecting pipe, and a low-temperature electromagnetic valve is arranged between the liquid phase joint and the connecting pipe; one end of the gas phase joint penetrates through the nitrogen heating device and then is connected with the serpentine coil through the connecting pipe, and a high-temperature electromagnetic valve is arranged on the gas phase joint between the nitrogen heating device and the connecting pipe; one end of the serpentine coil is connected with the connecting pipe, the other end of the serpentine coil is externally connected with a nitrogen gas exhaust port through an exhaust pipeline, liquid nitrogen or heated nitrogen gas can be respectively introduced into the serpentine coil by controlling the opening and closing of the low-temperature electromagnetic valve and the high-temperature electromagnetic valve, the sample stage can be further refrigerated or heated, and the nitrogen gas after heat exchange with the sample stage is exhausted through the nitrogen gas exhaust port; low temperature solenoid valve, high temperature solenoid valve and nitrogen gas heating device are connected with control system respectively, and control system is connected with temperature measuring device through signal feedback return circuit, and temperature measuring device is located sample platform position department, can send the temperature value of sample platform in to control system to convert the signal of telecommunication into and handle through control system analysis, control system can be according to the temperature value and the default of sample platform department compare, and according to the difference of actual temperature value and default as the foundation, control low temperature solenoid valve, high temperature solenoid valve and nitrogen gas heating device's switching heats or refrigerates sample platform department automatically to control system can be as required automatically regulated sample platform department's temperature, realizes the automatic rising of sample platform department temperature.
Optionally, the vacuum pumping device comprises a vacuum pump and a molecular pump, the vacuum pump and the molecular pump are respectively communicated with the experiment chamber through vacuum pipelines, the experiment chamber and the sample table can be respectively pumped, and the vacuum degree is high.
Optionally, a sample rack is arranged in the experiment chamber, the sample rack is arranged on the sample rack, and the serpentine coil is located between the sample rack and the sample rack; in the embodiment of the invention, the cross section of the sample groove is of a circular or rectangular structure, the sample table is suitable for various samples of different specifications, can be replaced, further increases the types of samples which can be tested, and can be fixed on the sample table frame through the clamping device, so that the movement of the sample table in the test process is avoided, the positioning is accurate, and the test is convenient.
Optionally, a heat dissipation fan is installed on the exhaust pipeline, so that high-temperature nitrogen can be discharged after heat dissipation; be provided with auxiliary heater on the connecting pipe, can heat the nitrogen gas of carrying to serpentine coil to the heat transfer of serpentine coil department of being convenient for, the high temperature ambient temperature scope that can build is bigger.
Optionally, the experiment cabin is connected with the fluid infusion storage tank through the fluid infusion pneumatic valve, the fluid infusion storage tank is external to have the fluid infusion pipeline to can reduce the liquid nitrogen loss among the cycle process, can form the circulation with the snakelike coil pipe in below, similar liquid level keeps the ware principle, when liquid nitrogen is sufficient in the snakelike coil pipe, the liquid level is higher than the liquid level and keeps the ware, fluid infusion storage tank and fluid infusion pipeline inside carry out the self-loopa this moment, when liquid nitrogen is not enough in the snakelike coil pipe, be less than the liquid level and keep the ware, carry out the fluid infusion in to the snakelike coil pipe through fluid infusion storage tank and fluid infusion pipeline this moment.
Compared with the prior art, the invention has the following technical effects:
the replaceable hatch cover is arranged at the top of the experiment cabin, so that the hatch cover can be customized according to use requirements, and the size of the observation window and the flange interface can be customized by the customized hatch cover, so that different kinds of in-situ tests can be carried out on experiment samples. Adopt the nitrogen gas or the liquid nitrogen of heating to carry to serpentine coil department, with the sample platform heat transfer that has cold conduction and thermal conductivity nature, and then can build required low temperature or high temperature environment for the sample, can be to experiment cabin and sample platform department evacuation respectively through evacuation equipment, the vacuum is high, can form the vacuum low temperature or the high temperature environment of simulation moon, the experiment of the sample of being convenient for.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required in the embodiments will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a planetary high-low temperature vacuum environment simulation experiment system of the present invention;
FIG. 2 is a schematic front view of a planetary high-low temperature vacuum environment simulation experiment system according to the present invention;
FIG. 3 is a schematic side view of a planetary high and low temperature vacuum environment simulation experiment system according to the present invention;
FIG. 4 is a schematic view of a sample rack and a sample table connecting structure of the planetary high-low temperature vacuum environment simulation experiment system of the present invention;
FIG. 5 is an exploded view of a sample stage and a sample stage of the planetary high-low temperature vacuum environment simulation experiment system according to the present invention;
description of reference numerals: the experimental system comprises a 100-planetary high-low temperature vacuum environment simulation experiment system, a 1-experiment chamber, a 2-chamber cover, a 3-sample table, a 4-serpentine coil, a 5-liquid phase connector, a 6-connecting pipe, a 7-low temperature electromagnetic valve, a 8-gas phase connector, a 9-nitrogen heating device, a 10-high temperature electromagnetic valve, a 11-nitrogen exhaust port, a 12-vacuum pump, a 13-molecular pump, a 14-sample table frame, a 15-sample tank, a 16-liquid supplementing storage tank, a 17-liquid supplementing pneumatic valve and an 18-liquid supplementing pipeline.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide a planetary high-low temperature vacuum environment simulation experiment system, which solves the problems in the prior art, has a large simulation temperature range, can simulate a vacuum low-temperature environment, and has a wide optional range of experiment environment states.
In order to make the aforementioned objects, features and advantages of the present invention more comprehensible, the present invention is described in detail with reference to the accompanying drawings and the detailed description thereof.
As shown in fig. 1, fig. 2 and fig. 3, the present invention provides a planetary high and low temperature vacuum environment simulation experiment system 100, which comprises a hermetically arranged experiment chamber 1, wherein the top of the experiment chamber 1 is hermetically connected with a replaceable hatch cover 2 through a flange, so that different flange interfaces can be adopted, and different instruments can be externally connected to the experiment chamber, so as to realize different experiment operations on samples; the experiment chamber 1 is internally provided with a sample table 3 capable of conducting cold or heat, the experiment chamber 1 is externally connected with a vacuumizing device, the bottom of the sample table 3 is provided with a heat exchange device, the heat exchange device is externally connected with a liquid nitrogen storage device, and a heat transfer medium can adopt liquid nitrogen and heated nitrogen. The method comprises the steps of placing a sample to be tested on a sample table, vacuumizing the test chamber 1, connecting a liquid nitrogen storage device with a heat exchange device after a vacuum detection device detects that a preset vacuum degree is reached, and opening or closing an auxiliary heating device, so that a high-temperature or low-temperature environment is provided for the sample, simulation of a lunar vacuum low-temperature or high-temperature environment can be realized, and then a sample test under the environment can be carried out.
Specifically, the heat exchange device comprises a serpentine coil 4 arranged at the bottom of the sample stage 3, two ends of the serpentine coil 4 are connected with the liquid nitrogen storage device through a pipeline, valves are arranged on the pipelines of the serpentine coil 4 and the liquid nitrogen storage device, nitrogen or liquid nitrogen is introduced into the serpentine coil 4, and compared with a traditional straight pipe structure, a bent structure of the serpentine coil prolongs the flow path of the liquid nitrogen or the nitrogen, increases the heat exchange time, improves the heat exchange effect, can quickly exchange heat with the sample stage 3, further provides a required low-temperature or high-temperature environment for a sample on the sample stage 3, and the temperature control precision can reach within 1 degree; the temperature control range can reach-196 ℃ to 200 ℃. The liquid nitrogen storage device is respectively connected with a liquid phase connector 5 and a gas phase connector 8, the liquid phase connector 5 is connected with one end of the serpentine coil 4 through a connecting pipe 6, and a low-temperature electromagnetic valve 7 is arranged between the liquid phase connector 5 and the connecting pipe 6; one end of a gas phase joint 8 penetrates through a nitrogen heating device 9 and then is connected with the serpentine coil 4 through a connecting pipe 6, and a high-temperature electromagnetic valve 10 is arranged on the gas phase joint 8 between the nitrogen heating device 9 and the connecting pipe 6; one end of the serpentine coil 4 is connected with a connecting pipe 6, the other end of the serpentine coil is externally connected with a nitrogen gas exhaust port 11 through an exhaust pipeline, the liquid nitrogen or the heated nitrogen gas can be respectively introduced into the serpentine coil 4 by controlling the opening and closing of the low-temperature electromagnetic valve 7 and the high-temperature electromagnetic valve 10, so that the sample stage 3 can be refrigerated or heated, an auxiliary heater is arranged on the connecting pipe 6, the nitrogen gas conveyed to the serpentine coil 4 can be heated, the heat exchange at the serpentine coil 4 is facilitated, and the temperature range of a high-temperature environment which can be created is larger; the nitrogen gas after exchanging heat with the sample stage 3 is discharged through the nitrogen gas exhaust port 11, and a heat radiation fan is installed on the exhaust pipeline and can be discharged after heat radiation is performed on the high-temperature nitrogen gas.The vacuumizing equipment comprises a vacuum pump 12 and a molecular pump 13, the vacuum pump 12 and the molecular pump 13 are respectively communicated with the experiment chamber 1 through a vacuum pipeline, the vacuum pipeline can extend to the position of the sample table 3, the experiment chamber 1 and the position of the sample table 3 can be respectively vacuumized, the vacuum degree is high and can reach 10 -4 Pa, and further realizing sample experiments under different states.
Further preferably, a sample table 14 is arranged in the experiment chamber 1, as shown in fig. 4 and 5, the sample table 3 is arranged on the sample table 14, and the serpentine coil 4 is positioned between the sample table 14 and the sample table 3; a plurality of sample grooves 15 have been seted up on sample platform 3, and sample groove 15 cross section is circular or rectangle structure, is applicable to the multiple sample of different specifications, and sample platform 3 can be changed, has further increased the kind that can experiment sample, and sample platform 3 can be fixed in sample rack 14 through latch device on, has avoided sample platform 3's removal in the experimentation, fixes a position accurately, the experiment of being convenient for. The experiment chamber 1 is connected with a liquid supplementing storage tank 16 through a liquid supplementing pneumatic valve 17, and the liquid supplementing storage tank 16 is externally connected with a liquid supplementing pipeline 18.
When the device works, a sample is placed on the sample table 3, different experimental instruments are externally connected to the top of the experiment chamber 1 through flanges according to needs, the vacuum pump 12 and the molecular pump 13 vacuumize the interior of the experiment chamber 1, so that a moon vacuum environment is simulated, the high-temperature electromagnetic valve 10 is closed, the low-temperature electromagnetic valve 7 is opened, liquid nitrogen is conveyed to the serpentine coil 4 through the liquid phase connector 5 and the connecting pipe 6, and heat exchange is carried out between the serpentine coil 4 and the sample table 3, so that the sample table 3 has a required low-temperature environment, and the vacuum low-temperature environment can be developed; when needs carry out the high temperature environment experiment, only need close low temperature solenoid valve 7, open high temperature solenoid valve 10, the liquid nitrogen gets into connecting pipe 6 after 8 transport to nitrogen gas heating device 9 heating for nitrogen gas through the gas phase joint this moment, and deliver to 4 departments of serpentine coil pipe through connecting pipe 6, then heat sample platform 3, and then build vacuum high temperature experiment environment, nitrogen gas after the heat transfer is carried to 11 discharges of nitrogen gas vent through 4 other ends of serpentine coil pipe, for avoiding the exhaust gas high temperature, can open the radiator fan of gas vent department to its cooling. The low-temperature electromagnetic valve 7 and the high-temperature electromagnetic valve 10 are respectively and electrically connected with a control system, so that the opening and closing states can be automatically switched according to needs, and the multi-period automatic cold and hot constant-speed circulation can be realized.
In the description of the present invention, it should be noted that the terms "center", "top", "bottom", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
The principle and the implementation mode of the invention are explained by applying a specific example, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the foregoing, the description is not to be taken in a limiting sense.
Claims (8)
1. The utility model provides a high low temperature vacuum environment simulation experiment system of planet which characterized in that: the device comprises an experimental cabin which is arranged in a sealed mode, wherein a sample table capable of conducting cold or heat is arranged in the experimental cabin, the experimental cabin is externally connected with a vacuumizing device, the bottom of the sample table is provided with a heat exchange device, and the heat exchange device is externally connected with a liquid nitrogen storage device.
2. The planetary high-low temperature vacuum environment simulation experiment system according to claim 1, wherein: the top of the experiment cabin is connected with a replaceable cabin cover through a flange in a sealing manner.
3. The planetary high-low temperature vacuum environment simulation experiment system according to claim 1, wherein: the heat exchange device comprises a coiled pipe arranged at the bottom of the sample platform, the two ends of the coiled pipe are connected with the liquid nitrogen storage device through pipelines, and a valve is arranged on the pipeline connected with the liquid nitrogen storage device through the coiled pipe.
4. The planetary high-low temperature vacuum environment simulation experiment system according to claim 3, wherein: the liquid nitrogen storage device is respectively connected with a liquid phase joint and a gas phase joint, the liquid phase joint is connected with one end of the coiled pipe through a connecting pipe, and a low-temperature electromagnetic valve is arranged between the liquid phase joint and the connecting pipe; one end of the gas phase joint penetrates through the nitrogen heating device and then is connected with the serpentine coil through the connecting pipe, and a high-temperature electromagnetic valve is arranged on the gas phase joint between the nitrogen heating device and the connecting pipe; one end of the serpentine coil is connected with the connecting pipe, and the other end of the serpentine coil is externally connected with a nitrogen gas exhaust port through an exhaust pipeline; the low-temperature electromagnetic valve, the high-temperature electromagnetic valve and the nitrogen heating device are respectively connected with a control system, and the control system can control the low-temperature electromagnetic valve, the high-temperature electromagnetic valve and the nitrogen heating device to be opened and closed according to the temperature value at the sample stage.
5. The planetary high-low temperature vacuum environment simulation experiment system according to claim 1, wherein: the vacuum pumping equipment comprises a vacuum pump and a molecular pump, and the vacuum pump and the molecular pump are respectively communicated with the experiment cabin through vacuum pipelines.
6. The planetary high-low temperature vacuum environment simulation experiment system according to claim 3, wherein: a sample rack is arranged in the experiment chamber, the sample rack is arranged on the sample rack, and the snake-shaped coil pipe is positioned between the sample rack and the sample rack; the sample table is provided with a plurality of sample grooves.
7. The planetary high-low temperature vacuum environment simulation experiment system according to claim 4, wherein: a heat radiation fan is arranged on the exhaust pipeline; and an auxiliary heater is arranged on the connecting pipe.
8. The planetary high-low temperature vacuum environment simulation experiment system according to claim 1, wherein: the experiment cabin is connected with a liquid supplementing storage tank through a liquid supplementing pneumatic valve, and the liquid supplementing storage tank is externally connected with a liquid supplementing pipeline.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211022857.4A CN115228514B (en) | 2022-08-25 | 2022-08-25 | Planet high-low temperature vacuum environment simulation experiment system |
| GB2215574.1A GB2622114A (en) | 2022-08-25 | 2022-10-21 | Experimental system for simulating high or low temperature vacuum environment of planet |
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| CN202211022857.4A CN115228514B (en) | 2022-08-25 | 2022-08-25 | Planet high-low temperature vacuum environment simulation experiment system |
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| CN115228514A true CN115228514A (en) | 2022-10-25 |
| CN115228514B CN115228514B (en) | 2024-05-07 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116989998A (en) * | 2023-07-13 | 2023-11-03 | 海辰精密机械(嘉兴)股份有限公司 | Detection device |
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| CN113920804A (en) * | 2021-09-26 | 2022-01-11 | 哈尔滨工业大学 | Large-scale multi-factor space irradiation environment integrated simulation device and simulation method |
| CN114062241A (en) * | 2021-12-17 | 2022-02-18 | 上海空间电源研究所 | Space environment simulation system |
| CN114720892A (en) * | 2022-04-18 | 2022-07-08 | 国检测试控股集团雄安有限公司 | Battery thermal failure test system |
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| CN116989998A (en) * | 2023-07-13 | 2023-11-03 | 海辰精密机械(嘉兴)股份有限公司 | Detection device |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2622114A (en) | 2024-03-06 |
| GB202215574D0 (en) | 2022-12-07 |
| CN115228514B (en) | 2024-05-07 |
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