Apparatus for simulating lunar space weathering of lunar breccia and a simulation method thereof

Abstract

This invention discloses a device and method for simulating the space weathering of lunar rocks. The device includes a vacuum chamber, a stage, a vacuum control module, a temperature control module, a pulsed laser module, a high-energy ion beam module, a microscope module, and a control module. The vacuum chamber is hollow, forming a vacuum cavity. The stage is located inside the vacuum chamber. The vacuum control module is located on the vacuum chamber. The temperature control module, pulsed laser module, and high-energy ion beam module are all connected to the vacuum chamber. The microscope module is located inside the vacuum chamber, facing the stage. The control module is electrically connected to the vacuum control module, temperature control module, pulsed laser module, and high-energy ion beam module. By integrating and precisely controlling multiple modules, the device simulates the space weathering of lunar rocks, realizing a scenario where multiple space weathering factors act together, thus improving the realism of ground-based simulation experiments.

Description

Technical Field

[0001] This invention relates to the field of surface experimental simulation technology of lunar space weathering, and in particular to a device and simulation method for simulating lunar rock space weathering. Background Technology

[0002] Space weathering refers to the combined physical and chemical processes that occur on the surfaces of planets or small celestial bodies exposed to space for extended periods, in environments with little or no atmosphere, due to the influence of micrometeoroid impacts, cosmic rays, solar wind radiation, and other environmental factors. Space weathering alters the physical and optical properties of materials on celestial surfaces, significantly impacting remote sensing and planetary science research. Since humanity began exploring the space environment, extensive research on space weathering has been conducted. However, for the Moon, Earth's closest natural satellite, the number of samples obtained is limited, and sampling locations are also limited. Relying on existing samples and remote sensing data for space weathering research has certain limitations, making it difficult to comprehensively represent the weathering characteristics of different regions of the lunar surface. Furthermore, the resolution and accuracy of remote sensing technology are limited, and it cannot penetrate deep beneath the lunar surface to detect changes. To overcome these shortcomings, researchers have gradually turned to ground-based simulation experiments, recreating the lunar environment in the laboratory to systematically study the space weathering effects on lunar surface materials, especially lunar rocks.

[0003] However, the existing laboratory simulation capabilities for lunar rocks subjected to space weathering are limited. Current technologies typically use pulsed laser technology alone to simulate micrometeoroid impacts, mainly simulating the instantaneous high-temperature effect of meteorite impacts through laser heating. This primarily involves physical changes triggered by thermal effects, leading to localized melting and vaporization. Such simulation methods are usually designed for specific simulation missions and are one-sided in recreating the comprehensive effects of lunar space weathering. The simulated effects produced differ significantly from the actual lunar environment where multiple factors work together, resulting in insufficient authenticity and reliability of the research results and data.

[0004] Therefore, existing technologies still need to be improved and developed. Summary of the Invention

[0005] In view of the shortcomings of the prior art, the purpose of this invention is to provide a device and a simulation method for simulating the space weathering of lunar rocks, aiming to solve the problem that existing simulation devices only reproduce a single space weathering factor without considering the comprehensive space weathering effect on lunar rocks, resulting in a large gap between the simulation effect and the actual situation, insufficient realism, and thus insufficient reliability of the research results.

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

[0007] A device for simulating the space weathering of lunar rocks includes a vacuum chamber, a stage, a vacuum control module, a temperature control module, a pulsed laser module, a high-energy ion beam module, a microscope module, and a control module. The vacuum chamber is hollow, forming a vacuum cavity. The stage is located inside the vacuum chamber and is used to place samples. The vacuum control module is located on the vacuum chamber and is used to collect vacuum data and control the vacuum level within the vacuum cavity. The temperature control module is connected to the vacuum chamber and is used to collect temperature data and adjust the temperature within the vacuum cavity. The pulsed laser module is connected to the vacuum chamber and is used to emit a laser beam toward the stage. The high-energy ion beam module is connected to the vacuum chamber and is used to emit a high-energy ion beam toward the stage. The microscope module is located inside the vacuum chamber, facing the stage. The control module is electrically connected to the vacuum control module, the temperature control module, the pulsed laser module, and the high-energy ion beam module.

[0008] The device for simulating the space weathering of lunar rocks includes a vacuum chamber with vents on its sidewalls. The vacuum control module comprises a three-way pipe, a vacuum gauge, an inlet pipe, an inlet valve, an outlet pipe, an outlet valve, and a vacuum pump. One port of the three-way pipe is inserted into the vent, and the other two ports are the inlet and outlet ports, respectively. The vacuum gauge is located on the three-way pipe and is used to monitor the vacuum level. The inlet pipe is connected to the inlet port. The inlet valve is located on the inlet pipe and is used to open or close the inlet pipe. The outlet pipe is connected to the outlet port. The outlet valve is located on the outlet pipe and is used to open or close the outlet pipe. The vacuum pump is located on the outlet pipe and is used to pump gas from the vacuum chamber. The vacuum gauge, the inlet valve, the outlet valve, and the vacuum pump are all electrically connected to the control module.

[0009] The device for simulating the space weathering of lunar rocks includes a stage whose top surface serves as a support surface for placing the sample; a first channel and a second channel extending to the support surface are formed within the stage, with the first channel and the second channel arranged intersecting each other; the temperature control module includes a heating component located in the first channel and a cooling component located in the second channel.

[0010] The device for simulating the space weathering of lunar rocks includes a control module comprising an environmental factor controller, an electronic controller, and a control terminal. The environmental factor controller is electrically connected to the vacuum control module and the temperature control module. The electronic controller is electrically connected to the pulsed 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 electronic controller.

[0011] The device for simulating the space weathering of lunar rocks includes a vacuum chamber with a first through-hole at its top; a pulsed laser module comprising a laser, a laser conductor, a laser emitting tube, and a focusing lens; the laser being electrically connected to the control module; the laser conductor being connected to the vacuum chamber; and the laser conductor being connected to the laser to guide the laser emitted by the laser through the first through-hole; the laser emitting tube being rotatably mounted on the inner wall of the vacuum chamber; one end of the laser emitting tube being connected to the first through-hole, and the other end facing the stage; and the focusing lens being mounted on the end of the laser emitting tube facing the stage for focusing the laser and adjusting the spot size.

[0012] The device for simulating the 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 includes a second through-hole on the top of the vacuum chamber; the high-energy ion beam module includes an ion beam generator, an ion beam cylinder, and an ion beam gun; the ion beam generator is electrically connected to the control module and is located on the outer wall of the vacuum chamber, used to generate a high-energy ion beam toward the second through-hole; the ion beam cylinder is rotatably mounted on the inner wall of the vacuum chamber; one end of the ion beam cylinder is connected to the second through-hole, and the other end faces the stage; the ion beam gun is located on the end of the ion beam cylinder facing the stage, used to control the direction and distribution of the high-energy ion beam.

[0014] This application also discloses a simulation method for an apparatus used to simulate the space weathering of lunar rocks as described in any of the above descriptions, wherein the method includes:

[0015] Load the sample onto the stage, then close the vacuum chamber and evacuate the vacuum chamber using the vacuum control module until the vacuum level of the vacuum chamber reaches the preset vacuum level.

[0016] The temperature control module is activated to adjust the temperature of the vacuum chamber to the preset temperature and maintain it at a constant temperature.

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

[0018] The test path and test time are determined based on the area to be bombarded, the bombardment energy of the pulsed laser module, and the bombardment energy of the high-energy ion beam module.

[0019] Start the pulsed laser module and the high-energy ion beam module, repeat the bombardment test multiple times along the test path, and record the bombardment time;

[0020] When the bombardment time reaches the test time, turn off the pulsed laser module, the high-energy ion beam module, and the temperature control module; wait for the temperature inside the vacuum chamber to reach room temperature, then open the vacuum chamber, remove the sample, and complete the test.

[0021] The simulation method of the device for simulating the space weathering of lunar rocks, wherein, before the steps of activating the pulsed 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:

[0022] Preheat the high-energy ion beam module and the pulsed laser module; wherein the preheating time for the high-energy ion beam module is 30-60 minutes, and the preheating time for the pulsed 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 disclosed in this invention for simulating the space weathering of lunar rocks forms a closed vacuum chamber within a vacuum capsule. Environmental factors are then controlled through vacuuming and temperature regulation to make the environment around the sample on the stage closely resemble the space environment. The sample is then subjected to simultaneous scanning laser and ion beam bombardment under a microscope, thereby simulating the combined effects of environmental factors such as micrometeoroid impacts, cosmic rays, and solar wind radiation in space. This achieves a comprehensive simulation of the combined effects of multiple factors, more realistically reproducing the effects of space weathering, thus increasing the authenticity of experimental results and improving the reliability of experimental data. This is beneficial for researching and exploring the impact of the space environment on materials. Attached Figure Description

[0026] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

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

[0028] Figure 2 This is a schematic diagram of the vacuum control module in this invention;

[0029] Figure 3This is another schematic diagram of the device for simulating the space weathering of lunar rocks in this invention;

[0030] Figure 4 This is a schematic diagram of the optical path of a portion of the device for simulating the space weathering of lunar rocks in this invention.

[0031] Figure 5 This is a schematic diagram of the structure inside the vacuum chamber in this invention;

[0032] Figure 6 This is a schematic diagram of the environmental factor controller in this invention;

[0033] Figure 7 This is a flowchart of the simulation method for the apparatus used in the invention to simulate the space weathering of lunar rocks.

[0034] The components include: 10. Vacuum chamber; 11. Vacuum cavity; 20. Stage; 21. Bearing surface; 30. Vacuum control module; 31. Three-way pipe; 32. Vacuum gauge; 33. Inlet pipe; 34. Inlet valve; 35. Outlet pipe; 36. Outlet valve; 37. Vacuum pump; 40. Temperature control module; 41. Heating component; 42. Cooling component; 50. Pulsed laser module; 51. Laser; 52. Laser conductor; 53. Laser emitting tube; 54. Focusing lens; 60. High-energy ion beam module; 61. Ion beam generator; 62. Ion beam tube; 63. Ion beam gun; 70. Microscope module; 80. Control module; 81. Environmental factor controller; 811. Control knob; 812. Indicator bar; 813. Display screen; 82. Electronic controller; 83. Control terminal. Detailed Implementation

[0035] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0036] See Figure 1 In one embodiment of this invention application, a device for simulating the space weathering of lunar rocks is disclosed, comprising a vacuum chamber 10, a stage 20, a vacuum degree control module 30, a temperature control module 40, a pulsed laser module 50, a high-energy ion beam module 60, a microscope module 70, and a control module 80. The vacuum chamber 10 has a hollow interior forming a vacuum chamber 11. The stage 20 is disposed inside the vacuum chamber 10 and is used to place samples.

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

[0038] During the experiment, the sample was bombarded with scanning laser and ion beams under a microscope. The advantages of simultaneous activation are: 1. The ion beam provides the implantation and sputtering effect of charged particles, while the pulsed laser simulates the instantaneous heating effect of high-energy radiation, thus more comprehensively reproducing the weathering process in space; 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, thus more realistically reproducing the changes in lunar rocks caused by space weathering; 3. Laser heating reduces the adhesion energy of the material surface, making the sputtering effect caused by the ion beam more obvious. This is especially important when simulating surface erosion caused by solar wind, and can more realistically reproduce the material loss caused by charged particles and thermal effects in the space environment.

[0039] Specifically, the device disclosed in this application for simulating lunar rock weathering in space can simulate the effects of sputtering and secondary ionization during space weathering, resulting in ion implantation; it can also simulate the physical changes and melting and recrystallization phenomena on the material surface under instantaneous high temperatures. In general, simulating weathering processes such as micrometeoroid impacts, cosmic rays, and solar wind radiation in space, and mimicking scenarios involving multiple factors working together, more realistically recreates the effects of space weathering, thereby increasing the authenticity of experimental results, improving the reliability of experimental data, and facilitating the research and exploration of the impact of the space environment on materials.

[0040] Specifically, the vacuum control module 30 is mounted on the vacuum chamber 10 and is used to collect vacuum data and control the vacuum level within the vacuum chamber 11; the temperature control module 40 is connected to the vacuum chamber 10 and is used to collect temperature data and adjust the temperature within the vacuum chamber 11. In this embodiment, by monitoring the vacuum level and temperature within the vacuum chamber 10 in real time, the environmental influencing factors within the vacuum chamber 11 are precisely controlled, so as to simulate the space environment according to experimental needs and improve the realism of the simulation effect.

[0041] Specifically, the pulsed laser module 50 is connected to the vacuum chamber 10 and is used to emit laser light toward the stage 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 stage 20; the microscope module 70 is located inside the vacuum chamber 10, facing the stage 20. By bombarding the sample surface with laser light and high-energy ion beams in a simulated space environment, the weathering effects of various particles in space are simulated, achieving a comprehensive simulation of multiple influencing factors.

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

[0043] Specifically, the concept of maturity for lunar weathering materials is currently unclear. The content of nano-iron particles in the sample is typically used as an assessment parameter. However, in the real space environment, the lunar surface is complex, with multiple physicochemical processes occurring simultaneously. Therefore, the simultaneous occurrence of electromagnetic wave effects, bombardment by charged ions, and other factors can have indirect effects, such as thermal or charge effects. The charge effect refers to the accumulation of charge on the material surface during ion beam irradiation, especially on insulating materials. Laser irradiation, while heating, also leads to charge redistribution and may even excite the diffusion of surface charge. This charge effect affects the behavior of the ion beam both on and within the material. Clearly, the combined effects of two or more of these factors are impossible to test with current technology.

[0044] In other words, the combined effects of laser and ion beams in the actual lunar environment cannot be simulated by traditional laser heating alone. The different experimental conditions inevitably lead to significant differences in the realism and validity of the experiments. Therefore, to accurately reproduce the weathering effects, it is necessary to consider all weathering factors simultaneously.

[0045] In this embodiment, both laser and high-energy ion beams are used to bombard the test area of ​​the sample to simulate the combined effect of the two processes, as well as the indirect effects when they act simultaneously. This approach more closely resembles the actual weathering environment of lunar rocks and increases the realism of the simulation experiment.

[0046] In this embodiment, the experiment can be observed through the microscope module 70, which directly conveys information about the sample surface and achieves a visualization effect. The microscope module 70 can directly reflect changes in the top surface of the sample, and under the microscope's viewpoint, the bombardment positions of the pulsed laser module 50 and the high-energy ion beam module 60 can be adjusted to focus the laser and high-energy particle beam, so that the same position can be accurately bombarded during the experiment, thereby improving the accuracy of the experiment and the validity of the experimental results.

[0047] Specifically, the control module 80 is electrically connected to the vacuum control module 30, the temperature control module 40, the pulsed 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 controls. The control module 80 can transmit electrical signals via cables or send communication signals via WiFi units, Bluetooth units, antenna units, etc., thereby transmitting signals with the vacuum control module 30, temperature control module 40, pulsed laser module 50, and high-energy ion beam module 60 to accurately control the output values ​​of multiple factors, accurately simulate experimental conditions, and further improve the realism of the simulation effect.

[0048] In summary, this embodiment integrates multiple environmental factors into a control module 80, constructing a simulation device that can comprehensively control multiple factors of space weathering. This realistically recreates the space environment, allowing for experiments to be conducted on the ground. This enables systematic research on materials on the surface of celestial bodies, facilitating the study and understanding of 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, as humans have been exploring space, a great deal of research has been conducted on the weathering of celestial surfaces. Current research has revealed the evolution, color changes, and reasons for the decrease in reflectivity of lunar rock weathering materials by analyzing lunar samples and remote sensing data from the lunar surface.

[0050] However, due to the unique nature of the space environment, the number of samples obtained is limited, and the sampling locations are also limited, making it difficult to comprehensively represent the weathering characteristics of different regions on the lunar surface. Furthermore, the resolution and accuracy of remote sensing technology are limited, and it cannot penetrate deep below the surface to detect changes. Currently, relying on existing samples and remote sensing data for space weathering research has certain limitations, is difficult to operate, and the stability and reliability of experimental results are hard to guarantee. The device for simulating lunar rock weathering in space disclosed in this embodiment can be used to conduct simulation experiments on the Earth's surface, thereby improving the reliability and stability of the experiments and facilitating systematic research on materials that can be developed, constructed, and used on the lunar surface.

[0051] Specifically, as one embodiment of this invention, the vacuum chamber 10 is disclosed to be generally cubic in shape. The vacuum chamber 10 can be integrally molded using a mold, and is cast from metals such as stainless steel or aluminum alloy, possessing sufficient hardness and strength, as well as good sealing performance, capable of maintaining an ultra-high vacuum state. A door can be provided on the side of the vacuum chamber 10. The sample is placed through the door, and after the door is closed, a sealed vacuum chamber 11 is formed inside the vacuum chamber 10. By evacuating air through the vacuum control module 30, a vacuum environment can be gradually formed.

[0052] Specifically, as another embodiment of this invention, the stage 20 is disclosed as a metal stage, installed at the center of the bottom surface of the vacuum chamber 11. A clamp can be provided in the central area of ​​the stage 20 to hold the sample, or a groove can be provided to limit the sample's position, thereby improving the sample's stability during the experiment. Furthermore, the stage 20 can prevent direct bombardment of the inner wall of the vacuum chamber 10 by laser or high-energy ion beams, preventing damage or accidents. The stage 20 can be configured as a movable stage 20, driven by an electric motor, allowing for lateral and longitudinal movement to precisely adjust the sample's position and facilitate experimentation.

[0053] like Figure 1 and Figure 2 As shown, in another embodiment of this invention, the side wall of the vacuum chamber 10 is provided with air holes; 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 experiment, the exhaust valve 36 can be opened and the inlet valve 34 can be closed. The vacuum pump 37 continuously pumps air until the vacuum gauge 32 indicates that the target vacuum level has been reached. Then, the exhaust valve 36 is closed, thus forming a sealed environment that meets the vacuum level requirements in the vacuum chamber 10. After the experiment, the inlet valve 34 is opened and gas is gradually introduced from the inlet pipe 33 to release the vacuum state in the vacuum chamber 11, balance the air pressure inside and outside the chamber, and then it is convenient to open the chamber door and take out the sample.

[0055] Specifically, the vacuum gauge 32 disclosed in this embodiment is installed on the three-way pipe 31 for monitoring the vacuum level. Gas in and out of the vacuum chamber 11 both pass through the three-way pipe 31; therefore, by taking readings from the vacuum gauge 32, the vacuum level data within the vacuum chamber 11 can be obtained in real time and accurately. Specifically, the vacuum gauge 32 disclosed in this embodiment includes, but is not limited to, the Pirani vacuum gauge 32. The Pirani vacuum gauge 32 is a type of thermal conductivity vacuum gauge 32, which has a fast response speed and accurate measurement, thus it can reflect the vacuum level within the vacuum chamber 10 in real time, facilitating improved control precision.

[0056] Specifically, the air inlet pipe 33 is connected to the air inlet port; the air inlet valve 34 is provided on the air inlet pipe 33 for opening or closing the air inlet pipe 33; the air outlet pipe 35 is connected to the air outlet port; and the air outlet valve 36 is provided on the air outlet pipe 35 for opening or closing the air outlet pipe 35. The air inlet valve 34 and the air outlet valve 36 allow for flexible control of the vacuum chamber 10's pumping and filling operations.

[0057] Specifically, the vacuum pump 37 is installed on the outlet pipe 35 and is used to draw gas from the vacuum chamber 11; the vacuum gauge 32, the inlet valve 34, the outlet valve 36, and the vacuum pump 37 are all electrically connected to the control module 80. In this embodiment, the vacuum pump 37 is controlled by the control module 80 to draw gas in a timely manner, creating a vacuum environment.

[0058] Specifically, to simulate a vacuum or near-vacuum environment in space, an extremely low vacuum level is required. Therefore, in this embodiment, the vacuum pump 37 can be a combination of a coarse pump and a high vacuum pump 37 (e.g., a turbomolecular pump or an ion pump) to fully extract the gas, so that the vacuum chamber 11 can achieve a vacuum level of less than or equal to 10. -6 Pascal's vacuum level, thus approximating the real space environment, enhances the simulation's effect.

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

[0060] like Figure 1 and Figure 3 As shown, in another embodiment of this invention, the bottom wall of the vacuum chamber 10 is welded, snap-fitted, or adhesively fitted with a stage 20 to improve stability. The top surface of the stage 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 within the stage 20, and the first channel and the second channel are arranged intersectingly; the temperature control module 40 includes a heating component 41 disposed in the first channel and a cooling component 42 disposed in the second channel.

[0061] In this embodiment, the stage 20 is in contact with the sample, so a temperature control module 40 is installed inside the stage 20. This is both concealed and allows for direct and efficient temperature control of the sample, resulting in good temperature regulation, convenient operation, and high safety. The heating component 41 includes, but is not limited to, any one of an infrared heater, a resistance heater, or 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 inside the stage 20. Whether heating or cooling, the efficiency is very high during the control process, thereby enabling rapid and accurate control of experimental factors and improving the accuracy of experimental 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 high or ultra-low temperature conditions, which is closer to the real situation of the space environment.

[0063] like Figure 3 , Figure 4 and Figure 5 As shown, in another embodiment of this invention, the top of the vacuum chamber 10 is provided with a first through hole; the pulsed laser module 50 includes a laser 51, a laser conductor 52, a laser emitting cylinder 53, and a focusing lens 54. The laser 51 is electrically connected to the control module 80. The laser conductor 52 is connected to the vacuum chamber 10; and the laser conductor 52 is connected to the laser 51 to guide the laser emitted by the laser 51 to the first through hole. The laser emitting cylinder 53 is rotatably mounted on the inner wall of the vacuum chamber 10. One end of the laser emitting cylinder 53 is connected to the first through hole, and the other end faces the stage 20; the focusing lens 54 is disposed on the end of the laser emitting 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. Utilizing the tunability of the laser, the wavelength can be selected according to the simulation requirements to emit the corresponding laser, thereby increasing the realism of simulating space particle bombardment. Specifically, the laser 51 disclosed in this embodiment is a neodymium-doped yttrium aluminum garnet (Nd:YAG) laser. Nd:YAG lasers have high peak power and short pulse width, making them suitable for simulating micrometeorite impacts. Furthermore, the laser energy and pulse frequency are adjustable, allowing them to adapt to different experimental needs.

[0065] Specifically, the laser guide 52 disclosed in this embodiment is composed of multiple optical elements, such as lenses, mirrors, and gratings, to achieve the effect of adjusting the optical path of the laser. In actual manufacturing, due to factors such as space and manufacturing processes, the output direction of the laser 51 may not directly hit the first through-hole. Therefore, the laser guide 52 is provided to guide the laser towards the first through-hole through the combination of multiple optical elements, and then into the laser emitting cylinder 53, transmitting it towards the stage 20. On the other hand, by using combinations such as gratings and mirrors, the focal position and spot size of the laser can also be adjusted, thereby improving the accuracy of laser bombardment and enhancing the reliability and stability of the experimental operation.

[0066] Since the requirements for bombardment energy and spot size need to be determined according to the specific circumstances when testing different materials, the laser conductor 52 disclosed in this embodiment is not limited to the combination of the above-mentioned optical elements. This embodiment is only an example of the type of laser conductor 52, but the scope of protection of this invention is not limited to this. Other types of laser conductors 52 and combinations of laser conductors 52, as long as they can achieve the technical effect disclosed in this application, can be regarded as equivalent substitutions of the concept of this invention and should also be within the scope of protection of this application.

[0067] Specifically, in this embodiment, the laser enters the laser emitting tube 53 after passing through the first through hole. The laser emitting tube 53 is rotatable, thereby controlling the laser emission direction and ensuring that the laser accurately bombards the target area on the sample surface. In addition, it is also convenient to scan the sample surface to perform multiple tests.

[0068] Furthermore, the laser emitting tube 53 disclosed in this embodiment maintains a vacuum, ensuring that the intensity of the laser beam is not affected by the gas in the vacuum chamber 11 during its trajectory toward the stage 20, thus efficiently directing the laser beam toward the sample. A focusing lens 54 is provided inside the laser emitting tube 53, which is used to focus the laser beam. By adjusting the focusing position and the size of the laser spot, the laser's bombardment spot becomes more concentrated, thereby increasing the bombardment energy.

[0069] For example Figure 3 , Figure 4 and Figure 5 As shown, in another embodiment of this invention, the top of the vacuum chamber 10 is provided with a second through hole; the high-energy ion beam module 60 includes an ion beam generator 61, an ion beam cylinder 62, and an ion beam gun 63. The ion beam generator 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 cylinder 62 is rotatably disposed on the inner wall of the vacuum chamber 10; one end of the ion beam cylinder 62 is connected to the second through hole, and the other end faces the stage 20; the ion beam gun 63 is disposed on the ion beam cylinder 62 at the end facing the stage 20 and is used to control the direction and distribution of the high-energy ion beam.

[0070] In this embodiment, the ion beam generator 61 is mounted on the outer wall of the vacuum chamber 10, and its energy output is activated and controlled by the control module 80. The ion beam generator 61 can accelerate hydrogen or helium ions to the required energy level via an accelerator to control the intensity of the ion beam. After passing through the second aperture, the high-energy ion beam propagates within the ion beam tube 62, which is rotatable. An ion beam gun 63 is mounted at the end of the ion beam tube 62 to precisely control the direction and distribution of the ion beam, ensuring that the ion beam is aimed at the target position on the sample surface.

[0071] Preferably, the ion beam tube 62 can be made of a high-density material, such as lead plate. The ion beam tube 62 shields against high-energy ion beam leakage, protecting the vacuum chamber 10 and other structures within it.

[0072] For example Figure 3 As shown, in another embodiment of this invention, the control module 80 includes an environmental factor controller 81, an electronic 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 electronic controller 82 is electrically connected to the pulsed 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 electronic 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 environmental factors during the experiment, and also to collect real-time data of environmental factors during the experiment. Figure 6 As shown, the environmental factor controller 81 has two control knobs 811, corresponding to two indicator bars 812, and a display screen 813 is set between the indicator bars 812 and the control knobs 811. In use, the environmental factor controller 81 independently controls the temperature control module 40 and the vacuum control module 30 by rotating the two control knobs 811 respectively, and the temperature adjustment range and 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 simple switches and sliding rheostats-like circuits to control the temperature, thereby increasing the flexibility and safety of control.

[0075] Specifically, the electronic controller 82 is connected to the pulsed laser module 50 and the high-energy ion beam module 60, and controls the start and stop of the pulsed laser module 50 and the high-energy ion beam module 60 by receiving signals emitted by the control terminal 83. The control terminal 83 disclosed in this embodiment includes, but is not limited to, electronic devices such as an operating table with an integrated circuit board, a computer, a smart remote control, and a smart tablet. It centrally collects and analyzes data, centrally controls the experimental process, sets experimental parameters, and stores data to comprehensively judge the weathering effect of multiple factors on the material and study the space weathering resistance of the sample.

[0076] like Figure 7 As shown, as another embodiment of this application, a simulation method for an apparatus used to simulate the space weathering of lunar rocks as described above is disclosed, comprising:

[0077] S100. Load the sample onto the stage 20, then close the vacuum chamber 10, and use the vacuum control module 30 to evacuate the vacuum chamber 10 until the vacuum level of the vacuum chamber 11 reaches the preset vacuum level.

[0078] S200: Start the temperature control module 40 to adjust the temperature of the vacuum chamber 11 to the preset temperature and maintain it at a constant temperature;

[0079] S300. Adjust the pulsed laser module 50 and the high-energy ion beam module 60 under the microscope to align them with the area to be bombarded on the sample.

[0080] S400. Determine the test path and test time based on the area to be bombarded, the bombardment energy of the pulsed laser module 50, and the bombardment energy of the high-energy ion beam module 60.

[0081] S500: Start the pulsed laser module 50 and the high-energy ion beam module 60, repeat the bombardment test multiple times along the test path, and record the bombardment time;

[0082] S600. When the bombardment time reaches the test time, turn off the pulsed laser module 50, the high-energy ion beam module 60 and the temperature control module 40; wait for the temperature inside 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 level and temperature in the vacuum chamber 11 are accurately controlled to simulate the real space environment. Then, laser bombardment and high-energy ion beam bombardment are used to simulate particle collisions in space, achieving a comprehensive simulation effect of multiple factors. Each factor can be precisely controlled during the experiment, which is conducive to conducting repeatable and accurate experiments, obtaining real and effective experimental data, and helping to study the application of space materials.

[0084] Specifically, as one implementation of this embodiment, before step S500, the method further includes:

[0085] S410. Preheat the high-energy ion beam module 60 and the pulsed 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 pulsed laser module 50 is 5-10 minutes.

[0086] In this embodiment, the vacuum chamber 11 is evacuated and its temperature is adjusted to be similar to that of space. 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, followed by the pulsed laser module 50, so that they can be bombarded simultaneously in the end, achieving the effect of testing both factors together and increasing the simulation degree of the test.

[0087] Specifically, as another implementation of this embodiment, the preset vacuum degree is disclosed to be less than or equal to 10. -6 Pa. The vacuum chamber 10 disclosed in this embodiment simulates a space environment, therefore the vacuum level is extremely low, and a preset vacuum level of less than or equal to 10 Pa is required. -6 Only then can the experiment begin in order to obtain accurate experimental data.

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

[0089] Step 1: Before the simulation, a solid sample with a reasonable volume and inert 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: Pre-treat the sample according to experimental requirements, including 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 hatch and adjust the initial position of stage 20 to the default test position.

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

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

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

[0096] Step 8: While the ion beam source is preheating for 20 minutes, start the Nd:YAG laser and preheat for 10 minutes. Set the laser energy and pulse frequency, selecting a wavelength of 1064 nanometers (nm), a pulse width of 6-8 nanoseconds (ns), a frequency of 20 Hz, and an energy of 1-30 millijoules (mJ). These parameters are suitable for simulating micrometeoroid impacts on the lunar surface around 108 years ago.

[0097] Step 9: Ensure that all subsystems are working properly, vacuum chamber 11 is well sealed, and equipment such as lasers, ion beams, and ultraviolet light sources are in a safe working condition.

[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: Activate the ion beam emitter to emit a high-energy ion beam onto the sample surface to simulate the effect of solar wind bombardment; at the same time, activate the laser emitter to simulate the effect of micrometeorite impact.

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

[0101] Step 13: Turn off the laser emitter and ion beam emitter in sequence, and then observe the sample under a microscope to determine whether the simulation experiment was successful.

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

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

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

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

[0106] It should be understood that various parts of this application can be implemented using hardware, software, firmware, or a combination thereof. In the above embodiments, multiple steps or methods can be implemented using software or firmware stored in memory and executed by a suitable instruction execution system. If implemented in hardware, as in another embodiment, it can be implemented using any one or a combination of the following techniques known in the art: discrete logic circuits having logic gates for implementing logical functions on data signals, application-specific integrated circuits (ASICs) having suitable combinational logic gates, programmable gate arrays (FPGAs), field-programmable gate arrays (FPGAs), etc.

[0107] Furthermore, the functional units in the various embodiments of this application can be integrated into a processing module, or each unit can exist physically separately, or two or more units can be integrated into a module. The integrated module can be implemented in hardware or as a software functional module. If the integrated module is implemented as a software functional module and sold or used as an independent product, it can also be stored in a computer-readable storage medium.

[0108] In summary, this application discloses a device for simulating the space weathering process of lunar rocks, comprising a vacuum chamber 10, a stage 20, a vacuum control module 30, a temperature control module 40, a pulsed laser module 50, a high-energy ion beam module 60, a microscope module 70, and a control module 80. The vacuum chamber 10 has a hollow interior forming a vacuum chamber 11. The stage 20 is disposed within the vacuum chamber 10 for placing samples. The vacuum control module 30 is disposed on the vacuum chamber 10 for collecting vacuum data and controlling the vacuum level within the vacuum chamber 11. The temperature control module 40... The 0 module is connected to the vacuum chamber 10 and is used to collect temperature data and adjust the temperature inside the vacuum chamber 11; the pulsed laser module 50 is connected to the vacuum chamber 10 and is used to emit lasers 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 beams toward the stage 20; the microscope module 70 is located inside the vacuum chamber 10 and faces the stage 20; the control module 80 is electrically connected to the vacuum degree control module 30, the temperature control module 40, the pulsed laser module 50, and the high-energy ion beam module 60.

[0109] The apparatus disclosed in this embodiment for simulating the weathering of lunar rocks in space forms a closed vacuum chamber 11 within the vacuum chamber 10. Environmental factors are then controlled by vacuuming and temperature regulation to make the environment around the sample on the stage 20 close to that of space. The sample is then bombarded with scanning laser and ion beams under a microscope to simulate weathering effects such as micrometeoroid impacts, cosmic rays, and solar wind radiation in space. This achieves a comprehensive simulation of the combined effects of multiple factors, more realistically reproducing the effects of weathering in space, thereby increasing the authenticity of experimental results, improving the reliability of experimental data, and facilitating the research and exploration of the impact of the space environment on materials.

[0110] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other.

[0111] It should be noted that this invention uses a device simulating the space weathering of lunar rocks as an example to introduce the specific structure and working principle of the invention, but the application of this invention is not limited to devices 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 materials on the surface of celestial bodies.

[0112] It should be understood that the present invention is not limited to the precise structure described above and shown in the accompanying drawings, and various modifications and changes can be made without departing from its scope. The scope of the 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 principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A device for simulating the space weathering of lunar rocks, characterized in that, include: Vacuum chamber, wherein the interior of the vacuum chamber is hollow and forms a vacuum cavity; A stage, located inside the vacuum chamber, is used to place samples; A vacuum control module, located on the vacuum chamber, is used to collect vacuum data and control the vacuum level within the vacuum chamber. A temperature control module, connected to the vacuum chamber, is used to collect temperature data and adjust the temperature inside the vacuum chamber. A pulsed laser module, connected to the vacuum chamber, is used to emit lasers toward the platform; A high-energy ion beam module, connected to the vacuum chamber, is used to emit a high-energy ion beam toward the stage; The microscope module is located inside the vacuum chamber, facing the stage; as well as The control module is electrically connected to the vacuum control module, the temperature control module, the pulsed laser module, and the high-energy ion beam module. The vacuum chamber has air vents on its side walls; the vacuum control module includes: A three-way pipe, with one port inserted into the air hole and the other two ports being the air inlet and air outlet ports, respectively; A vacuum gauge is installed on the three-way pipe to monitor the vacuum level; An intake pipe is connected to the intake port; An intake valve is provided on the intake pipe and is used to open or close the intake pipe; An exhaust pipe is connected to the exhaust port; An exhaust valve, located on the exhaust pipe, is used to open or close the exhaust pipe; and A vacuum pump, located on the outlet pipe, is used to draw gas from the vacuum chamber. The vacuum gauge, the inlet valve, the outlet valve, and the vacuum pump are all electrically connected to the control module; The top of the vacuum chamber is provided with a first through hole; the pulsed laser module includes: The laser is electrically connected to the control module; A laser conductor is connected to the vacuum chamber; and the laser conductor is connected to the laser, used to guide the laser emitted by the laser to the first through hole; A laser emitting tube is rotatably mounted on the inner wall of the vacuum chamber; one end of the laser emitting tube is connected to the first through hole, and the other end faces the platform; A focusing lens is disposed on the end of the laser emitting tube facing the stage, and is used to focus the laser and adjust the spot size; The top of the vacuum chamber is provided with a second through-hole; the high-energy ion beam module includes: An ion beam generator, electrically connected to the control module, is located on the outer wall of the vacuum chamber and is used to generate a high-energy ion beam toward the second through hole; An ion beam tube is rotatably mounted on the inner wall of the vacuum chamber; one end of the ion beam tube is connected to the second through hole, and the other end faces the stage. An ion beam gun, located on one end of the ion beam tube facing the stage, is used to control the direction and distribution of the high-energy ion beam.

2. The apparatus for simulating space weathering of lunar rocks according to claim 1, characterized in that, The top surface of the stage is a bearing surface for placing the sample; a first channel and a second channel extending to the bearing surface are formed inside the stage, and the first channel and the second channel are arranged intersectingly; the temperature control module includes a heating component disposed in the first channel and a cooling component disposed in the second channel.

3. The apparatus for simulating space weathering of lunar rocks according to claim 1, characterized in that, The control module includes: The environmental factor controller is electrically connected to both the vacuum control module and the temperature control module. The electronic controller is electrically connected to the pulsed laser module, the high-energy ion beam module, and the microscope module; and The control terminal is electrically connected to both the environmental factor controller and the electronic controller.

4. The apparatus for simulating space weathering of lunar rocks according to claim 1, characterized in that, The laser is a neodymium-doped yttrium aluminum garnet laser.

5. A simulation method for the apparatus used in any one of claims 1 to 4 to simulate the space weathering of lunar rocks, characterized in that, include: Load the sample onto the stage, then close the vacuum chamber and evacuate the vacuum chamber using the vacuum control module until the vacuum level of the vacuum chamber reaches the preset vacuum level. The temperature control module is activated to adjust the temperature of the vacuum chamber to the preset temperature and maintain it at a constant temperature. Under the microscope, adjust the pulsed laser module and the high-energy ion beam module to focus together on the area to be bombarded on the sample; The test path and test time are determined based on the area to be bombarded, the bombardment energy of the pulsed laser module, and the bombardment energy of the high-energy ion beam module. Start the pulsed laser module and the high-energy ion beam module, repeat the bombardment test multiple times along the test path, and record the bombardment time; When the bombardment time reaches the test time, turn off the pulsed laser module, the high-energy ion beam module, and the temperature control module; wait for the temperature inside the vacuum chamber to reach room temperature, then open the vacuum chamber, remove the sample, and complete the test.

6. The simulation method of the apparatus for simulating space weathering of lunar rocks according to claim 5, characterized in that, Before the steps of activating the pulsed laser module and the high-energy ion beam module, repeating the bombardment experiment multiple times along the test path, and recording the bombardment time, the method further includes: Preheat the high-energy ion beam module and the pulsed laser module; wherein the preheating time for the high-energy ion beam module is 30-60 minutes, and the preheating time for the pulsed laser module is 5-10 minutes.

7. The simulation method of the apparatus for simulating space weathering of lunar rocks according to claim 5, characterized in that, The preset vacuum degree is less than or equal to 10. -6 Pa.

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