A comprehensive simulation device for surface environment of extraterrestrial bodies

Abstract

The application discloses an extraterrestrial body surface environment comprehensive simulation device, and relates to the field of extraterrestrial body surface environment simulation.The device comprises a vacuum cavity, which can simulate the vacuum environment or the atmospheric composition of the extraterrestrial body surface after being vacuumized or filled with a specific atmosphere.The vacuum cavity is provided with an extension interface, an observation window and a reserved interface on the side wall or other preferred positions, and a pulsed laser deposition system and other equipment are incident from the reserved interface or the observation window to simulate the space weathering process represented by micro-meteorite impact; a temperature control system is used to adjust the temperature of a loading platform to a temperature value required for simulating the high-temperature and low-temperature environment of the extraterrestrial body surface; the observation window is used to observe the test sample in the simulation process, and the reserved interface is connected with a characterization instrument to obtain the change of the related characteristics of the test sample in situ.The application can simulate and truly reflect the extraterrestrial body surface environment and the space weathering modification effect, and can be used for in-situ characterization, thereby providing reliable ground verification and prediction for the difficulties and challenges that may be faced by a deep space exploration task.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of extraterrestrial surface environment simulation devices, in particular to an extraterrestrial surface environment comprehensive simulation device. BACKGROUND

[0002] With the deepening of human space exploration, the importance of simulating extraterrestrial surface environment to study planetary science, life science, space resource development technology and test spacecraft adaptability is increasingly prominent. Among them, the extraterrestrial surface environment is the core research goal of understanding and exploring the formation and evolution history of extraterrestrial bodies and realizing deep space exploration mission engineering. At present, with the increase of the difficulty and quantity of deep space exploration missions, the demand for high-fidelity comprehensive simulation of extraterrestrial surface environment is also increasing. In traditional laboratory simulation research, due to the limitation of technology, research target and other factors, only a single environmental factor is generally simulated to verify its influence on the specific research target. Due to the lack of comprehensive simulation devices and technologies for the complex environment of extraterrestrial bodies including vacuum, temperature, space weathering process and the like in current research, the understanding of the surface characteristics of future target exploration bodies is greatly hindered, the realization of engineering and scientific goals is affected, and the research development of related fields is restricted. SUMMARY

[0003] The purpose of the present application is to provide an extraterrestrial surface environment comprehensive simulation device to solve the problems existing in the prior art, which can simulate the vacuum environment, high and low temperature environment and space weathering modification process represented by micro-meteorite impact on the surface of extraterrestrial bodies, and can perform in-situ characterization while simulating the extraterrestrial surface environment, thereby truly reflecting the interaction effect of the extraterrestrial surface and improving the practicality and research accuracy of the experiment.

[0004] To achieve the above purpose, the present application provides the following scheme:

[0005] The present application provides an extraterrestrial surface environment comprehensive simulation device, comprising:

[0006] A vacuum chamber, after being evacuated or filled with a specific atmosphere, can be used to simulate the vacuum environment or atmospheric composition of an extraterrestrial surface. The sidewall of the vacuum chamber, or other preferred locations, are equipped with expansion interfaces, observation windows, and reserved interfaces. The specific locations of these interfaces are not limited and can be rationally selected according to actual experimental needs. Pulsed laser deposition systems and other equipment are introduced through the reserved interfaces or observation windows to simulate space weathering processes, such as micrometeorite impacts. Characterization instruments can be connected to the reserved interfaces to obtain in-situ changes in the relevant characteristics of the test samples. The expansion interfaces can connect to other sensors as needed. These expansion interfaces include universal flange interfaces on the sidewall of the vacuum chamber, providing versatility and allowing connection to different in-situ testing instruments. This enables various in-situ testing experiments based on different experimental methods, allowing for in-situ characterization while comprehensively simulating the surface environment of extraterrestrial bodies.

[0007] A molecular pump, sealed and connected to one side of the vacuum chamber, is capable of evacuating the interior of the vacuum chamber to a set vacuum level, thereby accurately simulating the vacuum environment on the surface of an extraterrestrial body.

[0008] A temperature control system, connected to the stage, is used to adjust the temperature of the stage to the temperature value required to simulate the high-temperature or low-temperature environment on the surface of an extraterrestrial body.

[0009] The stage, located within the vacuum cavity, is used to carry test samples and simulate the changes in the physical properties of test samples under vacuum, high temperature, low temperature, and space weathering processes, represented by micrometeorite impacts, on the surface of extraterrestrial objects, thus achieving comprehensive simulation of the surface environment of extraterrestrial objects.

[0010] The drive device, connected to the stage, can control and adjust the position and angle of the stage within the vacuum chamber, thereby carrying test samples of different types and sizes, and simulating the state and physical property changes of different samples under vacuum, high and low temperature and atmospheric conditions on the surface of extraterrestrial bodies.

[0011] When the present application is used, the sample to be tested is placed on the sample stage, and then the vacuum cavity is evacuated, and when the preset vacuum degree is reached, the vacuum environment of the surface of the extraterrestrial body can be simulated; the temperature control system adjusts the temperature of the sample stage to reach the temperature value required by the simulation of the high and low temperature environments of the surface of the extraterrestrial body, and the pulsed laser deposition system and other devices are incident from the reserved interface or the observation window, and the pulsed laser is used to simulate the space weathering process represented by micro-meteorite impact, and then the state and physical property changes of the test sample in the simulated vacuum environment, high and low temperature environments and space weathering process represented by micro-meteorite impact can be observed through the observation window. The present application simulates the temperature and pressure conditions generated in the process of micro-meteorite impact by using pulsed laser, and the pulsed laser of a set wave band and pulse interval is incident into the vacuum cavity through the reserved interface or the observation window, so that the space weathering process represented by micro-meteorite impact of the test sample can be simulated.

[0012] Optionally, the driving device comprises a rotating shaft and a vacuum transmission mechanism, and the vacuum transmission mechanism is not limited in particular, and in one specific embodiment, a magnetic fluid seal transmission device can be used. The vacuum transmission mechanism is fixedly arranged on the side wall of one end of the vacuum cavity, one end of the rotating shaft is fixedly connected with the sample stage, and the other end of the rotating shaft penetrates the vacuum transmission mechanism. When the rotating shaft rotates and moves axially in the vacuum transmission mechanism, the sample stage can be driven to rotate and move axially synchronously in the vacuum cavity, so that it can be applied to test samples of different sizes and types, and the required test sample can be replaced through axial and radial movement. When the test sample is driven to move to different positions, in-situ testing instruments connected with the universal flange interface can be used to carry out in-situ testing experiments, so that in-situ characterization under comprehensive simulation conditions can be realized.

[0013] Optionally, the observation window comprises a flange opening fixedly arranged on the top of the vacuum cavity, and the observation window can also be arranged on the side wall or other preferred positions of the vacuum cavity, and the specific position of the observation window is not limited. A sealing layer is fixedly and sealingly arranged at the flange opening, and the sealing layer is made of transparent material. An image acquisition device is arranged outside the observation window, which can acquire images of the physical property changes of the test sample in the simulated test vacuum environment, high temperature environment, low temperature environment and space weathering process represented by micro-meteorite impact. The flange opening of the observation window can adopt a universal flange interface, so that it can match in-situ testing instruments after the sealing layer is removed, and in-situ experiments can be carried out, so that the simulation results can be in-situ characterized.

[0014] Optionally, the pre-reserved interface comprises a connecting flange sealingly arranged on the side wall or other part of the vacuum cavity, and a light-transmitting layer is sealingly arranged at the connecting flange, so that the pulsed laser emitted by the external pulsed laser deposition system can enter the vacuum cavity through the light-transmitting layer, so as to simulate the temperature and pressure conditions generated in the process of micro-meteorite impact, and then simulate the space weathering process represented by micro-meteorite impact.

[0015] Optionally, a vacuum quick-opening door is sealingly arranged on the side wall of the vacuum cavity away from the pre-reserved interface, so that the required test sample can be replaced.

[0016] Optionally, a vacuum electrical connector and a vacuum gauge are arranged on the top of the vacuum cavity, the vacuum gauge is used to test the vacuum degree in the vacuum cavity, so as to ensure that the simulated extraterrestrial celestial body surface vacuum environment is real and accurate, the vacuum cavity is provided with a vacuum transmission mechanism, and the side wall of the vacuum cavity is provided with a vacuum electrical connector; an optical temperature measurement window and a backup vacuum electrical connector are arranged at the position close to the pre-reserved interface of the vacuum cavity, the optical temperature measurement window can measure the surface temperature of the test sample after the pulsed laser is shot, so as to realize the collection of test data of the simulation of the space weathering process represented by micro-meteorite impact; the vacuum electrical connector is used for electrical connection with the equipment in the vacuum cavity, and the vacuum electrical connector is an electrical connection element used in a vacuum environment, and its main feature is that it can work in an environment without gas or with very little gas, so as to avoid the influence of gas on current transmission and ensure the stability and reliability of the circuit.

[0017] Optionally, a bottom plate is further arranged, the bottom plate is provided with a sliding rail, a trolley is connected to the bottom of the vacuum cavity through a support, the trolley is slidingly arranged on the sliding rail, and the vacuum cavity is driven to move to a set position, so as to facilitate external connection of different in-situ test instruments at different positions and development of in-situ test experiments.

[0018] Optionally, one end of the object table is fixedly connected to one end of the rotating shaft through a fixing block, a sample holder is fixedly arranged on the top plane of the object table, and the sample holder is used for fixedly placing a test sample.

[0019] Optionally, the temperature control system comprises a cooling pipeline and a temperature sensor fixed on the sample holder, the temperature sensor can collect the temperature value of the sample holder in real time, so that the operator can adjust the temperature control system according to the detected temperature value, so that the sample holder can reach the required temperature value faster; a groove is formed in the objective table to install the cooling pipeline or an integrated 3D printing cooling pipeline, when the cooling pipeline is made by 3D printing, the surface of the 3D printed structure needs to be milled flat to meet the test requirements, the groove shape can be serpentine, grid and the like, the cooling pipeline comprises a cooling pipe, the cooling pipe is connected with the cooling system through the joint on the side wall of the vacuum cavity, which is used to cool the sample table to the set temperature, simulate the low temperature environment of the required celestial body surface, the medium in the cooling pipe can be liquid nitrogen, refrigerant or other cooling working medium, the present application takes liquid nitrogen as an example, nitrogen gas or liquid nitrogen is used in the cooling pipe, compared with the traditional straight pipe structure, the curved structure of the cooling pipe prolongs the flow path of liquid nitrogen or nitrogen gas, increases the heat exchange time and improves the heat exchange effect, which can quickly exchange heat with the sample table, and then provide the required low temperature or high temperature environment for the sample on the sample table; a heater is fixed at the bottom of the objective table, which is used to heat the sample table to the set temperature, simulating the high temperature environment of the required celestial body surface.

[0020] The liquid nitrogen system comprises a liquid nitrogen storage device, which is respectively connected with a liquid phase joint and a gas phase joint, the liquid phase joint is connected with one end of the cooling pipe through a connecting pipe, and a low temperature electromagnetic valve is arranged between the liquid phase joint and the connecting pipe; the gas phase joint is connected with the cooling pipe through the connecting pipe after passing through the nitrogen gas heating device, a high temperature electromagnetic valve is arranged on the gas phase joint between the nitrogen gas heating device and the connecting pipe; one end of the cooling pipe is connected with the connecting pipe, and the other end is connected with a nitrogen gas exhaust port through an exhaust pipeline, by controlling the opening and closing of the low temperature electromagnetic valve and the high temperature electromagnetic valve, liquid nitrogen or heated nitrogen gas can be respectively introduced into the cooling pipe, and then the test sample can be cooled or heated, and the nitrogen gas exchanged with the sample holder is discharged through the nitrogen gas exhaust port; the low temperature electromagnetic valve, the high temperature electromagnetic valve and the nitrogen gas heating device are respectively connected with a control system, the control system is connected with a temperature sensor through a signal feedback loop, the temperature value of the sample holder can be sent to the control system and converted into an electric signal for analysis and processing by the control system, the control system can compare the temperature value of the sample holder with the preset value, and control the opening and closing of the low temperature electromagnetic valve, the high temperature electromagnetic valve and the nitrogen gas heating device according to the difference between the actual temperature value and the preset value, so as to automatically heat or cool the sample holder, so that the control system can automatically adjust the temperature of the sample holder as needed, and realize the automatic rise and fall of the temperature of the sample holder.

[0021] Optionally, the vacuum cavity side wall is fixedly sealed with an atmosphere joint, and a specific atmosphere can be introduced into the vacuum cavity through the atmosphere joint.

[0022] The present application has the following technical effects compared with the prior art:

[0023] The vacuum cavity side wall is provided with a plurality of universal flange interfaces, which are universal and can be externally connected to different in-situ testing instruments, and are convenient to customize according to the use requirements, and the size of the observation window and the number and size of the flange interfaces can be customized. Nitrogen or liquid nitrogen is delivered to the cooling pipe through heating, and heat exchange is performed with the sample holder having heat conduction and heat conduction properties, thereby creating a required low or high temperature environment for the sample, thereby simulating the high or low temperature environment of the surface of an extraterrestrial celestial body. The vacuum cavity can be evacuated by a molecular pump to ensure that it can simulate the required vacuum environment of the surface of an extraterrestrial celestial body, and the vacuum degree is high. The pulse laser deposition system and other equipment can be incident through the reserved interface or the observation window. The temperature and pressure conditions generated during the micro-meteorite impact process can be simulated by using pulse laser, and the space weathering process represented by micro-meteorite impact on the surface of an extraterrestrial celestial body can be simulated. Thus, the present application can simultaneously or separately simulate the high or low temperature environment, the vacuum environment and the space weathering process represented by micro-meteorite impact on the surface of an extraterrestrial celestial body, and can carry out in-situ experiments and in-situ characterization while simulating comprehensively, which is convenient for accurate testing of test samples under the simulation of the surface environment of an extraterrestrial celestial body. BRIEF DESCRIPTION OF DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0025] Figure 1 It is a structural schematic diagram of the extraterrestrial celestial body surface environment comprehensive simulation device of the present application.

[0026] Figure 2 It is another angle structural schematic diagram of the extraterrestrial celestial body surface environment comprehensive simulation device of the present application.

[0027] Figure 3 It is a structural schematic diagram of the vacuum cavity of the extraterrestrial celestial body surface environment comprehensive simulation device of the present application.

[0028] Figure 4 It is the schematic view of the carrier table structure of the extraterrestrial object surface environment comprehensive simulation device of the present application.

[0029] Figure 5 It is the schematic view of the cooling pipe structure of the extraterrestrial object surface environment comprehensive simulation device of the present application.

[0030] In the figure: 1-vacuum cavity, 2-molecular pump, 3-observation window, 4-vacuum gauge, 5-vacuum electrical connector, 6-reserved interface, 7-optical temperature measurement window, 8-backup vacuum electrical connector, 9-vacuum quick opening door, 10-bottom plate, 11-vacuum transmission mechanism, 12-rotating shaft, 13-liquid nitrogen connector, 14-atmosphere connector, 15-carrier table, 16-sample holder, 17-fixing block, 18-heater, 19-temperature sensor, 20-test sample, 21-cooling pipe. DETAILED DESCRIPTION

[0031] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the present application.

[0032] The purpose of the present application is to provide an extraterrestrial object surface environment comprehensive simulation device to solve the problems existing in the prior art, which can simulate the vacuum environment, high and low temperature environment and space weathering process represented by micro-meteorite impact on the surface of extraterrestrial objects, and can perform in-situ characterization while simulating the extraterrestrial object surface environment, thereby truly reflecting the interaction effect on the surface of extraterrestrial objects and improving the practicality and research accuracy of the experiment.

[0033] In order to make the above-mentioned purposes, features and advantages of the present application more obvious and easy to understand, the present application will be further described in detail below with reference to the drawings and specific embodiments.

[0034] As Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5As shown, the present application provides a kind of extraterrestrial body surface environment comprehensive simulation device, including the vacuum cavity 1 being arranged on the bottom plate 10, the side wall of vacuum cavity 1 is connected with molecular pump 2, molecular pump 2 is started, can form vacuum test environment inside vacuum cavity 1 by the suction of molecular pump 2, in turn can simulate the vacuum environment of the surface of the required extraterrestrial body, its internal pressure can be set as required, vacuum cavity 1 side wall or other preferred position is respectively provided with expansion interface, observation window 3 and reserved interface 6, expansion interface is all flange interface type structure, can realize sealing and external other sensor, flange interface is standard, in later research, other in-situ testing instrument can be accessed, such as dielectric constant, conductivity test, these test results are the key influence parameters in deep space exploration mission.In a specific embodiment, vacuum cavity 1 is sealed and provided with vacuum quick opening door 9 on the side wall away from the side of reserved interface 6, in other preferred embodiments, the specific position of reserved interface 6 and vacuum quick opening door 9 is not limited, can be set according to actual test demand;Vacuum quick opening door 9 is closed usually, for ensuring the vacuum sealed environment in vacuum cavity 1, when the test sample 20 needs to be replaced, it can be quickly opened, and test sample 20 is installed on the object table 15 from here, observation window 3 includes the flange mouth being fixedly arranged on the top of vacuum cavity 1 or other preferred position, the flange mouth is fixedly and sealingly provided with closed layer, closed layer is made of transparent material, so that by setting camera structure outside observation window 3, the state change data of test sample 20 in the test process in vacuum cavity 1 can be collected and observed flexibly and accurately, also can be observed by staff from observation window 3 Place the eyes of internal test sample 20, it is convenient to be more accurate when replacing or adjusting the position of test sample 20, can be observed, replace or adjust the position of test sample 20, higher accuracy;Observation window can collect the physical property change image of test sample in the process of simulating test extraterrestrial body surface vacuum environment, high temperature environment, low temperature environment and space weathering process represented by micro meteorite impact in real time, observation window can also use general flange structure, after removing closed layer, it can also match in-situ testing instrument, carry out a variety of in-situ experiments, and in-situ characterization is carried out to simulation results.

[0035] The reserved interface 6 comprises a connecting flange which is sealingly arranged on the side wall of the vacuum cavity 1 or other preferred positions, and a light-transmitting layer is sealingly arranged at the connecting flange, and the pulsed laser emitted by the external pulsed laser deposition system and other equipment can pass through the light-transmitting layer and enter the vacuum cavity 1, and the pulsed laser is used to simulate the temperature and pressure conditions generated in the micro-meteorite impact process, the pulsed laser incident from the reserved interface 6 is used to simulate the space weathering process represented by the micro-meteorite impact, and the frequency of the pulsed laser can be adjusted as required; a sample stage 15 is arranged in the vacuum cavity 1 and used to carry the test sample 20; the sample stage 15 is connected with a driving device, the position and angle of the sample stage 15 in the vacuum cavity 1 can be controlled and adjusted, the test sample 20 can be replaced and different experiments can be performed on the test sample 20; a temperature control system is arranged at the sample stage 15 and used to adjust the temperature at the sample stage 15, and since the sample stage 15 has a heat conduction function, the extraterrestrial celestial body high and low temperature environment simulation at the test sample 20 can be realized.

[0036] An atmosphere joint 14 is fixedly and sealingly arranged on the side wall of the vacuum cavity 1, and the required gas can be introduced into the vacuum cavity 1 through the atmosphere joint 14, and when a specific atmospheric composition environment needs to be simulated, the gas of a set type and pressure can be introduced into the vacuum cavity 1 through the atmosphere joint 14, so that the atmospheric composition environment of the set type atmosphere state on the surface of the required extraterrestrial celestial body can be simulated.

[0037] In use, the test sample is placed on the sample stage 15, and then the vacuum cavity 1 is evacuated, and when the preset vacuum degree is reached, the vacuum environment on the surface of the extraterrestrial celestial body can be simulated, the temperature of the sample stage 15 is adjusted by the temperature control system, so that the high and low temperature values required for the test can be reached, the high and low temperature vacuum environment on the surface of the extraterrestrial celestial body can be simulated, and then the test sample 20 can be observed through the observation window 3, the reserved interface 6 is connected to the characterization instrument to obtain the change of the related characteristics of the test sample in situ, and the state and physical property change of the test sample in the simulated vacuum environment, high and low temperature environment, atmosphere environment and space weathering process represented by the micro-meteorite impact on the surface of the extraterrestrial celestial body are verified; since the temperature and pressure will change when the micro-meteorite impacts the surface of the extraterrestrial celestial body, the pulsed laser is used to replace the light-thermal environment when the micro-meteorite impacts, the pulsed laser deposition system and other equipment emit the pulsed laser of a set frequency into the vacuum cavity 1 through the reserved interface 6 or the observation window 3, the space weathering process represented by the micro-meteorite impact is simulated, the temperature and pressure conditions generated in the micro-meteorite impact process are simulated by using the pulsed laser, the micro-meteorite impact environment simulation of the test sample 20 is realized, and the simulation test of the space weathering modification process on the surface of the extraterrestrial celestial body is realized.

[0038] In order to flexibly adjust the sample angle and position at the stage 15, without damaging the sealing effect of the vacuum cavity 1, the drive device of the application is unique in that a rotating shaft 12 and a vacuum transmission mechanism 11 are arranged, the vacuum transmission mechanism 11 is fixedly arranged on the side wall of one end of the vacuum cavity 1, one end of the stage 15 is fixedly connected with one end of the rotating shaft 12 through a fixed block 17, a sample holder 16 is fixedly arranged on the top plane of the stage 15, the sample holder 16 is used for fixing and placing a test sample 20, the other end of the rotating shaft 12 penetrates through the vacuum transmission mechanism 11 and is externally connected with a driving part; when the rotating shaft 12 rotates and moves axially in the vacuum transmission mechanism 11, the stage 15 can be driven to rotate and move axially synchronously in the vacuum cavity 1, so that it can be suitable for different sizes and types of test samples, and through the axial and radial movement, the required test sample can be replaced, and when the test sample is driven to move to the set position, the in-situ testing instrument externally connected with the universal flange interface can be matched to carry out in-situ testing experiment. The vacuum transmission mechanism 11 in the embodiment adopts a magnetic fluid sealing transmission device, which is a device for realizing non-contact transmission of driving energy by using magnetic field principle, and is particularly suitable for occasions that need to be completely isolated, such as preventing medium leakage, eliminating wear, isolating heat conduction, avoiding cross contamination or working in extreme environments (such as high pressure, high temperature, low temperature, corrosive medium).

[0039] Further preferably, a vacuum electrical connector 5 and a vacuum gauge 4 are arranged on the top of the vacuum cavity 1, the vacuum gauge is used for testing the vacuum degree in the vacuum cavity 1, so as to ensure that the simulated extraterrestrial surface vacuum environment is real and accurate, the side wall of the vacuum cavity 1 provided with the vacuum transmission mechanism 11 is also provided with a vacuum electrical connector 5, which is used for electrical connection with the equipment in the vacuum cavity 1; an optical temperature measurement window 7 and a backup vacuum electrical connector 8 are arranged near the reserved interface 6 of the vacuum cavity 1, the optical temperature measurement window 7 can measure the surface temperature of the test sample after the pulsed laser is shot, so as to realize the collection of test data in the simulation of the space weathering process represented by micro-meteorite impact.

[0040] The vacuum cavity 1 is fixedly arranged on the bottom plate 10, and the position of the test sample 20 in the vacuum cavity 1 is adjusted through the axial movement of the rotating shaft 12, in another preferred embodiment, a slide rail can be arranged on the bottom plate 10, the length direction of the slide rail is arranged in parallel with the axial direction of the rotating shaft 12, a trolley is connected to the bottom of the vacuum cavity 1 through a support, and the trolley is slidably arranged on the slide rail, so that the rotating motor externally connected with the rotating shaft 12 is only responsible for rotating adjustment of the angle of the stage 15, and through the movement of the trolley on the slide rail, the vacuum cavity 1 is driven to move along the axial direction of the rotating shaft 12, so as to realize adjustment of the position of the test sample 20 in the vacuum cavity 1.

[0041] In a preferred embodiment of the present application, the temperature control system comprises a cooling pipeline and a temperature sensor 19 fixed on the sample holder 16, which can collect the temperature of the sample holder 16 in real time and transmit the temperature value to the control system, so that the operator can adjust the working mode of the temperature control system according to the displayed temperature value, so that the sample holder 16 can reach the required temperature value faster. The sample holder 16 is a heat-conducting structure, which is provided with a plurality of through holes for facilitating heat conduction. The object table 15 is provided with a groove, which can be in the shape of a snake or a grid, so that the contact area is larger, the cooling effect is better, the cooling efficiency is higher, and the required temperature of the simulated extraterrestrial surface low-temperature environment can be quickly realized. The cooling pipeline comprises a cooling pipe 21, which is connected to the cooling system through the joint on the side wall of the vacuum cavity 1. In this embodiment, the joint is a liquid nitrogen joint 13, and the cooling system is a liquid nitrogen system. Nitrogen or liquid nitrogen is used in the cooling pipe 21. Compared with the traditional straight pipe structure, the serpentine bending structure of the cooling pipe 21 prolongs the flow path of the liquid nitrogen or nitrogen, increases the heat exchange time, improves the heat exchange effect, and can quickly exchange heat with the sample table, thereby providing the required low-temperature or high-temperature environment for the sample on the sample table. The heater 18 is fixed at the bottom of the object table 15, which can also adjust the temperature of the test sample 20. In other embodiments, a GM machine cold head can be used to replace the cooling pipe 21, which can also realize the simulation of the low-temperature environment of the test sample 20.

[0042] The liquid nitrogen system comprises a liquid nitrogen storage device, which is respectively connected with a liquid phase joint and a gas phase joint. The liquid phase joint is connected with one end of the cooling pipe 21 through a connecting pipe, and a low-temperature electromagnetic valve is arranged between the liquid phase joint and the connecting pipe. The gas phase joint is connected with the cooling pipe 21 through a connecting pipe after passing through a nitrogen heating device, 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 cooling pipe 21 is connected with the connecting pipe, and the other end is connected with a nitrogen exhaust port through an exhaust pipeline. By controlling the opening and closing of the low-temperature electromagnetic valve and the high-temperature electromagnetic valve, liquid nitrogen or heated nitrogen can be respectively introduced into the cooling pipe 21, thereby cooling or heating the test sample, and the nitrogen exchanged with the sample holder 16 is discharged through the nitrogen exhaust port. The low-temperature electromagnetic valve, the high-temperature electromagnetic valve and the nitrogen heating device are respectively connected with the control system. The control system is connected with the temperature sensor 19 through a signal feedback loop, which can send the temperature value of the sample holder 16 to the control system and convert it into an electric signal for analysis and processing by the control system. The control system can compare the temperature value of the sample holder 16 with the preset value, and control the opening and closing of the low-temperature electromagnetic valve, the high-temperature electromagnetic valve and the nitrogen heating device according to the difference between the actual temperature value and the preset value, so as to automatically heat or cool the sample holder 16. Thus, the control system can automatically adjust the temperature of the sample holder 16 according to the need, and realize the automatic rise and fall of the temperature of the sample holder 16.

[0043] The present application can simultaneously or separately simulate the high and low temperature environment, vacuum environment, atmospheric composition environment and space weathering process represented by micro-meteorite impact on the surface of extraterrestrial objects, and can carry out in-situ experiments and in-situ characterization while comprehensively simulating, so as to facilitate accurate testing of test samples under the extraterrestrial object surface environment simulation.

[0044] The principle and implementation mode of the present application are described by using specific examples in the present application, and the above examples are only used to help understand the method and core idea of the present application; meanwhile, for those skilled in the art, according to the idea of the present application, the specific implementation mode and application range will be changed. In view of the above, the content of the specification should not be understood as a limitation of the present application.

Claims

1. An apparatus for comprehensive simulation of surface environment of extraterrestrial bodies, characterized in that, The device comprises: a vacuum chamber, which is capable of simulating the vacuum environment or atmospheric composition of the surface of extraterrestrial bodies after being internally evacuated or filled with a specific atmosphere; and a side wall of the vacuum chamber is respectively provided with an extension interface, an observation window and a reserved interface, a pulsed laser deposition system is incident from the reserved interface or the observation window to simulate the space weathering process represented by micro-meteorite impact; a molecular pump, which is in sealed communication with one side of the vacuum chamber and is capable of evacuating the interior of the vacuum chamber to a set vacuum degree to simulate the vacuum environment of the surface of extraterrestrial bodies; a sample stage, which is arranged in the vacuum chamber and is used for carrying a test sample and simulating the physical property changes of the test sample in the vacuum environment, high-temperature environment, low-temperature environment and space weathering process represented by micro-meteorite impact on the surface of extraterrestrial bodies; a temperature control system, which is in communication with the sample stage and is used for adjusting the temperature of the sample stage to a temperature value required for simulating the high-temperature or low-temperature environment on the surface of extraterrestrial bodies; a driving device, which is connected with the sample stage and is capable of controlling and adjusting the position and angle of the sample stage in the vacuum chamber, thereby carrying different kinds and sizes of test samples; the reserved interface comprises a connecting flange which is sealingly arranged on the side wall or other parts of the vacuum chamber, a light-transmitting layer is sealingly arranged at the connecting flange, and the pulsed laser emitted by an external pulsed laser deposition system can pass through the light-transmitting layer and enter the vacuum chamber, thereby simulating the temperature and pressure conditions in the process of micro-meteorite impact and further simulating the space weathering process represented by micro-meteorite impact; the frequency of the pulsed laser can be adjusted as required.

2. The extraterrestrial body surface environment integrated simulation device according to claim 1, characterized by, the driving device comprises a rotating shaft and a vacuum transmission mechanism, the vacuum transmission mechanism is fixedly arranged on the side wall of one end of the vacuum chamber, one end of the rotating shaft is fixedly connected with the sample stage, and the other end of the rotating shaft penetrates through the vacuum transmission mechanism; when the rotating shaft rotates and moves axially in the vacuum transmission mechanism, the sample stage can be synchronously rotated and moved axially in the vacuum chamber.

3. The extraterrestrial surface environment integrated simulation device according to claim 1, wherein, the observation window comprises a general flange interface which is fixedly arranged on the top or side wall of the vacuum chamber, a sealingly closed layer is fixedly arranged at the general flange interface, and the closed layer is made of transparent material; an image acquisition device is arranged outside the observation window and is capable of acquiring images of the physical property changes of the test sample in the simulated test of the vacuum environment, high-temperature environment, low-temperature environment and space weathering process represented by micro-meteorite impact on the surface of extraterrestrial bodies in real time; after the closed layer is removed from the observation window, the in-situ test instrument can be matched to characterize the simulation results in-situ.

4. The extraterrestrial surface environment integrated simulation device according to claim 1, wherein, a vacuum quick-opening door is sealingly arranged on the side wall of the vacuum chamber away from the reserved interface, and the test sample can be quickly replaced.

5. The extraterrestrial surface environment integrated simulation device according to claim 2, wherein, The vacuum cavity top is provided with a vacuum electric connector and a vacuum gauge, the vacuum gauge is used for testing the vacuum degree in the vacuum cavity; the vacuum cavity is provided with a vacuum transmission mechanism, the side wall of the vacuum cavity is provided with a vacuum electric connector; the vacuum cavity is provided with an optical temperature measurement window and a spare vacuum electric connector near the reserved interface position, the optical temperature measurement window can measure the surface temperature of the test sample after the pulse laser is shot.

6. The extraterrestrial surface environment simulation facility of claim 1, wherein, A bottom plate is further included, the bottom plate is provided with a slide rail, a trolley is connected to the bottom of the vacuum cavity through a support, the trolley is slidingly arranged on the slide rail, and the vacuum cavity is driven to move to a set position.

7. The extraterrestrial surface environment simulation facility of claim 2, wherein, One end of the object table is fixedly connected with one end of the rotating shaft through a fixing block, a sample holder is fixedly arranged on the top plane of the object table, and the sample holder is used for fixedly placing a test sample.

8. The extraterrestrial surface environment integrated simulation device according to claim 7, wherein, The temperature control system includes a cooling pipeline and a temperature sensor fixedly arranged on the sample holder, can collect temperature values of the sample holder in real time, a groove is arranged in the object table to install a cooling pipeline or an integrated 3D printing cooling pipeline, the cooling pipeline includes a cooling pipe, the cooling pipe is connected with a cooling system through a connector on the side wall of the vacuum cavity, is used for cooling the sample table to a set temperature, and simulates a low-temperature environment of a required extraterrestrial body surface; a heater is fixedly arranged at the bottom of the object table, is used for heating the sample table to a set temperature, and simulates a high-temperature environment of a required extraterrestrial body surface.

9. The extraterrestrial surface environment simulation facility of claim 1, wherein, An atmosphere connector is fixedly and sealingly arranged on the side wall of the vacuum cavity, the atmosphere connector is connected with a gas generating device through a pipeline, and a specific atmosphere can be introduced into the vacuum cavity through the atmosphere connector to simulate a required atmospheric composition of an extraterrestrial body surface.

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