Device for simulating space weathering effect of lunar rock and simulation method thereof

Abstract

The invention discloses a device for simulating the space weathering effect of lunar rock and a simulation method thereof.The device for simulating the space weathering effect of lunar rock comprises a vacuum chamber, a carrying table, a vacuum degree control module, a temperature control module, a pulse laser module, a high-energy ion beam module, a microscope module and a control module; the interior of the vacuum cabin is hollow to form a vacuum chamber; the carrying table is arranged in the vacuum cabin; the vacuum degree control module is arranged on the vacuum cabin; the temperature control module, the pulse laser module and the high-energy ion beam module are all connected with the vacuum chamber; the microscope module is arranged in the vacuum cabin and directly faces the carrying table; the control module is electrically connected with the vacuum degree control module, the temperature control module, the pulse laser module and the high-energy ion beam module. A plurality of modules are integrated and accurately controlled to simulate the space weathering action on the lunar rock, so that a scene under the combined action of a plurality of space weathering factors is realized, and the authenticity of a ground simulation test is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of surface experimental simulation of lunar space weathering, and in particular to a device for simulating lunar space weathering of lunar rocks and a simulation method thereof. Background Art

[0002] Space weathering refers to the combined effects of various physical and chemical processes on the surface of a planet or a small celestial body due to long-term exposure to space in an atmosphereless or weak atmosphere environment, and the impact of micrometeorites, cosmic rays, solar wind radiation and other space environments. Space weathering changes the physical and optical properties of materials on the surface of celestial bodies, and these changes have an important impact on remote sensing detection and planetary science research. Since humans began to explore the space environment, a large number of studies on space weathering have been carried out. For the moon, the closest natural satellite to the earth, humans have obtained a limited number of samples and limited sampling locations. There are certain limitations in space weathering research based on existing samples and remote sensing data, and it is difficult to fully represent the weathering characteristics of different areas on the moon. At the same time, the resolution and accuracy of remote sensing technology are limited, and it is impossible to deeply detect changes below the surface of the moon. In order to make up for these shortcomings, researchers have gradually turned to ground simulation experiments, reproducing the lunar environment in the laboratory, and systematically studying the space weathering of lunar surface materials, especially lunar rocks.

[0003] However, the level of simulation of space weathering of lunar rocks in existing laboratories is limited. Existing technologies usually use pulsed laser technology alone to simulate micrometeorite impacts, mainly simulating the instantaneous high temperature effect of meteorite impact through laser heating, which mainly induces physical changes through thermal effects to cause local melting and vaporization. This simulation method is usually carried out for special simulation tasks, and is one-sided in restoring the comprehensive effects of lunar space weathering. The simulation effect it produces is significantly different from the situation where multiple factors work together in the actual lunar environment. Therefore, the authenticity of the research results is insufficient and the reliability of the research data is insufficient.

[0004] Therefore, the prior art still needs to be improved and developed. Summary of the invention

[0005] In view of the above-mentioned deficiencies in the prior art, the purpose of the present invention is to provide a device for simulating the space weathering of lunar rocks and a simulation method thereof, aiming to solve the problem that the existing simulation devices only reproduce a single space weathering factor but do not take into account the comprehensive space weathering effects on lunar rocks, the simulation effect is far from the actual situation, the authenticity is insufficient, and the research results are not reliable enough.

[0006] The technical solution of the present invention is as follows:

[0007] A device for simulating the space weathering of lunar rocks, comprising a vacuum chamber, a carrier, a vacuum control module, a temperature control module, a pulse laser module, a high-energy ion beam module, a microscope module and a control module, wherein the vacuum chamber is hollow inside to form a vacuum chamber; the carrier is arranged in the vacuum chamber for placing samples; the vacuum control module is arranged on the vacuum chamber for collecting vacuum data in the vacuum chamber and controlling the vacuum degree; the temperature control module is connected to the vacuum chamber for collecting temperature data in the vacuum chamber and adjusting the temperature; the pulse laser module is connected to the vacuum chamber for emitting laser toward the carrier; the high-energy ion beam module is connected to the vacuum chamber for emitting high-energy ion beam toward the carrier; the microscope module is arranged in the vacuum chamber and faces the carrier; the control module is electrically connected to the vacuum control module, the temperature control module, the pulse laser module and the high-energy ion beam module.

[0008] The device for simulating the space weathering of lunar rocks is characterized in that an air hole is provided on the side wall of the vacuum chamber; the vacuum control module comprises a three-way pipeline, a vacuum gauge, an air inlet pipeline, an air inlet valve, an air outlet pipeline, an air outlet valve and a vacuum pump, one port of the three-way pipeline is inserted in the air hole, and the other two ports are respectively an air inlet port and an air outlet port; the vacuum gauge is arranged on the three-way pipeline for monitoring the vacuum degree; the air inlet pipeline is connected to the air inlet port; the air inlet valve is arranged on the air inlet pipeline for opening or closing the air inlet pipeline; the air outlet pipeline is connected to the air outlet port; the air outlet valve is arranged on the air outlet pipeline for opening or closing the air outlet pipeline; the vacuum pump is arranged on the air outlet pipeline for sucking the gas in the vacuum chamber; the vacuum gauge, the air inlet valve, the air outlet valve and the vacuum pump are all electrically connected to the control module.

[0009] The device for simulating space weathering of lunar rocks, wherein the top surface of the carrier is a bearing surface for placing the sample; a first channel and a second channel extending to the bearing surface are formed in the carrier, and the first channel and the second channel are cross-arranged; the temperature control module includes a heating component arranged in the first channel and a cooling component arranged in the second channel.

[0010] The device for simulating space weathering of lunar rocks, wherein the control module includes an environmental factor controller, an electric controller and a control terminal, the environmental factor controller is electrically connected to the vacuum control module and the temperature control module; the electric controller is electrically connected to the pulse laser module, the high-energy ion beam module and the microscope module; the control terminal is electrically connected to the environmental factor controller and the electric controller.

[0011] The device for simulating the space weathering of lunar rocks is characterized in that a first through hole is provided on the top of the vacuum chamber; the pulse laser module includes a laser, a laser transmission component, a laser emission cylinder and a focusing mirror, and the laser is electrically connected to the control module; the laser transmission component is connected to the vacuum chamber; and the laser transmission component is connected to the laser, and is used to guide the laser emitted by the laser to the first through hole; the laser emission cylinder is rotatably arranged on the inner wall of the vacuum chamber; one end of the laser emission cylinder is connected to the first through hole, and the other end faces the carrier; the focusing mirror is arranged on the end of the laser emission cylinder facing the carrier, and is used to focus the laser and adjust the spot size.

[0012] The device for simulating space weathering of lunar rocks, wherein the laser is a neodymium-doped yttrium aluminum garnet laser.

[0013] The device for simulating the space weathering of lunar rocks is characterized in that a second through hole is provided on the top of the vacuum chamber; the high-energy ion beam module includes an ion beam generator, an ion beam barrel, and an ion beam gun, wherein the ion beam generator is electrically connected to the control module and is disposed on the outer wall of the vacuum chamber to generate a high-energy ion beam toward the second through hole; the ion beam barrel can be rotatably disposed on the inner wall of the vacuum chamber; one end of the ion beam barrel is connected to the second through hole, and the other end faces the carrier; the ion beam gun is disposed on one end of the ion beam barrel facing the carrier to control the direction and distribution of the high-energy ion beam.

[0014] The present application also discloses a simulation method for the device for simulating space weathering of lunar rocks as described above, which comprises:

[0015] Load the sample onto the stage, then close the vacuum chamber, and evacuate the vacuum chamber through the vacuum control module until the vacuum degree of the vacuum chamber reaches a preset vacuum degree;

[0016] Starting the temperature control module to adjust the temperature of the vacuum chamber to a preset temperature and maintain a constant temperature;

[0017] Under the microscope field of view, adjust the pulse laser module and the high-energy ion beam module to focus together on the area to be bombarded on the sample;

[0018] Determining a test path and a test time based on the area to be bombarded, the bombardment energy of the pulse laser module, and the bombardment energy of the high-energy ion beam module;

[0019] Starting the pulse laser module and the high-energy ion beam module, repeating the bombardment test multiple times along the test path, and recording the bombardment time;

[0020] When the bombardment time reaches the test time, the pulse laser module, the high energy ion beam module and the temperature control module are turned off; the temperature in the vacuum chamber is waited to reach room temperature, the vacuum chamber is opened, the sample is taken out, and the test is completed.

[0021] The simulation method of the device for simulating space weathering of lunar rocks, wherein before the step of starting the pulse laser module and the high-energy ion beam module, repeating multiple bombardment tests along the test path, and recording the bombardment time, further comprises:

[0022] Preheating the high energy ion beam module and the pulse laser module; wherein the preheating time of the high energy ion beam module is 30-60 minutes, and the preheating time of the pulse laser module is 5-10 minutes.

[0023] The simulation method of the device for simulating the space weathering of lunar rocks, wherein the preset vacuum degree is less than or equal to 10 -6 Pa.

[0024] Compared with the prior art, the embodiments of the present invention have the following advantages:

[0025] The device for simulating the space weathering of lunar rocks disclosed in the present invention forms a closed vacuum chamber in a vacuum cabin, and then controls environmental factors by means of vacuuming and temperature adjustment, so that the surrounding area of ​​the sample on the carrier is close to the space environment, and then the sample is simultaneously bombarded with scanning lasers and ion beams under the perspective of a microscope, thereby simulating the combined effects of environmental factors such as micrometeor impacts, cosmic rays, and solar wind radiation in space, thereby achieving a comprehensive simulation of the scene where multiple factors work together, and more realistically restoring the effect of space weathering, so as to increase the authenticity of the test results, improve the reliability of the test data, and facilitate research and exploration of the impact of the space environment on materials. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0027] Figure 1 It is a schematic diagram of the structure of the device for simulating the space weathering of lunar rocks in the present invention;

[0028] Figure 2 It is a structural schematic diagram of the vacuum control module in the present invention;

[0029] Figure 3Another schematic diagram of the structure of the device for simulating the space weathering of lunar rocks in the present invention;

[0030] Figure 4 A schematic diagram of the optical path of a part of the structure of the device for simulating the space weathering of lunar rocks in the present invention;

[0031] Figure 5 It is a schematic diagram of the structure in the vacuum chamber of the present invention;

[0032] Figure 6 It is a structural schematic diagram of the environmental factor controller in the present invention;

[0033] Figure 7 The present invention is a flow chart of the simulation method of the device for simulating the space weathering of lunar rocks.

[0034] Among them, 10, vacuum chamber; 11, vacuum chamber; 20, carrier; 21, bearing surface; 30, vacuum control module; 31, three-way pipe; 32, vacuum gauge; 33, air inlet pipe; 34, air inlet valve; 35, air outlet pipe; 36, air outlet valve; 37, vacuum pump; 40, temperature control module; 41, heating component; 42, cooling component; 50, pulse laser module; 51, laser; 52, laser transmission component; 53, laser emission cylinder; 54, focusing mirror; 60, high-energy ion beam module; 61, ion beam generating component; 62, ion beam cylinder; 63, ion beam gun; 70, microscope module; 80, control module; 81, environmental factor controller; 811, control knob; 812, indicator bar; 813, display screen; 82, electric controller; 83, control terminal. DETAILED DESCRIPTION

[0035] In order to enable those skilled in the art to better understand the scheme of the present invention, the technical scheme in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0036] See also Figure 1 In one embodiment of the present invention application, a device for simulating space weathering of lunar rocks is disclosed, which includes a vacuum chamber 10, a carrier 20, a vacuum control module 30, a temperature control module 40, a pulse laser module 50, a high-energy ion beam module 60, a microscope module 70 and a control module 80. The interior of the vacuum chamber 10 is hollow to form a vacuum chamber 11; the carrier 20 is arranged in the vacuum chamber 10 for placing samples.

[0037] The device for simulating the space weathering of lunar rocks disclosed in this embodiment forms a closed vacuum chamber 11 in a vacuum cabin 10, and controls environmental factors by means of vacuuming and temperature adjustment, so that the surroundings of the sample on the carrier 20 are close to the space environment.

[0038] During the experiment, the samples were bombarded with scanning lasers and ion beams under the perspective of a microscope. The advantages of starting them at the same time are: 1. The ion beam provides implantation and sputtering effects of charged particles, and the pulsed laser simulates the instantaneous heating effect of high-energy radiation, thereby more fully reproducing the space weathering effect; 2. The instantaneous high temperature of the laser can change the electrical and optical properties of the material, making it easier for the ion beam to implant and react deeply with the material, and can more realistically reproduce the changes in the lunar surface and rocks affected by space weathering; 3. Laser heating will reduce the adhesion energy on the surface of the material, making the sputtering effect caused by the ion beam more obvious, which is particularly important when simulating surface erosion caused by solar wind, and can more realistically reproduce the loss of materials due to charged particles and thermal effects in the space environment.

[0039] Specifically, the device for simulating the space weathering of lunar rocks disclosed in the present application can simulate the sputtering and secondary ionization in space weathering to produce the effect of ion implantation; it can also simulate the physical changes and melting recrystallization phenomena on the surface of materials under instantaneous high temperature conditions. In general, the simulation of weathering effects such as micrometeor impacts, cosmic rays, and solar wind radiation in space, and the simulation of scenes where multiple factors work together can more realistically restore the effects of space weathering, so as to increase the authenticity of the test results, improve the reliability of the test data, and facilitate the study and exploration of the impact of the space environment on materials.

[0040] Specifically, the vacuum control module 30 is provided on the vacuum cabin 10, and is used to collect vacuum data and control the vacuum degree in the vacuum chamber 11; the temperature control module 40 is connected to the vacuum cabin 10, and is used to collect temperature data and adjust the temperature in the vacuum chamber 11. In this embodiment, the vacuum degree and temperature in the vacuum cabin 10 are monitored in real time, and the environmental influencing factors in the vacuum chamber 11 are precisely controlled, so as to simulate the space environment according to the test needs and improve the authenticity of the simulation effect.

[0041] Specifically, the pulse laser module 50 is connected to the vacuum chamber 10 and is used to emit laser toward the stage 20; the high-energy ion beam module 60 is connected to the vacuum chamber 10 and is used to emit high-energy ion beam toward the stage 20; the microscope module 70 is arranged in the vacuum chamber 10 and faces the stage 20. In the simulated space environment, the sample surface is bombarded by laser and the sample surface is bombarded by high-energy ion beam, thereby simulating the weathering effect of various particles in space, and achieving the effect of comprehensively simulating multiple influencing factors.

[0042] Specifically, the solar wind is mainly composed of hydrogen ions (H + ), so in this embodiment, a hydrogen ion source is used as the ion source of the high-energy ion beam module 60, which is ionized by plasma discharge, and is accelerated and focused by the electric field to complete beam regulation and energy control to bombard the sample target area, thereby improving the degree of simulation to be close to the real scene in the universe.

[0043] Specifically, the concept of maturity of lunar rock weathering products is still unclear. The content of nano-iron particles in the sample is usually used as an evaluation parameter. In the real cosmic environment, due to the complexity of the lunar environment and the simultaneous occurrence of multiple physical and chemical processes, when electromagnetic waves, charged ion bombardment and other effects occur simultaneously, indirect effects such as thermal effects or charge effects will occur. The charge effect is that ion beam irradiation will produce charge accumulation on the surface of the material, especially on insulating materials. Laser irradiation will also cause charge redistribution while heating, and even stimulate the diffusion of surface charges. This charge effect will affect the behavior of the ion beam on the surface and inside of the material. Obviously, the impact of two or more effects acting simultaneously cannot be tested in the prior art.

[0044] In other words, the effect of the simultaneous action of laser and ion beam in the actual lunar environment cannot be simulated by traditional single laser heating. The different test conditions will inevitably lead to a large gap between the authenticity and effectiveness of the test. Therefore, in order to restore the real weathering effect, it is necessary to consider all weathering factors at the same time.

[0045] In this embodiment, laser and high-energy ion beam are simultaneously used to bombard the test area of ​​the sample to simulate the combined effect of the two effects, as well as the indirect impact when they act simultaneously, thereby getting closer to the actual weathering environment of lunar rocks and increasing the realism of the simulation test.

[0046] During the test of this embodiment, observation can be performed through the microscope module 70, and information on the sample surface can be intuitively transmitted to achieve a visualization effect. The microscope module 70 can intuitively feedback changes in the top surface of the sample, and can adjust the bombardment position of the pulse laser module 50 and the high-energy ion beam module 60 under the microscope viewing angle, focusing the laser and the high-energy particle beam so as to accurately bombard the same position during the test, thereby improving the accuracy of the test and the effectiveness of the test results.

[0047] Specifically, the control module 80 is electrically connected to the vacuum control module 30, the temperature control module 40, the pulse laser module 50 and the high energy ion beam module 60. The control module 80 disclosed in this embodiment includes but is not limited to electronic devices such as integrated circuit boards, computers, smart tablets, and smart remote controllers. The control module 80 can transmit electrical signals through cables, or send communication signals through WiFi units, Bluetooth units, antenna units, etc., so as to transmit signals with the vacuum control module 30, the temperature control module 40, the pulse laser module 50 and the high energy ion beam module 60, etc., so as to accurately control the output values ​​of multiple factors, perform accurate simulation according to the test conditions, and further improve the authenticity of the simulation effect.

[0048] In summary, in this embodiment, a control module 80 that integrates multiple environmental factors is constructed to construct a simulation device for space weathering that can comprehensively control multiple factors, truly restoring the space environment, so that experiments can be carried out on the ground and systematic research can be conducted on the materials on the surface of celestial bodies. This is conducive to studying and understanding the impact of the space environment on materials, exploring the response mechanism of earth materials under space weathering, and contributing to the development of new materials and technologies.

[0049] For example, since the last century, humans have been continuously exploring space, and therefore have also carried out a large number of studies on space weathering on the surfaces of celestial bodies. Current research has revealed the evolution of lunar rock weathering products, color changes, and the reasons for reduced reflectivity by analyzing lunar samples and remote sensing data of the lunar surface.

[0050] However, due to the particularity of the space environment, the number of samples obtained is limited, and the sampling locations are limited, making it difficult to fully represent the weathering characteristics of different areas on the lunar surface. At the same time, the resolution and accuracy of remote sensing technology are limited, and it is impossible to deeply detect changes below the surface. At present, there are certain limitations in relying on existing samples and remote sensing data to conduct space weathering research, which is difficult to operate and the stability and reliability of the test results are difficult to guarantee. The device for simulating the space weathering of lunar rocks disclosed in this embodiment can be used to conduct simulation tests on the surface, thereby improving the reliability and stability of the test, which is conducive to systematic research on materials that can be developed, built, and used on the lunar surface.

[0051] Specifically, as an implementation of this embodiment, it is disclosed that the shape of the vacuum chamber 10 is a cube as a whole. The vacuum chamber 10 can be integrally formed by a mold, and is cast from metals such as stainless steel or aluminum alloy, and has sufficient hardness and strength, and has good sealing performance, and can maintain an ultra-high vacuum state. A hatch can be set on the side of the vacuum chamber 10, and the sample is placed through the hatch. After the hatch is closed, a sealed vacuum chamber 11 is formed in the vacuum chamber 10, and air is pumped through the vacuum control module 30, so that a vacuum environment can be gradually formed.

[0052] Specifically, as another implementation of this embodiment, it is disclosed that the stage 20 can be set as a metal stage, which is installed at the center of the bottom surface of the vacuum chamber 11. A clamp can be set in the central area of ​​the stage 20 to clamp the sample, or a groove can be set to limit the sample to improve the stability of the sample during the test; in addition, the stage 20 can also prevent the laser or high-energy ion beam from directly bombarding the inner wall of the vacuum chamber 10 to prevent damage or accidents. The stage 20 can be set as a mobile stage 20, which can be driven by electric means and can move horizontally and vertically to accurately adjust the position of the sample for convenient testing.

[0053] like Figure 1 and Figure 2 As shown, as another implementation of this embodiment, it is disclosed that an air hole is provided on the side wall of the vacuum chamber 10; the vacuum control module 30 includes a three-way pipe 31, a vacuum gauge 32, an air inlet pipe 33, an air inlet valve 34, an air outlet pipe 35, an air outlet valve 36 and a vacuum pump 37, one port of the three-way pipe 31 is inserted into the air hole, and the other two ports are the air inlet port and the air outlet port respectively.

[0054] During the test, the outlet valve 36 can be opened, the inlet valve 34 can be closed, and air can be continuously pumped through the vacuum pump 37. After the vacuum gauge 32 indicates that the target vacuum degree has been reached, the outlet valve 36 is closed to form a closed environment that meets the vacuum degree requirements in the vacuum chamber 10. After the test is completed, the inlet valve 34 is opened to gradually introduce gas from the inlet pipe 33 to release the vacuum state in the vacuum chamber 11, balance the air pressure inside and outside the cabin, and then the cabin door can be opened conveniently to take out the sample.

[0055] Specifically, the vacuum gauge 32 disclosed in the present embodiment is arranged on the three-way pipe 31, and is used to monitor the vacuum degree. The gas in and out of the vacuum chamber 11 passes through the three-way pipe 31. Therefore, by taking a reading through the vacuum gauge 32, the vacuum degree data in the vacuum chamber 11 can be obtained in real time and accurately. Specifically, the vacuum gauge 32 disclosed in the present embodiment includes but is not limited to the Pirani vacuum gauge 32. The Pirani vacuum gauge 32 is a type of thermal conduction vacuum gauge 32, which has a faster response speed and accurate measurement, so it can reflect the vacuum degree in the vacuum chamber 10 in real time, which is convenient for improving the control accuracy.

[0056] Specifically, the air inlet pipeline 33 is communicated with the air inlet port; the air inlet valve 34 is provided on the air inlet pipeline 33, and is used to open or close the air inlet pipeline 33; the air outlet pipeline 35 is communicated with the air outlet port; the air outlet valve 36 is provided on the air outlet pipeline 35, and is used to open or close the air outlet pipeline 35. The air extraction and inflation operations of the vacuum chamber 10 can be flexibly controlled by providing the air inlet valve 34 and the air outlet valve 36.

[0057] Specifically, the vacuum pump 37 is provided on the gas outlet pipeline 35, and is used to suck the gas in the vacuum chamber 11; the vacuum gauge 32, the gas inlet valve 34, the gas outlet valve 36 and the vacuum pump 37 are all electrically connected to the control module 80. The vacuum pump 37 disclosed in this embodiment is controlled by the control module 80 to extract gas in a timely manner to form a vacuum environment.

[0058] Specifically, in order to simulate the vacuum or near-vacuum environment in space, an extremely low vacuum degree needs to be achieved. Therefore, in this embodiment, the vacuum pump 37 can be a combination of a roughing pump and a high vacuum pump 37 (such as a turbomolecular pump or an ion pump) to fully extract the gas so that the vacuum chamber 11 can reach a vacuum less than or equal to 10 -6 Pascal's vacuum degree, thus approaching the real space environment and increasing the simulation effect.

[0059] Specifically, as another implementation of the present embodiment, it is disclosed that a plurality of interfaces may be provided on the top wall of the vacuum chamber 10 for connecting the external structure and the internal structure provided on the vacuum chamber 10, such as an electrical interface, an optical fiber interface, etc. In order to improve the airtightness, a mechanical coupling component may be provided on the top of the vacuum chamber 10 to connect with external equipment by coupling.

[0060] like Figure 1 and Figure 3 As shown, as another implementation of this embodiment, it is disclosed that the bottom wall of the vacuum chamber 10 can be welded, clamped or bonded to set the carrier 20, so as to improve stability. The top surface of the carrier 20 is a bearing surface 21 for placing the sample; a first channel and a second channel extending to the bearing surface 21 are formed in the carrier 20, and the first channel and the second channel are arranged crosswise; the temperature control module 40 includes a heating component 41 arranged in the first channel and a cooling component 42 arranged in the second channel.

[0061] The carrier 20 disclosed in this embodiment is in contact with the sample, so a temperature control module 40 is set inside the carrier 20, which is both concealed and can directly and efficiently control the temperature of the sample, with good control effect, convenient operation, and high safety. The heating component 41 includes but is not limited to any one of an infrared heater, a resistance heater, and an electromagnetic heater; the cooling component 42 includes but is not limited to a water cooling circulation system or a liquid nitrogen cooling system. In this embodiment, the heating component 41 and the cooling component 42 are alternately arranged in the carrier 20. Whether it is heating or cooling during the control process, the efficiency is very high, so that the test factors can be quickly and accurately controlled to improve the accuracy of the test data.

[0062] Preferably, in this embodiment, an infrared heater is used as the heating component 41, and a liquid nitrogen cooling system is used as the cooling component 42, so as to achieve a high temperature or ultra-low temperature state, which is closer to the actual situation of the space environment.

[0063] like Figure 3 , Figure 4 and Figure 5 As shown, as another implementation of this embodiment, a first through hole is provided on the top of the vacuum chamber 10; the pulse laser module 50 includes a laser 51, a laser transmission component 52, a laser emission cylinder 53 and a focusing mirror 54, and the laser 51 is electrically connected to the control module 80. The laser transmission component 52 is connected to the vacuum chamber 10; and the laser transmission component 52 is connected to the laser 51, and is used to guide the laser emitted by the laser 51 to the first through hole. The laser emission cylinder 53 is rotatably arranged on the inner wall of the vacuum chamber 10. One end of the laser emission cylinder 53 is connected to the first through hole, and the other end faces the stage 20; the focusing mirror 54 is arranged on the end of the laser emission cylinder 53 facing the stage 20, and is used to focus the laser and adjust the spot size.

[0064] The laser 51 disclosed in this embodiment is used to generate and emit laser light. By utilizing the adjustability of the laser light, the wavelength of the laser light can be selected according to the simulation requirements, and the corresponding laser light can be emitted to increase the realistic effect of simulating the bombardment of space particles. Specifically, the laser 51 disclosed in this embodiment is a neodymium-doped yttrium aluminum garnet (Nd:YAG) laser. The Nd:YAG laser has high peak power and short pulse width, which is suitable for simulating micrometeorite impacts, and the laser energy and pulse frequency are adjustable, which can meet different experimental requirements.

[0065] Specifically, the laser transmission member 52 disclosed in this embodiment is composed of a plurality of optical elements, such as lenses, reflectors, gratings, etc., to achieve the effect of adjusting the optical path of the laser. In the actual manufacturing process, due to factors such as space and manufacturing process, the output direction of the laser 51 may not be directly directed to the first via hole, so the laser transmission member 52 is set to guide the laser to the first via hole through the combination of multiple optical elements, and then to the laser emission cylinder 53, and to be transmitted toward the stage 20. On the other hand, for example, by using a combination of gratings, reflectors, etc., the focal position and spot size of the laser can also be adjusted, thereby improving the accuracy of laser bombardment and improving the reliability and stability of the test operation.

[0066] When testing different materials, the requirements for bombardment energy and spot size need to be determined according to specific circumstances. Therefore, the laser transmission component 52 disclosed in this embodiment is not limited to the combined use of the above-mentioned optical elements. This embodiment only cites the types of laser transmission components 52, but the protection scope of the present invention is not limited to this. As long as other types of laser transmission components 52 and combinations of laser transmission components 52 can achieve the technical effects disclosed in this application, they should also be within the scope of protection of this application as equivalent replacements for the concepts of the present invention.

[0067] Specifically, in this embodiment, the laser enters the laser emitting cylinder 53 after passing through the first through hole. The laser emitting cylinder 53 can rotate to control the emission direction of the laser, ensuring that the laser accurately bombards the target area on the surface of the sample. It is also convenient to scan the surface of the sample for multiple tests.

[0068] In addition, the laser emission cylinder 53 disclosed in this embodiment maintains a vacuum, so that the laser will not be affected by the gas in the vacuum chamber 11 in the process of emitting to the stage 20, and the laser can be efficiently emitted to the sample. A focusing mirror 54 is arranged in the laser emission cylinder 53, and the focusing position and the spot size are adjusted by the focusing mirror 54 to make the bombardment spot of the laser more concentrated and improve the bombardment energy.

[0069] For example Figure 3 , Figure 4 and Figure 5 As shown, as another implementation of this embodiment, it is disclosed that a second through hole is provided on the top of the vacuum chamber 10; the high-energy ion beam module 60 includes an ion beam generating element 61, an ion beam barrel 62, and an ion beam gun 63, the ion beam generating element 61 is electrically connected to the control module 80, and is disposed on the outer wall of the vacuum chamber 10, for generating a high-energy ion beam toward the second through hole; the ion beam barrel 62 can be rotatably disposed on the inner wall of the vacuum chamber 10; one end of the ion beam barrel 62 is connected to the second through hole, and the other end faces the carrier 20; the ion beam gun 63 is disposed on the ion beam barrel 62 at one end facing the carrier 20, for controlling the direction and distribution of the high-energy ion beam.

[0070] In this embodiment, the ion beam generator 61 is arranged on the outer wall of the vacuum chamber 10, and the output energy is started and controlled by the control module 80. The ion beam generator 61 can accelerate hydrogen ions or helium ions to the required energy level through an accelerator to control the intensity of the ion beam. After the high-energy ion beam passes through the second through hole, it propagates in the ion beam barrel 62. The ion beam barrel 62 can rotate, and an ion beam gun 63 is arranged at the end of the ion beam barrel 62 to accurately control the direction and distribution of the ion beam to ensure that the ion beam bombards the target position on the sample surface.

[0071] Preferably, the ion beam barrel 62 can be made of a high-density material, such as a lead plate. The ion beam barrel 62 is shielded to prevent leakage of high-energy ion beams, thereby protecting the vacuum chamber 10 and other structures in the vacuum chamber 10.

[0072] For example Figure 3 As shown, as another implementation of this embodiment, it is disclosed that the control module 80 includes an environmental factor controller 81, an electric controller 82 and a control terminal 83, the environmental factor controller 81 is electrically connected to the vacuum control module 30 and the temperature control module 40; the electric controller 82 is electrically connected to the pulse laser module 50, the high energy ion beam module 60, and the microscope module 70; the control terminal 83 is electrically connected to the environmental factor controller 81 and the electric controller 82.

[0073] In this embodiment, the environmental factor controller 81 is connected to the temperature control module 40 and the vacuum control module 30, and is used to control the environmental factors during the test and to collect data on the environmental factors collected in real time during the test. Figure 6 As shown, the environmental factor controller 81 is provided with two control knobs 811, corresponding to two indicator bars 812, and a display screen 813 is provided between the indicator bars 812 and the control knobs 811. When in use, the environmental factor controller 81 controls the temperature control module 40 and the vacuum control module 30 independently by rotating the two control knobs 811 respectively, and the temperature adjustment range and the vacuum adjustment range can be intuitively observed through the indicator bars 812.

[0074] Specifically, the environmental factor controller 81 disclosed in this embodiment is an independent control console, which uses a simple electric switch and a sliding rheostat-like circuit to control the temperature respectively, so as to increase the flexibility and safety of the control.

[0075] Specifically, the electric controller 82 is connected to the pulse laser module 50 and the high energy ion beam module 60, and controls the start and stop of the pulse laser module 50 and the high energy ion beam module 60 by receiving the signal transmitted by the control terminal 83. The control terminal 83 disclosed in this embodiment includes but is not limited to electronic devices such as an operation table, a computer, an intelligent remote controller, and an intelligent tablet computer installed with an integrated circuit board, and collects and analyzes data centrally, controls the test process centrally, sets test parameters, and stores data, so as to comprehensively judge the weathering effects of multiple factors on the material and study the space weathering tolerance of the sample.

[0076] like Figure 7 As shown, as another embodiment of the present application, a simulation method for a device for simulating space weathering of lunar rocks as described above is disclosed, which includes:

[0077] S100, loading the sample onto the stage 20, then closing the vacuum chamber 10, and evacuating the vacuum chamber 10 through the vacuum control module 30 until the vacuum degree of the vacuum chamber 11 reaches a preset vacuum degree;

[0078] S200, starting the temperature control module 40 to adjust the temperature of the vacuum chamber 11 to a preset temperature and maintain a constant temperature;

[0079] S300, adjusting the pulse laser module 50 and the high energy ion beam module 60 under the microscope field of view to align with the area to be bombarded on the sample;

[0080] S400, determining a test path and a test time based on the area to be bombarded, the bombardment energy of the pulse laser module 50 and the bombardment energy of the high-energy ion beam module 60;

[0081] S500, starting the pulse laser module 50 and the high energy ion beam module 60, repeating the bombardment test multiple times along the test path, and recording the bombardment time;

[0082] S600, when the bombardment time reaches the test time, turn off the pulse laser module 50, the high energy ion beam module 60 and the temperature control module 40; wait for the temperature in the vacuum chamber 10 to reach room temperature, open the vacuum chamber 10, take out the sample, and complete the test.

[0083] In this embodiment, the vacuum degree and temperature in the vacuum chamber 11 are accurately controlled to simulate the real space environment, and then laser bombardment and high-energy ion beam bombardment are used to simulate particle collisions in space to achieve a comprehensive simulation effect of multiple factors. During the test, each factor can be accurately controlled, which is conducive to conducting repeatable and accurate tests, obtaining real and effective test data, and facilitating the study of the application of space materials.

[0084] Specifically, as an implementation of this embodiment, before the step S500, the following is further disclosed:

[0085] S410, preheating the high energy ion beam module 60 and the pulse laser module 50; wherein the preheating time of the high energy ion beam module 60 is 30-60 minutes, and the preheating time of the pulse laser module 50 is 5-10 minutes.

[0086] The vacuum chamber 11 disclosed in the present embodiment is evacuated and is in an adjusted temperature similar to the space environment. However, both the high-energy ion beam and the laser need to be preheated before they can be excited. Therefore, depending on the required preheating time, the high-energy particle beam module can be preheated first, and then the pulse laser module 50 can be preheated, so that they can be bombarded at the same time at the end, achieving the effect of testing two factors together and increasing the simulation degree of the test.

[0087] Specifically, as another implementation of this embodiment, the preset vacuum degree is less than or equal to 10 -6 The vacuum chamber 10 disclosed in this embodiment simulates the space environment, so the vacuum degree is extremely small, and the vacuum degree needs to be preset to be less than or equal to 10 -6 Pa can start the test to obtain accurate test data.

[0088] Specifically, as another implementation of this embodiment, a process of using a device simulating the space weathering of lunar rocks to study lunar rock weathering materials is disclosed as follows:

[0089] Step 1: Before simulation, a solid sample with a reasonable volume and inactive chemical properties should be prepared according to the experimental purpose, and the space weathering factors to be studied (such as micrometeorite impact, solar wind bombardment, ultraviolet radiation, etc.) should be determined.

[0090] Step 2: According to the experimental requirements, pre-treat the sample by surface cleaning, drying and preliminary heating.

[0091] Step 3: Open the door of the vacuum chamber 10 , fix the sample on the stage 20 , and ensure that the initial position of the sample is within the sample placement area of ​​the stage 20 .

[0092] Step 4: Close the door and adjust the initial position of the carrier 20 to the test default position.

[0093] Step 5: Set the vacuum degree of the vacuum chamber 10 on the control module 80 -6 Pa, start the vacuum pump 37 to reach the preset vacuum degree and maintain this state.

[0094] Step 6: Set the test temperature and reach the target temperature through the temperature control module 40.

[0095] Step 7: Start the ion beam source and preheat it for 30 minutes, then set the ion source beam energy.

[0096] Step 8: When the ion beam source is preheated for 20 minutes, start the Nd:YAG laser and preheat for 10 minutes. Set the laser energy and pulse frequency, and select a wavelength of 1064 nanometers (nm), a pulse width of 6-8 nanoseconds (ns), a frequency of 20 hertz (Hz), and an energy of 1-30 millijoules (mj). This set of parameters is suitable for simulating the impact of micrometeoroids on the lunar surface around 108 years.

[0097] Step 9: Ensure that all subsystems are working properly, the vacuum chamber 11 is well sealed, and the laser, ion beam, ultraviolet light source and other equipment are in a safe working state.

[0098] Step 10: Under an optical microscope, select the appropriate laser focal length and spot size as needed, and adjust the laser emitter to ensure that it can correctly bombard the target area of ​​the sample; adjust the intensity and direction of the ion beam as needed to ensure that it can correctly bombard the sample surface.

[0099] Step 11: Start the ion beam emitter to fire a high-energy ion beam toward the sample surface to simulate the effect of solar wind bombardment; at the same time, start the laser emitter to simulate the effect of micrometeorite impact.

[0100] Step 12: Based on the real-time monitoring data, keep the parameters of each subsystem stable to ensure that the experimental conditions are consistent with expectations until the end of the set experimental time.

[0101] Step 13: Turn off the laser emitter and ion beam emitter in turn, and then observe the sample through a microscope to determine whether the simulation test is successful.

[0102] Step 14: Turn off the temperature control module 40 to ensure that the device returns to a safe state and returns to normal temperature.

[0103] Step 15: After the temperature returns to normal, slowly release the vacuum state.

[0104] Step 16: After the vacuum state is released, open the cabin door and carefully remove the sample for subsequent detailed analysis.

[0105] Step 17: Close the hatch and complete the simulation.

[0106] It should be understood that the various parts of the present application can be implemented in hardware, software, firmware or a combination thereof. In the above-mentioned embodiments, multiple steps or methods can be implemented in software or firmware stored in a memory and executed by a suitable instruction execution system. If implemented in hardware, as in another embodiment, it can be implemented by any one of the following technologies known in the art or their combination: a discrete logic circuit having a logic gate circuit for implementing a logic function on a data signal, a dedicated integrated circuit having a suitable combination of logic gate circuits, a programmable gate array, a field programmable gate array, etc.

[0107] In addition, each functional unit in each embodiment of the present application may be integrated into a processing module, or each unit may exist physically separately, or two or more units may be integrated into one module. The above-mentioned integrated module may be implemented in the form of hardware or in the form of a software functional module. If the integrated module is implemented in the form of a software functional module and sold or used as an independent product, it may also be stored in a computer-readable storage medium.

[0108] In summary, the present application discloses a device for simulating space weathering of lunar rocks, which includes a vacuum chamber 10, a stage 20, a vacuum control module 30, a temperature control module 40, a pulse laser module 50, a high-energy ion beam module 60, a microscope module 70 and a control module 80. The vacuum chamber 11 is formed in a hollow space inside the vacuum chamber 10; the stage 20 is arranged in the vacuum chamber 10 for placing samples; the vacuum control module 30 is arranged on the vacuum chamber 10 for collecting vacuum data in the vacuum chamber 11 and controlling the vacuum degree; the temperature control module 4 ... 0 is connected to the vacuum chamber 10, and is used to collect temperature data in the vacuum chamber 11 and adjust the temperature; the pulse laser module 50 is connected to the vacuum chamber 10, and is used to emit laser toward the carrier 20; the high-energy ion beam module 60 is connected to the vacuum chamber 10, and is used to emit a high-energy ion beam toward the carrier 20; the microscope module 70 is arranged in the vacuum chamber 10, facing the carrier 20; the control module 80 is electrically connected to the vacuum degree control module 30, the temperature control module 40, the pulse laser module 50 and the high-energy ion beam module 60.

[0109] The device for simulating the space weathering of lunar rocks disclosed in this embodiment forms a closed vacuum chamber 11 in a vacuum cabin 10, and then controls environmental factors by means of vacuuming and temperature adjustment so that the surrounding area of ​​the sample on the carrier 20 is close to the space environment, and then the sample is bombarded with scanning lasers and ion beams under the perspective of a microscope, so as to simulate the weathering effects such as micrometeor impacts, cosmic rays, and solar wind radiation in space, thereby achieving a comprehensive simulation of the scene where multiple factors work together, and more realistically restoring the effect of space weathering, so as to increase the authenticity of the test results, improve the reliability of the test data, and facilitate research and exploration of the impact of the space environment on materials.

[0110] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application may be combined with each other.

[0111] It should be noted that the present invention takes the device for simulating the space weathering of lunar rocks as an example to introduce the specific structure and working principle of the present invention, but the application of the present invention is not limited to the device for simulating the space weathering of lunar rocks. It can also be applied to other similar objects, such as the detection and research of Martian soil, mineral crystals, and surface materials of cosmic celestial bodies.

[0112] It should be understood that the present invention is not limited to the exact construction that has been described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the present invention is limited only by the appended claims.

[0113] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A device for simulating space weathering of lunar rocks, characterized in that: include: A vacuum chamber, wherein the interior of the vacuum chamber is hollow to form a vacuum chamber; A stage, disposed in the vacuum chamber, for placing a sample; A vacuum control module is provided on the vacuum chamber and is used to collect vacuum data in the vacuum chamber and control the vacuum degree; A temperature control module, connected to the vacuum chamber, for collecting temperature data in the vacuum chamber and adjusting the temperature; A pulse laser module, connected to the vacuum chamber, for emitting laser light toward the carrier; A high energy ion beam module, connected to the vacuum chamber, for emitting a high energy ion beam toward the carrier; A microscope module is disposed in the vacuum chamber and faces the stage; as well as The control module is electrically connected to the vacuum control module, the temperature control module, the pulse laser module and the high-energy ion beam module.

2. The device for simulating space weathering of lunar rocks according to claim 1, characterized in that: The side wall of the vacuum chamber is provided with air holes; the vacuum degree control module comprises: A three-way pipeline, one port of which is inserted into the air hole, and the other two ports are respectively an air inlet port and an air outlet port; A vacuum gauge, arranged on the three-way pipeline, for monitoring the vacuum degree; an air intake pipeline, connected to the air intake port; An air intake valve, disposed on the air intake pipeline, for opening or closing the air intake pipeline; An air outlet pipeline, connected to the air outlet port; an air outlet valve, disposed on the air outlet pipeline, for opening or closing the air outlet pipeline; and A vacuum pump, disposed on the gas outlet pipeline, for sucking gas in the vacuum chamber; Wherein, the vacuum gauge, the air inlet valve, the air outlet valve and the vacuum pump are all electrically connected to the control module.

3. The device for simulating space weathering of lunar rocks according to claim 1, characterized in that: The top surface of the carrier is a bearing surface for placing the sample; a first channel and a second channel extending to the bearing surface are formed in the carrier, and the first channel and the second channel are cross-arranged; the temperature control module includes a heating component arranged in the first channel and a cooling component arranged in the second channel.

4. The device for simulating space weathering of lunar rocks according to claim 1, characterized in that: The control module comprises: An environmental factor controller, electrically connected to the vacuum control module and the temperature control module; an electric controller, electrically connected to the pulse laser module, the high energy ion beam module, and the microscope module; and The control terminal is electrically connected to the environmental factor controller and the electric controller.

5. The device for simulating space weathering of lunar rocks according to claim 1, characterized in that: The top of the vacuum chamber is provided with a first through hole; the pulse laser module comprises: A laser, electrically connected to the control module; A laser transmission element connected to the vacuum chamber; and the laser transmission element is connected to the laser, and is used to guide the laser emitted by the laser to the first via hole; A laser emitting cylinder is rotatably disposed on the inner wall of the vacuum chamber; one end of the laser emitting cylinder is connected to the first through hole, and the other end faces the carrier; and A focusing mirror is arranged on the end of the laser emitting cylinder facing the carrier, and is used for focusing the laser and adjusting the spot size.

6. The device for simulating space weathering of lunar rocks according to claim 5, characterized in that: The laser is a neodymium-doped yttrium aluminum garnet laser.

7. The device for simulating space weathering of lunar rocks according to claim 1, characterized in that: A second through hole is provided on the top of the vacuum chamber; the high energy ion beam module comprises: an ion beam generating element, electrically connected to the control module, disposed on an outer wall of the vacuum chamber, and used for generating a high-energy ion beam toward the second through hole; An ion beam barrel is rotatably disposed on the inner wall of the vacuum chamber; one end of the ion beam barrel is butted against the second through hole, and the other end faces the carrier; The ion beam gun is arranged on one end of the ion beam barrel facing the carrier and is used to control the direction and distribution of the high energy ion beam.

8. A simulation method for the device for simulating space weathering of lunar rocks as claimed in any one of claims 1 to 7, characterized in that: include: Load the sample onto the stage, then close the vacuum chamber, and evacuate the vacuum chamber through the vacuum control module until the vacuum degree of the vacuum chamber reaches a preset vacuum degree; Starting the temperature control module to adjust the temperature of the vacuum chamber to a preset temperature and maintain a constant temperature; Under the microscope field of view, adjust the pulse laser module and the high-energy ion beam module to focus together on the area to be bombarded on the sample; Determining a test path and a test time based on the area to be bombarded, the bombardment energy of the pulse laser module, and the bombardment energy of the high-energy ion beam module; Starting the pulse laser module and the high-energy ion beam module, repeating the bombardment test multiple times along the test path, and recording the bombardment time; When the bombardment time reaches the test time, the pulse laser module, the high energy ion beam module and the temperature control module are turned off; the temperature in the vacuum chamber is waited to reach room temperature, the vacuum chamber is opened, the sample is taken out, and the test is completed.

9. The simulation method of the device for simulating space weathering of lunar rocks according to claim 8, characterized in that: Before the step of starting the pulse laser module and the high energy ion beam module, repeating the bombardment test multiple times along the test path, and recording the bombardment time, the method further includes: Preheating the high energy ion beam module and the pulse laser module; wherein the preheating time of the high energy ion beam module is 30-60 minutes, and the preheating time of the pulse laser module is 5-10 minutes.

10. The simulation method of the device for simulating space weathering of lunar rocks according to claim 8, characterized in that: The preset vacuum degree is less than or equal to 10 -6 Pa.

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