Active gas confining pressure triaxial apparatus for moon extreme environment simulation
By designing an active gas confining pressure triaxial apparatus, employing inert gas and precise confining pressure control, the problem of existing equipment being unable to simulate the extreme lunar environment was solved, enabling efficient and accurate testing of the mechanical properties of lunar soil.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- GUANGZHOU UNIVERSITY
- Filing Date
- 2026-02-12
- Publication Date
- 2026-05-12
AI Technical Summary
Existing geomechanical testing equipment cannot accurately simulate the high vacuum and extreme temperature environment of the moon, and cannot conduct real thermo-mechanical coupling tests. Furthermore, traditional triaxial instruments are easily damaged under the extreme temperature differences on the moon.
Design an active gas confined pressure triaxial apparatus that uses inert gas as the confined pressure medium and combines a confined pressure inlet and outlet system to achieve efficient gas replacement and precise confined pressure control. Heat is isolated by an isolation chamber, and a temperature gradient is simulated by setting up a sample top seat and base control system. Metal bellows and actuators are used for active control of the confined pressure.
It enables accurate testing of the physical and mechanical properties of lunar soil under high vacuum and extreme temperatures, reduces heat loss, ensures the accuracy and reliability of test data, and simulates the multi-field coupled extreme environment on the lunar surface.
Smart Images
Figure CN122016495A_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of geomechanical testing technology for extraterrestrial bodies, and particularly relates to an active gas confining pressure triaxial apparatus for simulating extreme lunar environments. Background Technology
[0002] With the advancement of lunar exploration programs worldwide, lunar base construction and resource development have become crucial directions in the aerospace field. The mechanical properties of lunar surface geological materials directly impact the stability of lunar landers, the safety of base construction, and the feasibility of resource extraction. Currently, research on lunar geomechanical properties relies primarily on remote sensing and limited lunar soil sample analysis, lacking systematic in-situ testing data. The unique environmental conditions on the lunar surface, including high vacuum and extreme temperature variations, significantly influence the mechanical behavior of geological materials, and test results from Earth environments are difficult to directly apply to lunar engineering practices.
[0003] Existing geomechanical testing equipment is primarily designed for Earth's environment and cannot accurately simulate the unique lunar environment. While traditional triaxial apparatuses can test the mechanical properties of soil under complex stress states, they have the following limitations: they cannot simulate the high vacuum environment of the moon; and they struggle to simulate extreme temperature changes and cycles on the lunar surface. The lunar surface experiences extreme diurnal temperature variations, with daytime temperatures reaching 110–140°C and nighttime temperatures dropping to -180–-130°C. Furthermore, traditional triaxial apparatuses often use water or oil as the confining pressure medium. Under the extreme temperature differences on the moon, liquids may freeze and expand, leading to structural damage, or violently vaporize, causing uncontrolled confining pressure. Liquid media have high heat capacity, resulting in high energy consumption and slow temperature control, and making precise temperature cycling difficult. Existing equipment lacks effective thermal insulation design, making it impossible to establish a stable extreme temperature environment. Traditional equipment cannot simultaneously simulate the high vacuum and large temperature differences of the moon's stress states, making realistic thermo-mechanical coupling tests impossible. Summary of the Invention
[0004] The purpose of this invention is to provide an active gas confining pressure triaxial apparatus for simulating extreme lunar environments, in order to solve the problems existing in the prior art.
[0005] To achieve the above objectives, the present invention provides the following solution: The present invention provides an active gas confining pressure triaxial apparatus for simulating extreme lunar environments, comprising a base, a sample base control system on the top surface of the base, a sample mounted on the sample base control system, a sample top seat control system on the top of the sample, a confining pressure chamber outside the sample, an isolation chamber outside the confining pressure chamber, a loading frame fixed to the top surface of the base, a vertical loading system on the loading frame for applying pressure to the sample, a confining pressure exhaust system on the top of the confining pressure chamber, an active confining pressure control system on one side of the bottom of the confining pressure chamber, a confining pressure intake system and a vacuum extraction system on the other side of the bottom of the confining pressure chamber, and a monitoring mechanism inside the confining pressure chamber.
[0006] Optionally, the sample base control system includes a sample base fixed to the top surface of the base, a cooling element on the top surface of the sample base, a first oxygen-free copper on the top surface of the cooling element, the sample on the top surface of the first oxygen-free copper, a water chiller inside the base, the water chiller being connected to multiple water cooling pipes, and the water cooling pipes being located below the cooling element.
[0007] Optionally, the water-cooling pipe is provided with circumferential 360° needle-shaped turbulence columns.
[0008] Optionally, the sample top seat adjustment system includes a second oxygen-free copper in contact with the top surface of the sample. The top surface of the second oxygen-free copper is provided with a heating plate, and the top surface of the heating plate is provided with aluminum nitride ceramic. The top of the aluminum nitride ceramic abuts against the vertical loading system.
[0009] Optionally, the confining pressure venting system includes a convex arc-shaped venting device that communicates with the top surface of the confining pressure chamber. The top of the convex arc-shaped venting device is provided with a first valve and an oxygen sensor, with the oxygen sensor located above the first valve.
[0010] Optionally, the confining pressure air intake system includes a concave arc-shaped air guide outlet connected to the bottom of the confining pressure chamber. The concave arc-shaped air guide outlet is connected to a first gas supply pipe, which is connected to an inert gas loading controller. A second valve and a gas flow meter are respectively provided on the first gas supply pipe, and the gas flow meter is located on the side of the first gas supply pipe near the concave arc-shaped air guide outlet.
[0011] Optionally, the vacuum pumping system includes a second gas supply pipe, which is connected to a confining pressure chamber connecting pipe and an isolation chamber connecting pipe, respectively. The confining pressure chamber connecting pipe is connected to the sample, and a sample vacuum valve is provided on the confining pressure chamber connecting pipe. An isolation chamber valve is provided on the isolation chamber connecting pipe. A vacuum gauge is provided on the second gas supply pipe, and the second gas supply pipe is connected to a vacuum controller.
[0012] Optionally, the active pressure control system includes a metal bellows communicating with the confining chamber, a metal limiting tube on the outside of the metal bellows, an insulation layer on the outside of the metal limiting tube, and an actuator connected to the side of the metal bellows away from the confining chamber.
[0013] Optionally, the monitoring mechanism includes a pressure sensor and a temperature sensor respectively disposed on both sides of the sample base control system.
[0014] Optionally, the outer side of the sample base control system is provided with an annular heating wire.
[0015] This invention discloses the following technical effects: It can simultaneously achieve physical and mechanical property testing of simulated lunar soil under high vacuum and extreme temperature changes; through the confining pressure inlet and outlet systems, it can maximize air replacement, offering advantages such as high efficiency, thorough replacement, and stable flow; cold inert gas enters the bottom of the confining pressure chamber, and due to momentum, it may mix slightly with the bottom air, but will quickly settle due to density differences, forming a relatively clear, bottom-up gas interface; under continuous gas supply, this interface will rise steadily, with the area below the interface mainly consisting of inert gas and the area above the interface consisting of compressed and discharged air; through the active confining pressure control system, precise control of the confining pressure is achieved, effectively avoiding temperature interference with the confining pressure; the isolation chamber design achieves heat isolation, thereby reducing heat loss during temperature control and meeting green, low-carbon, and environmentally friendly requirements; by setting up a sample top seat control system and a sample base control system between the samples, it can achieve uneven heating of the soil or reproduce the huge temperature gradients existing on the surface of the moon and other extraterrestrial bodies (such as Mars). Attached Figure Description
[0016] The accompanying drawings, which form part of this application, are used to provide a further understanding of this application. The embodiments of this application and their descriptions are used to explain this application and do not constitute an undue limitation of this application. In the drawings: Figure 1 This is a schematic diagram of the active gas confining pressure triaxial apparatus for simulating extreme lunar environments according to the present invention; Figure 2 This is a schematic diagram of the sample base adjustment system of the present invention; Figure 3 This is a schematic diagram of the water-cooling pipe arrangement of the present invention; Figure 4 This is a schematic diagram of the cross-section of the water-cooling pipe of the present invention; Figure 5 This is a schematic diagram of the confining pressure control system of the present invention; Figure 6 This is a schematic diagram of the sample top seat adjustment system of the present invention; Figure 7 This is a schematic diagram of the confining pressure venting system of the present invention; Figure 8 This is a schematic diagram of the confining pressure air intake system of the present invention; Figure 9 This is a schematic diagram of the vacuum pumping system of the present invention.
[0017] Figure label: 1. Base; 2. Sample base control system; 201. First oxygen-free copper; 202. Cooling element; 203. Water-cooled pipe; 204. Water chiller; 3. Confining pressure active control system; 301. Metal bellows; 302. Metal limiting pipe; 303. Insulation layer; 304. Actuator; 4. Confining pressure chamber; 5. Pressure sensor; 6. Isolation chamber; 7. Sample; 8. Sample top seat control system; 801. Second oxygen-free copper; 802. Heating element; 803. Aluminum nitride ceramic; 9. Confining pressure venting system; 901. Convex arc-shaped venting device; 902. First valve; 903. Oxygen sensor; 10. Vertical loading system; 11. Loading frame; 12. Annular heating wire; 13. Temperature sensor; 14. Confining pressure inlet system; 1401. Concave arc-shaped gas guide outlet; 1402. Second valve; 1403. Gas flow meter; 1404. First gas supply pipe; 15. Vacuum pumping system; 1501. Sample vacuum valve; 1502. Isolation chamber valve; 1503. Vacuum gauge; 1504. Second gas supply pipe; 16. Vacuum controller; 17. Inert gas loading controller. Detailed Implementation
[0018] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. 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.
[0019] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.
[0020] Reference Figures 1 to 9As shown, this embodiment provides an active gas confining pressure triaxial apparatus for simulating extreme lunar environments, including a base 1, a sample base control system 2 on the top surface of the base 1, a sample 7 mounted on the sample base control system 2, a sample top seat control system 8 on the top of the sample 7, a confining pressure chamber 4 outside the sample 7, an isolation chamber 6 outside the confining pressure chamber 4, a loading frame 11 fixed to the top surface of the base 1, a vertical loading system 10 on the loading frame 11, the vertical loading system 10 is used to apply axial stress / displacement to the sample 7, a confining pressure exhaust system 9 on the top of the confining pressure chamber 4, an active confining pressure control system 3 on one side of the bottom of the confining pressure chamber 4, a confining pressure intake system 14 and a vacuum extraction system 15 on the other side of the bottom of the confining pressure chamber 4, and a monitoring mechanism inside the confining pressure chamber 4.
[0021] The confining chamber 4 uses stainless steel as its outer shell, specifically precipitation-hardening stainless steel, which boasts high strength and hardness, allowing for reduced wall thickness. Its coefficient of thermal expansion is significantly lower than that of 304 steel, resulting in more controllable thermal stress and good fatigue and corrosion resistance. Furthermore, the isolation chamber 6 also uses stainless steel as its outer shell, specifically 304 austenitic stainless steel, which offers moderate cost and good vacuum performance.
[0022] This invention enables simultaneous testing of the physical and mechanical properties of simulated lunar soil under high vacuum and extreme temperature variations. Through the confining pressure inlet system 14 and the confining pressure outlet system 9, air replacement is maximized, offering advantages such as high efficiency, thorough replacement, and stable flow. Cold inert gas enters the bottom of the confining pressure chamber 4; due to momentum, it may mix slightly with the bottom air, but quickly settles due to density differences, forming a relatively clear, bottom-up gas interface. Under continuous gas supply, this interface rises steadily; below the interface is primarily inert gas, while above is compressed and discharged air. Precise control of the confining pressure is achieved through the active confining pressure control system 3, effectively avoiding temperature interference. The isolation chamber 6 isolates heat, reducing heat loss during temperature control and meeting green, low-carbon, and environmentally friendly requirements. By setting up the sample top control system 8 and the sample base control system 2 between the samples 7, uneven heating of the soil or the reproduction of the large temperature gradients present on the surface of the moon and other extraterrestrial bodies (such as Mars) can be achieved.
[0023] Further optimization of the scheme: The sample base control system 2 includes a sample 7 base fixed to the top surface of the base 1. The top surface of the sample 7 base is provided with a cooling element 202. The top surface of the cooling element 202 is provided with a first oxygen-free copper 201. The top surface of the first oxygen-free copper 201 is provided with a sample 7. The base 1 is provided with a water chiller 204. The water chiller 204 is connected to multiple water cooling pipes 203. The water cooling pipes 203 are located below the cooling element 202.
[0024] The design was further optimized by incorporating 360° circumferential needle-shaped baffles within the water-cooling tube 203. The cross-section of the water-cooling tube 203 was designed as an advanced cold plate with 360° circumferential needle-shaped baffles.
[0025] The cooling element 202 is composed of Peltier components, with its cooling end close to the first oxygen-free copper 201. The first oxygen-free copper 201 has good thermal conductivity, enabling effective heat transfer and ensuring the cooling of sample 7. The water-cooling pipe 203 is arranged in a multi-channel parallel configuration, continuously circulating heat away through the water chiller 204. The integrated multi-channel parallel water circuit and 360° circumferential needle-shaped turbulence column ensure that the coolant has no dead zones in the flow field, resulting in uniform flow velocity, greatly improving heat exchange efficiency, and avoiding local boiling and temperature unevenness.
[0026] Further optimization of the scheme: the sample top seat control system 8 includes a second oxygen-free copper 801 that contacts the top surface of the sample 7. The top surface of the second oxygen-free copper 801 is provided with a heating plate 802. The top surface of the heating plate 802 is provided with an aluminum nitride ceramic 803. The top of the aluminum nitride ceramic 803 abuts against the vertical loading system 10.
[0027] The second oxygen-free copper 801 can effectively transfer the heat from the heating element 802 to the sample 7, while the aluminum nitride ceramic 803 can provide thermal insulation to prevent heat dissipation.
[0028] Further optimization of the scheme: the confining pressure venting system 9 includes a convex arc-shaped air guide 901 that communicates with the top surface of the confining pressure chamber 4. The top of the convex arc-shaped air guide 901 is respectively provided with a first valve 902 and an oxygen sensor 903, with the oxygen sensor 903 located above the first valve 902.
[0029] The convex arc-shaped gas guide 901 is selected as hemispherical or parabolic to better concentrate and discharge the gas to the top during gas replacement, and the oxygen sensor 903 detects the oxygen concentration to determine whether the gas in the suffocation chamber 4 has been completely discharged.
[0030] Further optimization of the scheme: the confining pressure air intake system 14 includes a concave arc-shaped air guide outlet 1401 connected to the bottom of the confining pressure chamber 4. The concave arc-shaped air guide outlet 1401 is connected to a first gas supply pipe 1404. The first gas supply pipe 1404 is connected to an inert gas loading controller 17. A second valve 1402 and a gas flow meter 1403 are respectively provided on the first gas supply pipe 1404. The gas flow meter 1403 is located on the side of the first gas supply pipe 1404 near the concave arc-shaped air guide outlet 1401.
[0031] The concave arc-shaped gas guide 1401 is selected as hemispherical or parabolic. Its function is to transform the incoming nitrogen gas flow from a concentrated jet into a laminar flow that diffuses uniformly along the cross-section of the pressure chamber, thereby achieving efficient and dead-angle-free gas replacement, and monitoring the gas pressure through the pressure sensor 5.
[0032] Further optimizing the scheme, the vacuum pumping system 15 includes a second gas supply pipe 1504, which is connected to a confining pressure chamber connecting pipe connected to the confining pressure chamber 4 and an isolation chamber connecting pipe connected to the isolation chamber 6. The confining pressure chamber connecting pipe is connected to the sample 7. The confining pressure chamber connecting pipe is equipped with a sample vacuum valve 1501, and the isolation chamber 6 connecting pipe is equipped with an isolation chamber valve 1502. The second gas supply pipe 1504 is equipped with a vacuum gauge 1503 and is connected to a vacuum controller 16.
[0033] Vacuum controller 16 is used to evacuate the confining chamber 4 and the isolation chamber 6 respectively.
[0034] Further optimization of the scheme: the confining pressure active control system 3 includes a metal bellows 301 that is connected to the confining pressure chamber 4. A metal limiting tube 302 is provided on the outside of the metal bellows 301. An insulation layer 303 is provided on the outside of the metal limiting tube 302. An actuator 304 is connected to the side of the metal bellows 301 away from the confining pressure chamber 4.
[0035] The metal bellows 301 can achieve good longitudinal deformation, thus enabling effective confining pressure control under the action of the actuator 304. The lateral deformation of the metal bellows 301 is limited by the metal limiting tube 302, and temperature insulation is achieved by the insulation layer 303.
[0036] The scheme has been further optimized, and the monitoring mechanism includes a pressure sensor 5 and a temperature sensor 13 respectively installed on both sides of the sample base control system 2.
[0037] To further optimize the design, an annular heating wire 12 is provided on the outside of the sample base control system 2.
[0038] A method for using an active gas confining pressure triaxial apparatus for simulating extreme lunar environments includes the following steps: S1. Sample 7 installation: Install sample 7 on top of sample base control system 2, and install confining pressure chamber 4 and isolation chamber 6 in sequence to ensure that sample 7 is sealed properly. S2. Vacuum treatment: After the sample 7 is installed, first open the sample vacuum valve 1501, use the vacuum controller 16 to evacuate the inside of the sample 7, and monitor the vacuum level with the vacuum gauge 1503. After the requirement is met, close the sample vacuum valve 1501. Next, open the isolation chamber valve 1502, use the vacuum controller 16 to evacuate the isolation chamber 6, and monitor the vacuum level with the vacuum gauge 1503. After the requirement is met, close the isolation chamber valve 1502 to ensure that both the sample 7 and the isolation chamber 6 are in a vacuum state. S3. Air exchange process: Open the second valve 1402 of the confining pressure inlet system 14 and the first valve 902 of the confining pressure outlet system 9. Then, continuously input low-temperature inert gas through the inert gas loading controller 17. The incoming nitrogen flow is transformed from a concentrated jet into a laminar flow that diffuses evenly along the cross-section of the pressure chamber through the concave arc-shaped guide air outlet 1401. Since the inert gas has a high density due to its low temperature, it continuously pushes the air upwards in an orderly manner. The air is then better gathered and discharged to the top through the convex arc-shaped guide air outlet 901. The oxygen concentration is detected by the oxygen sensor 903 to determine whether the air in the confining pressure chamber 4 has been completely removed, thereby achieving efficient and dead-angle-free gas replacement. After the air has been completely removed, close the second valve 1402 of the confining pressure inlet system 14 and the first valve 902 of the confining pressure outlet system 9. S4. Pressurization of confining pressure: Open the second valve 1402 of the confining pressure intake system 14, and continuously input low-temperature inert gas through the inert gas loading controller 17. The pressure sensor 5 monitors whether the pressure of the confining chamber 4 reaches the preset value. After reaching the preset value, the second valve 1402 is closed. S5. Temperature control: Low temperature conditions can be achieved through the sample base adjustment system 2, which is cooled by the cooling element 202. Its cooling end is close to the first oxygen-free copper 201. The first oxygen-free copper 201 has good thermal conductivity and can achieve effective heat conduction to ensure the cooling of the sample 7. The temperature sensor 13 monitors whether the temperature has reached the preset value. High-temperature conditions can be achieved through the sample top seat control system 8 and the annular heating wire 12. Heating is performed by the heating plate 802. The second oxygen-free copper 801 can effectively transfer the heat of the heating plate 802 to the sample 7, while the aluminum nitride ceramic 803 can provide thermal insulation to prevent heat diffusion. In addition, the annular heating wire 12 provides auxiliary heating, which can accelerate the temperature rise of the sample 7 and promote uniform heating of the sample 7. The temperature sensor 13 monitors whether the temperature has reached the preset value. This invention can simulate the mechanical changes of soil at different temperatures. It can also achieve temperature cycling by making the sample top control system 8 and the base control system work sequentially to simulate the periodic temperature changes of soil on the surface of extraterrestrial bodies such as the moon. In addition, it can also simulate large temperature differences in soil by making the sample top control system 8 and the base control system work simultaneously. S6. Confining Pressure Control: After temperature regulation is completed, since temperature will have a certain impact on the gas, and thus affect the confining pressure of the confining chamber 4, regulation is carried out through the active confining pressure regulation system 3. The active confining pressure regulation system 3 operates according to the following closed-loop logic: First, the active confining pressure regulation system 3 reads the value of temperature sensor 13 in real time. and the temperature value of the previous control cycle. Comparison is performed when the absolute value of the temperature change is detected. When the temperature exceeds a preset threshold ε (e.g., ε = 1.0°C, which can be set according to control accuracy requirements), the confining pressure compensation control program is triggered; then the controller calculates according to the formula... Calculate the theoretical volume compensation amount required to change the metal bellows 301. ,in The volume of the ballast chamber is 4. Then, the controller calculates the volume compensation amount. This is converted into a displacement command for actuator 304; actuator 304 drives metal bellows 301 to produce precise axial extension and contraction, thereby changing its internal volume to achieve the desired result. This enables active adjustment of the overall volume of the ballast chamber 4.
[0039] Specifically, the metal bellows 301, under the constraint of the metal limiting tube 302, mainly undergoes axial deformation, and its nominal inner diameter is... To achieve volume change The required theoretical axial displacement According to the formula During this process, the metal limiting tube 302 restricts the radial deformation of the metal bellows 301, ensuring that it undergoes stable axial deformation along a predetermined path; the insulation layer 303 is used to reduce the heat exchange between the metal bellows 301 and the outside environment, and the metal bellows 301 can achieve better longitudinal deformation, thereby changing the volume to regulate the confining pressure; after the actuator 304 completes its action, the system collects the actual pressure value inside the confining chamber 4 in real time through the pressure sensor 5 and compares it with the target confining pressure value; if the pressure error exceeds the allowable range, the system will make fine adjustments based on this deviation until the confining pressure stabilizes at the preset target value, thereby forming a closed-loop control loop of "temperature monitoring - volume compensation - pressure verification"; S7. Pressure / Displacement Loading: After temperature control and confining pressure control are completed, the sample 7 is subjected to loading treatment; the axial force and vertical deformation are recorded by the vertical loading system 10.
[0040] This invention uses an inert gas as the confining pressure medium and incorporates an active pressure compensation system to monitor pressure changes within the pressure chamber in real time and dynamically offset the pressure decay caused by temperature fluctuations. This achieves long-term, high-precision, and stable control of the confining pressure, thereby maximally simulating the vacuum and large temperature variations characteristic of lunar regolith. Furthermore, the isolation chamber 6 and other features ensure minimal heat loss, guaranteeing the accuracy and reliability of the mechanical test data. This invention can simultaneously reproduce the multi-field coupled extreme environment of the lunar surface—high vacuum, extreme high and low temperatures, and low gravity effects (simulated by controlling the confining pressure)—in a terrestrial laboratory environment, and conduct in-situ tests on the physical and mechanical properties of lunar regolith sample 7.
[0041] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.
[0042] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.
Claims
1. An active gas confining pressure triaxial apparatus for simulating extreme lunar environments, characterized in that: The system includes a base (1), a sample base control system (2) on the top surface of the base (1), a sample (7) on the sample base control system (2), a sample top seat control system (8) on the top of the sample (7), a confining pressure chamber (4) outside the sample (7), an isolation chamber (6) on the outside of the confining pressure chamber (4), a loading frame (11) fixed to the top surface of the base (1), a vertical loading system (10) on the loading frame (11), the vertical loading system (10) for applying pressure to the sample (7), a confining pressure exhaust system (9) on the top of the confining pressure chamber (4), a confining pressure active control system (3) on one side of the bottom of the confining pressure chamber (4), a confining pressure intake system (14) and a vacuum pumping system (15) on the other side of the bottom of the confining pressure chamber (4), and a monitoring mechanism inside the confining pressure chamber (4).
2. The active gas confining pressure triaxial apparatus for simulating extreme lunar environments according to claim 1, characterized in that: The sample base control system (2) includes a sample (7) base fixed to the top surface of the base (1). The top surface of the sample (7) base is provided with a cooling element (202). The top surface of the cooling element (202) is provided with a first oxygen-free copper (201). The top surface of the first oxygen-free copper (201) is provided with the sample (7). The base (1) is provided with a water chiller (204). The water chiller (204) is connected to a plurality of water cooling pipes (203). The water cooling pipes (203) are located below the cooling element (202).
3. The active gas confining pressure triaxial apparatus for simulating extreme lunar environments according to claim 2, characterized in that: The water-cooled pipe (203) is provided with a circumferential 360° needle-shaped turbulence column.
4. The active gas confining pressure triaxial apparatus for simulating extreme lunar environments according to claim 1, characterized in that: The sample top seat adjustment system (8) includes a second oxygen-free copper (801) that contacts the top surface of the sample (7). The top surface of the second oxygen-free copper (801) is provided with a heating plate (802). The top surface of the heating plate (802) is provided with aluminum nitride ceramic (803). The top of the aluminum nitride ceramic (803) abuts against the vertical loading system (10).
5. The active gas confining pressure triaxial apparatus for simulating extreme lunar environments according to claim 1, characterized in that: The confining pressure exhaust system (9) includes a convex arc-shaped air guide (901) that communicates with the top surface of the confining pressure chamber (4). The top of the convex arc-shaped air guide (901) is provided with a first valve (902) and an oxygen sensor (903). The oxygen sensor (903) is located above the first valve (902).
6. The active gas confining pressure triaxial apparatus for simulating extreme lunar environments according to claim 1, characterized in that: The confining pressure air intake system (14) includes a concave arc-shaped air guide outlet (1401) connected to the bottom of the confining pressure chamber (4). The concave arc-shaped air guide outlet (1401) is connected to a first gas supply pipe (1404). The first gas supply pipe (1404) is connected to an inert gas loading controller (17). A second valve (1402) and a gas flow meter (1403) are respectively provided on the first gas supply pipe (1404). The gas flow meter (1403) is located on the side of the first gas supply pipe (1404) near the concave arc-shaped air guide outlet (1401).
7. The active gas confining pressure triaxial apparatus for simulating extreme lunar environments according to claim 1, characterized in that: The vacuum pumping system (15) includes a second gas supply pipe (1504), which is connected to a confining pressure chamber connecting pipe connected to the confining pressure chamber (4) and an isolation chamber connecting pipe connected to the isolation chamber (6). The confining pressure chamber (4) connecting pipe is connected to the sample (7). The confining pressure chamber (4) connecting pipe is equipped with a sample vacuum valve (1501), and the isolation chamber connecting pipe is equipped with an isolation chamber valve (1502). The second gas supply pipe (1504) is equipped with a vacuum gauge (1503), and the second gas supply pipe (1504) is connected to a vacuum controller (16).
8. The active gas confining pressure triaxial apparatus for simulating extreme lunar environments according to claim 1, characterized in that: The active pressure control system (3) includes a metal bellows (301) communicating with the confining chamber (4). A metal limiting tube (302) is provided on the outside of the metal bellows (301). An insulation layer (303) is provided on the outside of the metal limiting tube (302). An actuator (304) is connected to the side of the metal bellows (301) away from the confining chamber (4).
9. The active gas confining pressure triaxial apparatus for simulating extreme lunar environments according to claim 1, characterized in that: The monitoring mechanism includes a pressure sensor (5) and a temperature sensor (13) respectively installed on both sides of the sample base control system (2).
10. The active gas confining pressure triaxial apparatus for simulating extreme lunar environments according to claim 1, characterized in that: The sample base control system (2) is provided with an annular heating wire (12) on the outside.