A low-pressure temperature-controlled experimental cabin and experimental method for Mars environment simulation testing

Abstract

The present invention discloses a low-pressure temperature control experimental cabin for Mars environment simulation test and an experimental method, which relates to the technical field of ground simulation equipment for Mars environment and solves the problem of insufficient comprehensive simulation ability of ground simulation equipment for Mars environment, especially in terms of temperature. The experimental cabin of the present invention has an inner and outer double-layer cavity. The upper cover of the experimental cabin is provided with a refrigeration expander and a vacuum baffle valve connected to the inner cavity; the vacuum baffle valve connected to the inner cavity is communicated with the inner cavity body, and the refrigeration expander is connected to the inner cavity body; an outer cavity connection vacuum baffle valve and an outer cavity air intake channel provided on the outer cavity are communicated with the outer cavity, and an inner cavity air intake channel on the outer cavity is communicated with the inner cavity body; a condenser and a heater are provided on the inner cavity body, and a copper cold screen is arranged inside. The refrigeration expander, the condenser and the copper cold screen are connected in sequence. The present invention can fully simulate the surface temperature, gas environment and pressure environment of Mars, make up for the deficiencies of ground simulation experimental devices for Mars environment, and provide equipment support for fields such as aerospace and Mars exploration.

Description

Technical Field

[0001] The present invention relates to the technical field of ground simulation of Martian environment equipment, and specifically to a low-pressure temperature control experimental chamber and an experimental method for Martian environment simulation testing. Background Art

[0002] Mars, as a neighboring planet of the Earth, has a history of more than 5 billion years and occupies an important position in human space exploration and potential immigration. However, the environment on the Martian surface is extremely rugged and complex, posing extremely high requirements for the operation of ground and aerial detection equipment. In particular, the extreme temperature, low pressure, and specific gas composition on Mars jointly pose a huge challenge to the design and function realization of detection equipment.

[0003] Traditional Martian exploration technologies such as Mars rovers are significantly restricted by terrain when operating on the Martian surface, while aerospace facilities such as Martian drones, due to their high mobility and flexibility, offer the possibility of overcoming these terrain challenges. In response to this complex environment, it is particularly important to develop a ground experimental support device that can comprehensively simulate the Martian environment. This device can not only simulate the atmospheric pressure and specific gas environment on Mars but also precisely control extreme temperature conditions, making it a comprehensive experimental system. This system will support the conduct of electrohydrodynamics experiments, plasma physics experiments, and comprehensive performance tests of small aerospace facilities such as Martian drones.

[0004] In the past 20 years, research institutions around the world have designed corresponding experimental platforms for the Martian environment. In the initial stage of the research on Martian unmanned exploration equipment, simulation was the relatively mainstream method chosen by researchers. However, simulation experiments can reflect the dynamic performance of drones from a more intuitive perspective, making up for the possible unreasonable models and inaccurate results of numerical simulation methods.

[0005] In summary, in terms of simulation devices, according to the differences between Mars and the main environmental parameters on the Earth's surface, Martian experimental platforms should be able to simulate the atmospheric environment and temperature. Currently, countries such as the United States, Japan, and China have successively carried out research and design on Martian drone experimental platforms.

[0006] (1) Ames Research Center Tower Experimental Platform: In 2001, the Ames Research Center in the United States initially demonstrated the feasibility of using the vertical takeoff and landing characteristics of rotorcraft drones to detect the rugged terrain on the Martian surface. This experimental platform was set up in the vacuum environment of the Ames Planetary Aeolus Laboratory, and the gas density in the vacuum chamber was pumped to the same level as the Martian atmosphere for experiments, but it did not further integrate temperature and gas composition simulation, and the authenticity of environmental simulation was insufficient.

[0007] (2) Stanford University Lever Test Bench: In 2003, Stanford University in the United States designed a test bench themed on the lever principle to measure the lift of the drone rotor. The test environment was the surface environment of normal temperature and pressure, and no simulation of the Martian environment was carried out.

[0008] (3) University of Tokyo Pendulum Test Bench: In 2004, the University of Tokyo in Japan studied the feasibility of Martian drones. The experimental device was set in a vacuum chamber with a diameter of 2.40 m and a height of 2.73 m. The simulation of gas composition and temperature was not reflected in the experimental process.

[0009] (4) University of Maryland Tower Test Bench: In 2015, the University of Maryland in the United States tested the hovering performance of small-scale Martian drones. Its test bench was built in a vacuum chamber with a height of about 0.91 m. The simulation of gas composition and temperature was not reflected in the experimental process.

[0010] (5) Harbin Institute of Technology Lever Test Bench: Harbin Institute of Technology has achieved a lot in the pneumatic characteristic test device of Martian drones. For example, on the basis of the lever test bench of Stanford University, the lift generated by the rotor was accurately measured through a balance plate and bearings. At the same time, a lot of improvements were also proposed on the pendulum test bench of the University of Tokyo. However, all the achievements only measured and simulated the pressure and CO2 environment of Mars, and the simulation application for other environments was limited.

[0011] (6) "Ingenuity" Martian Drone Test Bench: In 2021, NASA's Martian drone "Ingenuity" achieved autonomous flight on Mars for the first time. The test environment simulation process was carried out in a vacuum chamber. The Martian atmospheric environment was simulated by filling carbon dioxide, and it was verified by analysis that the experimental results under room temperature conditions were close to the aerodynamic performance under the low temperature conditions of the actual Mars.

[0012] It can be seen that most test benches can meet the simulation of the low atmospheric density on Mars. For the simulation of atmospheric composition, most research institutions have chosen air as the gas in the airtight chamber, while Harbin Institute of Technology and the Jet Propulsion Laboratory of the California Institute of Technology in the United States have chosen carbon dioxide, which dominates absolutely on Mars, for simulation, undoubtedly making the simulated gas environment closer to the real Martian atmosphere. However, the vast majority of test benches have not achieved the simulation of the low and high temperature environments on Mars.

[0013] In addition, most existing precision vacuum equipment has deficiencies in simulating the extreme temperature conditions on the Martian surface and sky and their impacts on equipment performance. For example:

[0014] (1) The horizontal thermal vacuum chamber for low-pressure and CO2 atmosphere environment developed by Beijing Institute of Spacecraft Environment Engineering is an important equipment for the test and research of Mars probes in China at present. The diameter of the chamber is 4200 mm and the length is 5000 mm. This equipment can simulate a stable CO2 atmosphere and low-pressure environment, but it cannot simulate extreme temperature environments.

[0015] (2) The STC space environment simulator of the Rutherford Appleton Laboratory in the UK has a diameter of 3 m and a length of about 5.5 m. This space environment simulator is equipped with a horizontal chamber, a heat sink of the gas nitrogen temperature control system, a pressure control system, a solar simulator system and a blower system. The temperature of the heat sink is -110 to 150 °C, the pressure control system can maintain the pressure at 700 Pa, and the blower system can control the flow rate of the carbon dioxide gas at about 10 m / s. This equipment was once used for the test of the Beagle 2 Mars lander, but due to its large space scale, it is impossible to obtain a lower system pressure.

[0016] (3) The JPL 10-foot space environment simulator in the United States was once used for the tests of the "Pathfinder", "Spirit" and "Opportunity" Mars probes. The space environment simulator is equipped with a temperature-controlled cold plate for simulating space temperature. The main indicators are that the atmospheric temperature range is -130 to 20 °C and the nitrogen gas pressure is 100 to 1300 Pa. The subsequent "Curiosity" Mars rover carried out thermal tests in a 25-ft space environment simulator, with an external diameter of 7.5 m, a height of 21 m, an internal test space diameter of 6 m and a height of 7.5 m, and the temperature of the heat sink is -180 to 100 °C. Unfortunately, the temperature simulation ability of this simulator did not reach the upper limit of the Mars temperature.

[0017] In summary, although the existing experimental platforms have their own characteristics, there are generally deficiencies in not fully simulating the Mars environment, especially in the simulation of temperature. Summary of the Invention

[0018] In order to solve the problem of insufficient simulation of the Mars environment temperature by the existing experimental platforms mentioned above, the present invention hereby provides a low-pressure temperature-controlled experimental chamber and experimental method for Mars environment simulation testing. The present invention can fully simulate the surface temperature, gas environment and pressure environment of Mars, fill the deficiencies of the ground simulation experimental devices for the Mars environment in China, and provide basic experimental equipment support for fields such as aerospace and Mars exploration.

[0019] The present invention provides a low-pressure temperature control experimental chamber for Mars environment simulation tests, which specifically includes an upper cover of the experimental chamber, an inner cavity of the experimental chamber, and an outer cavity of the experimental chamber. The upper cover of the experimental chamber is arranged at the upper end of the outer cavity of the experimental chamber; the inner cavity of the experimental chamber is arranged inside the outer cavity of the experimental chamber and is hoisted below the upper cover of the experimental chamber; the upper cover of the experimental chamber includes an upper end cover, on which a refrigeration expander and an inner cavity connecting vacuum baffle valve are arranged; the inner cavity connecting vacuum baffle valve is communicated with the inner cavity of the experimental chamber, and the refrigeration expander is connected with the inner cavity of the experimental chamber; the outer cavity of the experimental chamber includes an outer layer cavity, on which an outer cavity connecting vacuum baffle valve, an outer cavity rear-view vacuum observation window, an inner cavity air inlet channel, and an outer cavity air inlet channel are arranged. The outer cavity connecting vacuum baffle valve and the outer cavity air inlet channel are both communicated with the inside of the outer layer cavity, and the inner cavity air inlet channel is communicated with the inner cavity of the experimental chamber; the inner cavity of the experimental chamber includes an inner cavity body, on which a plurality of condensers are arranged, heaters are arranged on the condensers, a copper cold shield is arranged inside the inner cavity body, and the refrigeration expander, the condensers, and the copper cold shield are connected in sequence.

[0020] Furthermore, a vacuum bellows is sleeved on the condenser.

[0021] Furthermore, the copper cold shield is suspended inside the inner cavity body by bolts, and a cold shield door is arranged on the copper cold shield.

[0022] Furthermore, the distance between the copper cold shield and the inner wall of the inner cavity body is 3 - 5 mm.

[0023] Furthermore, the inner cavity connecting vacuum baffle valve is communicated with the inner cavity body through a vacuum air pipe, and expansion bends are arranged on the vacuum air pipe, the inner cavity air inlet channel, and the outer cavity air inlet channel.

[0024] Furthermore, an experimental inner cavity door, an inner cavity top-view vacuum observation window, and an inner cavity rear-view vacuum observation window are arranged on the inner cavity body, and an inner cavity front-view vacuum observation window is arranged on the experimental inner cavity door.

[0025] Furthermore, a low-voltage vacuum aviation plug and a high-voltage vacuum aviation plug are arranged at the upper end of the inner cavity body.

[0026] Furthermore, an experimental chamber door is arranged on the outer layer cavity, and an outer cavity front-view vacuum observation window is arranged on the experimental chamber door.

[0027] Furthermore, a high-voltage electric vacuum aviation plug, a low-voltage electric vacuum aviation plug, a top-view vacuum observation window, and a pressure gauge are arranged on the upper end cover. The low-voltage electric vacuum aviation plug is connected with the heater; the lower surface of the upper end cover is connected with the inner cavity body through a plurality of threaded suspension rods.

[0028] An experimental method using the above-mentioned low-pressure temperature control experimental chamber for Mars environment simulation tests includes the following steps:

[0029] Place the experimental object in the copper cold shield, evacuate the inner cavity and the outer cavity separately, and after reaching the required vacuum degree for the experiment, fill it with CO2 gas; stop inflating after reaching the predetermined pressure;

[0030] Start the refrigeration expander to start the refrigeration operation or start the heater to start the heating operation;

[0031] After the experiment is completed, turn off the refrigeration expander or the heater. Wait for the temperature of the cabin to return to room temperature. After the gas enters the cavity, then open the cabin door and take out the experimental piece.

[0032] The beneficial effects of the low-pressure temperature control experimental cabin and experimental method for Mars environment simulation test described in the present invention are as follows:

[0033] (1) The low-pressure temperature control experimental cabin and experimental method for Mars environment simulation test described in the present invention overcome the problem of insufficient simulation of the Mars environment temperature by the existing experimental bench. It can achieve an ultra-low vacuum degree in terms of the cavity vacuum degree. The inner cavity and the outer cavity of the experimental cabin are evacuated by a molecular pump. The ultimate vacuum of the outer cavity of the experimental cabin is 2.6×10 -4 Pa, and the ultimate vacuum of the inner cavity of the experimental cabin is 3.4×10 -4 Pa. The time from atmospheric pressure to 5.0×10 -3 Pa is less than 35 minutes; in terms of temperature control, it can achieve a large-span temperature control. The refrigeration expander transfers the cold quantity to the condenser through a flexible copper cold conduction belt, and the condenser transfers the cold quantity to the copper cold shield to cool the test area. The heat generated by the heater is conducted to the copper cold shield through the condenser to heat the experimental area. The temperature range in the inner cavity of the experimental cabin is as low as -150°C and as high as 120°C, and the temperature change rate is less than 1°C / min;

[0034] (2) The low-pressure temperature control experimental cabin and experimental method for Mars environment simulation test described in the present invention support the input of various gas components, and can flexibly adjust the gas components in the space environment of the cavity, such as the gas components of the Mars environment mainly composed of carbon dioxide;

[0035] (3) The low-pressure temperature control experimental cabin and experimental method for Mars environment simulation test described in the present invention can actively disassemble the inner cavity of the experimental cabin and only use the outer cavity of the experimental cabin for operation to obtain a larger and more intuitive experimental operation space when not using the temperature control system. The low-voltage vacuum aviation plugs reserved in the cavity support the power supply of various sensors inside the cavity, and the high-voltage vacuum aviation plugs can meet the strong voltage experiments within 30 kV in the cavity. Description of the Drawings

[0036] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention.

[0037] In the accompanying drawings:

[0038] Figure 1 is an assembly schematic diagram of a low-pressure temperature-controlled experimental chamber for Mars environment simulation test according to the present invention;

[0039] Figure 2 is a three-dimensional structure schematic diagram of a low-pressure temperature-controlled experimental chamber for Mars environment simulation test according to the present invention;

[0040] Figure 3 is a top view of the outer chamber of the experimental chamber of a low-pressure temperature-controlled experimental chamber for Mars environment simulation test according to the present invention;

[0041] Figure 4 is a front view of the outer chamber of the experimental chamber of a low-pressure temperature-controlled experimental chamber for Mars environment simulation test according to the present invention;

[0042] Figure 5 is a left view of the outer chamber of the experimental chamber of a low-pressure temperature-controlled experimental chamber for Mars environment simulation test according to the present invention;

[0043] Figure 6 is a three-dimensional structure schematic diagram of the inner chamber of the experimental chamber of a low-pressure temperature-controlled experimental chamber for Mars environment simulation test according to the present invention;

[0044] Figure 7 is a top view of the inner chamber of the experimental chamber of a low-pressure temperature-controlled experimental chamber for Mars environment simulation test according to the present invention;

[0045] Figure 8 is a front view of the inner chamber of the experimental chamber of a low-pressure temperature-controlled experimental chamber for Mars environment simulation test according to the present invention;

[0046] Figure 9 is a left view of the inner chamber of the experimental chamber of a low-pressure temperature-controlled experimental chamber for Mars environment simulation test according to the present invention;

[0047] Figure 10 is a sectional view of the low-pressure temperature-controlled experimental chamber for Mars environment simulation test according to the present invention at Figure 4 section A-A;

[0048] Figure 11 is a sectional view of the low-pressure temperature-controlled experimental chamber for Mars environment simulation test according to the present invention at Figure 5 section B-B;

[0049] Wherein: 1 - upper cover of the experimental module, 2 - inner cavity of the experimental module, 3 - outer cavity of the experimental module, 101 - outer layer cavity, 102 - upper end cover, 103 - experimental module door, 104 - main view vacuum observation window of the outer cavity, 105 - top view vacuum observation window, 106 - refrigeration expander, 107 - high-voltage electrical vacuum connector, 108 - low-voltage electrical vacuum connector, 109 - inner cavity connecting vacuum baffle valve, 110 - outer cavity connecting vacuum baffle valve, 111 - pressure gauge, 112 - lifting ring, 113 - door hinge of the module, 114 - reserved interface, 115 - rear view vacuum observation window of the outer cavity, 116 - inner cavity air intake channel, 117 - outer cavity air intake channel, 201 - inner cavity of the experimental module, 202 - inner cavity door of the experiment, 203 - main view vacuum observation window of the inner cavity, 204 - top view vacuum observation window of the inner cavity, 205 - rear view vacuum observation window of the inner cavity, 206 - low-voltage vacuum connector, 207 - high-voltage vacuum connector, 208 - heater, 209 - condenser, 210 - vacuum bellows, 211 - lifting lug, 212 - copper cold shield, 213 - cold shield door, 214 - vacuum air pipe, 215 - threaded suspension rod. Detailed implementation mode

[0050] Next, the technical solution of the present invention will be clearly and completely described in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of them. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative work shall fall within the protection scope of the present invention.

[0051] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present invention. In addition, the terms "first", "second", "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0052] In the description of the present invention, it should be noted that unless otherwise clearly specified and limited, the terms "installation", "connection", "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0053] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0054] Specific Embodiment 1: Refer to Figures 1-11 This embodiment will be specifically described. A low-pressure temperature-controlled experimental chamber for Mars environment simulation test described in this embodiment specifically includes an upper cover 1 of the experimental chamber, an inner cavity 2 of the experimental chamber, and an outer cavity 3 of the experimental chamber. The upper cover 1 of the experimental chamber is arranged at the upper end of the outer cavity 3 of the experimental chamber; the inner cavity 2 of the experimental chamber is arranged inside the outer cavity 3 of the experimental chamber and is hoisted below the upper cover 1 of the experimental chamber; the inner cavity 2 of the experimental chamber is the main component for realizing environmental temperature control. If the experimental environment does not require temperature control (only conducting experiments at room temperature), it is possible to choose to remove the inner cavity 2 of the experimental chamber from the lower end of the upper cover 1 of the experimental chamber and only use the experimental chamber composed of the upper cover 1 of the experimental chamber and the outer cavity 3 of the experimental chamber to expand the experimental section capacity in the vacuum chamber.

[0055] The upper cover 1 of the experimental chamber includes an upper end cover 102. A refrigeration expander 106 and an inner cavity connecting vacuum baffle valve 109 are arranged on the upper end cover 102. The refrigeration expander 106 is encapsulated on the upper end plate 102 through a vacuum flange; the inner cavity connecting vacuum baffle valve 109 is communicated with the inner cavity 2 of the experimental chamber, and the inner cavity 2 of the experimental chamber is evacuated through the inner cavity connecting vacuum baffle valve 109 to control the vacuum degree inside the inner cavity 201; the refrigeration expander 106 is connected to an external GM refrigerator, and the refrigeration expander 106 is connected to the inner cavity 2 of the experimental chamber, and the inner cavity 2 of the experimental chamber is cooled through the refrigeration expander 106; the cavity walls of the inner cavity 2 of the experimental chamber, the outer cavity 3 of the experimental chamber, and the upper end cover 102 are all made of 10-mm-thick steel plates.

[0056] The outer cavity 3 of the experimental chamber includes an outer layer cavity 101. An outer cavity connecting vacuum baffle valve 110, an outer cavity rear-view vacuum observation window 115, an inner cavity air inlet channel 116, and an outer cavity air inlet channel 117 are arranged on the outer layer cavity 101. Both the outer cavity connecting vacuum baffle valve 110 and the outer cavity air inlet channel 117 are communicated with the inside of the outer layer cavity 101. The outer cavity connecting vacuum baffle valve 110 evacuates the inside of the outer layer cavity 101 to control the vacuum degree inside the outer layer cavity 101; experimental gas is introduced into the outer layer cavity 101 through the outer cavity air inlet channel 117; the inner cavity air inlet channel 116 is communicated with the inner cavity 2 of the experimental chamber, and experimental gas is introduced into the inner cavity 2 of the experimental chamber through the inner cavity air inlet channel 116; both the inner cavity air inlet channel 116 and the outer cavity air inlet channel 117 are composed of a needle valve, a vacuum flange, and a stainless steel vacuum tube. Both the inner cavity connecting vacuum baffle valve 109 and the outer cavity connecting vacuum baffle valve 110 are connected to an external molecular combination pump with a fore pump.

[0057] The experimental chamber's inner chamber 2 includes an inner chamber 201, which is equipped with several condensers 209, each of which is equipped with a heater 208. A copper cold shield 212 is located within the inner chamber 201. The flange at the primary cold head of the refrigeration expander 106 is connected to the condensers 209 in the inner chamber 201 via a flexible copper cold strip, secured with bolts. The condensers 209 are bolted to the copper cold shield 212 within the inner chamber 201. The copper cold shield 212 is a box-shaped structure welded from 5mm-thick copper steel plates. The cooling energy generated by the compression and expansion of the refrigerator gas is transferred to the condensers 209 located in the inner chamber 201 via the primary cold head of the refrigeration expander 106 and the flexible copper cold strip. Finally, the cooling energy is evenly transferred to the copper cold shield 212, achieving uniform low temperature control in the experimental area through radiation heat transfer and natural convection. The heat generated by the heater 208 is evenly transferred to the copper cold screen 212 through the condenser 209, and the high temperature uniformity of the experimental area is achieved through radiation heat transfer and natural convection heat transfer.

[0058] The condenser 209 is sheathed with a vacuum bellows 210 , and the condenser 209 exposed outside the inner cavity 201 is isolated from the inner space of the outer cavity 101 by the vacuum bellows 210 .

[0059] The copper cold screen 212 is suspended in the inner cavity 201 by bolts, and the distance between the copper cold screen 212 and the inner wall of the inner cavity 201 is 3-5 mm. A cold screen door 213 is provided on the copper cold screen 212.

[0060] The inner cavity is connected to the vacuum baffle valve 109 and communicates with the inner cavity 201 via a vacuum airway steel pipe 214. The vacuum airway steel pipe 214, the inner cavity air inlet channel 116, and the outer cavity air inlet channel 117 are provided with an expansion bend structure, i.e., there is at least one "匚"-shaped pipe in the vertical direction. In actual experiments, thermal expansion and contraction caused by temperature changes are often encountered. This problem can be effectively solved by bending the pipe to form an expansion bend. This design allows the pipe to expand and contract freely when the temperature changes without causing damage to the pipe system.

[0061] The inner cavity body 201 is provided with an experimental inner cavity door 202, an inner cavity top-view vacuum observation window 204 and an inner cavity rear-view vacuum observation window 205, and the experimental inner cavity door 202 is provided with an inner cavity main-view vacuum observation window 203; the copper cold screen 212 is provided with through holes at positions corresponding to the inner cavity main-view vacuum observation window 203, the inner cavity top-view vacuum observation window 204 and the inner cavity rear-view vacuum observation window 205, and the diameter of the through holes is the same as the size of the observation windows on the inner cavity body 201. The copper cold screen 212 is also provided with through holes for electrical connection and gas pipeline passage; the inner cavity rear-view vacuum observation window 205 and the outer cavity rear-view vacuum observation window 115 are coaxially arranged.

[0062] A low-voltage vacuum aviation plug 206 and a high-voltage vacuum aviation plug 207 are provided at the upper end of the inner cavity 201 , and the devices inside the inner cavity 201 are powered by the low-voltage vacuum aviation plug 206 and the high-voltage vacuum aviation plug 207 .

[0063] The outer cavity 101 is provided with an experimental cabin door 103, which is rotatably connected to the outer cavity 101 through a cabin hinge; the experimental cabin door 103 is provided with an outer cavity main view vacuum observation window 104, which is coaxially arranged with the inner cavity main view vacuum observation window 203.

[0064] The upper end cover 102 is provided with a high-voltage electric vacuum aviation plug 107, a low-voltage electric vacuum aviation plug 108, a top-view vacuum observation window 105, a pressure gauge 111 and several hanging rings 112; the pressure gauge 111 is a high-precision pressure gauge, which is installed on the upper end plate 102 through a vacuum flange and is connected to the cavity 2 in the experimental cabin through a stainless steel pipe, and is used to display the pressure of the cavity 2 in the experimental cabin in real time; when a double-layer cavity including the cavity 2 in the experimental cabin is used for experiments, the vacuum degree in the cavity 3 outside the experimental cabin is measured by the pressure gauge on the molecular pump. When only a single-layer cavity of the cavity 3 outside the experimental cabin is used for experiments, the cavity 2 in the experimental cabin is disassembled, and the pressure gauge 111 is connected to the space inside the outer cavity, and the pressure value in the cavity 3 outside the experimental cabin can be read through the pressure gauge 111. The experimental equipment in the outer cavity 101 is powered by a high-voltage vacuum aviation plug 107 and a low-voltage vacuum aviation plug 108, wherein the heater 208 is electrically connected to the outside of the experimental chamber through the pins of the low-voltage vacuum aviation plug 108, thereby controlling the power of the heater 208; the top-view vacuum observation window 105 and the inner cavity top-view vacuum observation window 204 are coaxially arranged; the lifting ring 112 is used to lift the upper end cover 102.

[0065] The lower surface of the upper end cover 102 is connected to the inner cavity 201 through a plurality of threaded suspension rods 215 ; a plurality of lifting ears 211 are provided on the inner cavity 201 , and the lower ends of the threaded suspension rods 215 are connected to the lifting ears 211 .

[0066] The upper end cover 102 is further provided with a reserved interface 114 .

[0067] An experimental method using the aforementioned low-pressure temperature-controlled experimental chamber for Mars environment simulation testing includes the following steps:

[0068] The experimental object is placed in the copper cold shield 212, and the inner cavity 201 and the outer cavity 101 are evacuated separately. After reaching the vacuum degree required by the experiment, CO2 gas is filled in. When the predetermined pressure is reached, the inflation is stopped.

[0069] Start the refrigeration expander 106 to start the cooling operation or start the heater 208 to start the heating operation;

[0070] After the experiment is completed, turn off the refrigeration expander 106 or the heater 208. Wait for the temperature of the cabin to return to room temperature. After the gas enters the cavity, then open the cabin door and take out the test piece.

[0071] The specific experimental process of the low-pressure temperature-controlled experimental cabin for Mars environment simulation test described in the present invention is as follows:

[0072] Detailed operation process under refrigeration condition:

[0073] Under the refrigeration condition, it simulates the low-temperature environment on Mars, the working medium is CO2, and the pressure is 1000 Pa.

[0074] Open the experimental cabin door 103, then open the experimental inner cavity door 202 and the cold shield door 213 in sequence. Place the test object in the copper cold shield 212, and then lock the cold shield door 213, the experimental inner cavity door 202 and the experimental cabin door 103. It is recommended to cover the main viewing vacuum observation window 104 and the top-down vacuum observation window 105 of the outer cavity during the experiment, and open the optical window for observation or lighting according to needs.

[0075] Connect the high-voltage electric vacuum aviation plug 107, the temperature display instrument, the vacuum gauge, the heater 208 and the low-voltage electric vacuum aviation plug 108 to ensure the correct connection of the electrical equipment.

[0076] Confirm that all valves are in the closed state. Use the molecular pump to evacuate the inner cavity 201 and the outer cavity 101 respectively. After reaching the required vacuum degree for the experiment, prepare to fill in CO2 gas. Slowly introduce the gas through the inner cavity air inlet channel 116 and the outer cavity air inlet channel 117, observe the pressure of the vacuum gauge, and close the valve to stop inflating after reaching 1000 Pa.

[0077] Turn on the compressor and start the refrigeration expander 106 to start the refrigeration operation. The temperature is monitored by the temperature display instrument. If a higher temperature is required, the input voltage of the heater 208 can be adjusted to control the power.

[0078] After the experiment is completed, turn off the compressor and wait for the temperature of the cabin to return to room temperature. Slowly open the inner cavity connecting vacuum baffle valve 109. After the gas enters the cavity, then open the cabin door and take out the test piece.

[0079] Detailed operation process under heating condition:

[0080] This embodiment shows the operation process of the equipment in the heating state, simulating the high-temperature environment on Mars, the working medium is CO2, and the pressure is 1000 Pa.

[0081] Open the experimental cabin door 103, the experimental inner cavity door 202 and the cold shield door 213. Place the test object in the copper cold shield 212, and then lock all the doors. Cover the main viewing vacuum observation window 104 and the top-down vacuum observation window 105 of the outer cavity to reduce the light and heat interference.

[0082] The inner cavity 201 and the outer cavity 101 are evacuated separately using a molecular pump, and CO2 gas is injected through the inner cavity air inlet channel 116 and the outer cavity air inlet channel 117 to reach a pressure of 1000 Pa.

[0083] The heater 208 is turned on and the temperature change is monitored by a temperature display. The input voltage of the heater 208 is adjusted as needed to control the power of the heater 208 until the desired experimental temperature is reached.

[0084] After the experiment, turn off the heater power supply and wait for the temperature to drop to room temperature naturally. Slowly open the inner cavity vacuum baffle valve 109 and wait for the gas to enter the cavity before opening the hatch.

[0085] During the above-mentioned experiment, the gas environment is divided into two modes. The first is an experiment in a closed gas environment. During the test, the required gas is introduced into the experimental chamber. After adjusting the pressure, the needle valves on the inner cavity air inlet channel 116 and the outer cavity air inlet channel 117 are closed to stop the gas supply and turn off the vacuum pump. The experiment is carried out after the gas environment in the environment is stable. In addition, the second is an experiment in a flowing gas environment. A fixed flow of gas is introduced through the inner cavity air inlet channel 116 and the outer cavity air inlet channel 117. At the same time, the vacuum pump is turned on to stabilize the pressure inside the cavity. After the pressure is stabilized, the experiment is carried out. The inner cavity air inlet channel 116 and the outer cavity air inlet channel 117 are externally connected to a multi-branch pipeline. Each branch is equipped with a flow meter, a pressure reducing valve and a single-component gas cylinder. The gas components simulating the Martian environment are prepared through flow control. The gas components include carbon dioxide, nitrogen, argon and oxygen.

[0086] Detailed operation process after the inner cavity is removed:

[0087] This operation procedure does not use the inner cavity to perform experiments, so as to provide a larger experimental space and is suitable for large experiments that do not require temperature control.

[0088] Follow the steps below to disassemble the inner cavity 201: open the experimental cabin door 103, loosen the M6 screws and remove the KF25 clamp, use the lifting equipment to lift the inner cavity 201 out of the outer cavity 101 through the lifting ring 112, avoid colliding with the inner cavity main view vacuum observation window 203 and the inner cavity top view vacuum observation window 204 of the inner cavity 201, and place the inner cavity 201 stably in a safe position.

[0089] All electrical interfaces (low-voltage vacuum aviation plug 206 and high-voltage vacuum aviation plug 207 ) and pipelines connected to the inner cavity 201 are removed to complete the separation of the inner cavity 201 from the outer cavity 101 .

[0090] After the inner cavity body 201 is removed, reset the upper end cover 102 and lock the experimental cabin door 103. Confirm that all valves are closed, adjust the vacuum and gas environment according to the experimental requirements, and start the experimental operation.

[0091] After the experiment is completed, slowly open the outer cavity connecting vacuum baffle valve 110 in accordance with the safety procedure to restore the outer cavity body 101 to atmospheric pressure, and take out the test piece.

[0092] Summarizing the above embodiments, a low-pressure temperature-controlled experimental cabin and experimental method for Mars environment simulation test according to the present invention overcomes the problem of insufficient simulation of the Mars environment temperature by existing test benches. It can achieve an ultra-low vacuum degree in terms of the cavity vacuum degree. The inner cavity body 2 and the outer cavity body 3 of the experimental cabin are evacuated by a molecular pump. The ultimate vacuum of the outer cavity body 3 of the experimental cabin is 2.6×10 -4 Pa, and the ultimate vacuum of the inner cavity body 2 of the experimental cabin is 3.4×10 -4 Pa. The time taken to pump from atmospheric pressure to 5.0×10 -3 Pa is less than 35 minutes; in terms of temperature control, it can achieve a large-span temperature control. The refrigeration expander 106 transfers the cold quantity to the condenser 209 through a flexible copper cold conduction belt, and the condenser 209 transfers the cold quantity to the copper cold screen to cool the test area. The heat generated by the heater 208 is conducted to the copper cold screen through the condenser 209 to heat the experimental area. The temperature range inside the inner cavity body 2 of the experimental cabin is as low as -150°C and as high as 120°C, and the temperature change rate is less than 1°C / min; a low-pressure temperature-controlled experimental cabin and experimental method for Mars environment simulation test according to the present invention supports the input of various gas components and can flexibly regulate the gas components in the inner space environment of the cavity, such as the gas components of the Mars environment mainly composed of carbon dioxide; a low-pressure temperature-controlled experimental cabin and experimental method for Mars environment simulation test according to the present invention can actively disassemble the inner cavity body of the experimental cabin and only use the outer cavity body of the experimental cabin for operation to obtain a larger and more intuitive experimental operation space when the temperature control system is not used. The low-voltage electrical vacuum connectors reserved in the cavity support the power supply of various sensors inside the cavity, and the high-voltage electrical vacuum connectors can meet the high-voltage experiments within 30 kV inside the cavity.

[0093] The specific embodiments described above further elaborate on the purpose, technical solutions, and beneficial effects of the present invention. It should be understood that the above are only specific embodiments of the present invention and are not used to limit the invention. It can also be a reasonable combination of the features described in the above embodiments. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims

1. A low-pressure temperature-controlled experimental chamber for Mars environment simulation tests, characterized in that: It includes the upper cover (1) of the experimental module, the inner cavity (2) of the experimental module, and the outer cavity (3) of the experimental module. The upper cover (1) of the experimental module is provided at the upper end of the outer cavity (3) of the experimental module; the inner cavity (2) of the experimental module is arranged inside the outer cavity (3) of the experimental module and is hoisted below the upper cover (1) of the experimental module; the upper cover (1) of the experimental module includes an upper end cover (102), and a refrigeration expander (106) and an inner cavity connecting vacuum baffle valve (109) are provided on the upper end cover (102); the inner cavity connecting vacuum baffle valve (109) is communicated with the inner cavity (2) of the experimental module, and the refrigeration expander (106) is connected with the inner cavity (2) of the experimental module; The outer cavity (3) of the experimental module includes an outer layer cavity (101), and an outer cavity connecting vacuum baffle valve (110), an outer cavity rear-view vacuum observation window (115), an inner cavity air inlet channel (116), and an outer cavity air inlet channel (117) are provided on the outer layer cavity (101). Both the outer cavity connecting vacuum baffle valve (110) and the outer cavity air inlet channel (117) are communicated with the inside of the outer layer cavity (101), and the inner cavity air inlet channel (116) is communicated with the inner cavity (2) of the experimental module; The inner cavity (2) of the experimental module includes an inner cavity body (201), and a plurality of condensers (209) are provided on the inner cavity body (201). A heater (208) is provided on the condenser (209). A copper cold shield (212) is arranged inside the inner cavity body (201). The refrigeration expander (106), the condenser (209), and the copper cold shield (212) are connected in sequence; The copper cold shield (212) is suspended inside the inner cavity body (201) by bolts, and a cold shield door (213) is provided on the copper cold shield (212); An experimental inner cavity door (202), an inner cavity top-view vacuum observation window (204), and an inner cavity rear-view vacuum observation window (205) are provided on the inner cavity body (201), and an inner cavity front-view vacuum observation window (203) is provided on the experimental inner cavity door (202).

2. The low-pressure temperature control experimental chamber for Mars environment simulation test according to claim 1, wherein: A vacuum bellows (210) is sleeved on the condenser (209).

3. The low-pressure temperature control experimental chamber for Mars environment simulation test according to claim 1, characterized in that: The distance between the copper cold shield (212) and the inner wall of the inner cavity body (201) is 3 - 5 mm.

4. The low-pressure temperature control experimental chamber for Mars environment simulation test according to claim 1, characterized in that: The inner cavity connecting vacuum baffle valve (109) is communicated with the inner cavity body (201) through a vacuum air pipe (214), and expansion bend structures are provided on the vacuum air pipe (214), the inner cavity air inlet channel (116), and the outer cavity air inlet channel (117).

5. The low-pressure temperature-controlled experimental chamber for Mars environment simulation test according to claim 1, characterized in that: A low-voltage vacuum aviation plug (206) and a high-voltage vacuum aviation plug (207) are provided at the upper end of the inner cavity body (201).

6. The low-pressure temperature control experimental chamber for Mars environment simulation test according to claim 1, characterized in that: An experimental module door (103) is provided on the outer layer cavity (101), and an outer cavity front-view vacuum observation window (104) is provided on the experimental module door (103).

7. The low-pressure temperature control experimental chamber for Mars environment simulation test according to claim 1, characterized in that: A high-voltage electric vacuum aviation plug (107), a low-voltage electric vacuum aviation plug (108), a top-view vacuum observation window (105), and a pressure gauge (111) are provided on the upper end cover (102). The low-voltage electric vacuum aviation plug (108) is connected with the heater (208); the lower surface of the upper end cover (102) is connected with the inner cavity body (201) through a plurality of threaded suspension rods (215).

8. An experimental method using the low-pressure temperature control experimental chamber for Mars environment simulation test described in claim 1, characterized in that: It includes the following steps: Place the experimental object in the copper cold shield (212), evacuate the inner cavity body (201) and the outer cavity body (101) separately. After reaching the required vacuum degree for the experiment, fill it with CO2 gas; stop inflating after reaching the predetermined pressure; Start the refrigeration expansion machine (106) to start the refrigeration operation or start the heater (208) to start the heating operation; After the experiment is over, turn off the refrigeration expansion machine (106) or the heater (208). Wait for the temperature of the cabin to return to room temperature. After the gas enters the cavity, then open the cabin door and take out the experimental piece.

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