Low-voltage temperature control experiment module for Mars environment simulation test and experiment method

Abstract

The invention discloses a low-voltage temperature control experiment module for a Mars environment simulation test and an experiment method, relates to the technical field of ground simulation Mars environment equipment, and solves the problem that the comprehensive simulation capability, especially the temperature aspect, of the ground simulation equipment for the Mars environment is insufficient. An upper cover of the experiment cabin is provided with a refrigeration expansion machine, and an inner cavity of the experiment cabin is connected with a vacuum baffle valve; the inner cavity is communicated with the vacuum baffle valve and the inner cavity body, and the refrigeration expansion machine is connected with the inner cavity body; an outer cavity connecting vacuum baffle valve and an outer cavity air inlet channel arranged on the outer cavity are communicated with the outer cavity, and an inner cavity air inlet channel on the outer cavity is communicated with the inner cavity; a condenser and a heater are arranged on the inner cavity, a copper cold screen is arranged in the inner cavity, and the refrigeration expansion machine, the condenser and the copper cold screen are sequentially connected. The Mars environment ground simulation experiment device can fully simulate the surface temperature, gas environment and pressure environment of Mars, overcomes the defects of the Mars environment ground simulation experiment device, and provides equipment support for the fields of aerospace, Mars detection and the like.

Description

Technical Field

[0001] The present invention relates to the technical field of ground-based equipment for simulating the Martian environment, and in particular to a low-pressure temperature-controlled 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 plays an important role in human space exploration and potential immigration. However, the surface environment of Mars is extremely rugged and complex, which places extremely high demands on the operation of ground and air exploration equipment. In particular, the extreme temperature, low air pressure and specific gas composition of Mars together constitute a huge challenge to the design and function realization of exploration equipment.

[0003] Traditional Mars exploration technologies, such as the activities of Mars rovers on the surface of Mars, are significantly restricted by the terrain, while aerospace facilities such as the Mars UAV provide the possibility of overcoming these terrain challenges due to their high mobility and flexibility. In view of this complex environment, it is particularly important to develop a ground experiment support device that can fully simulate the Martian environment. This equipment can not only simulate the air pressure and specific gas environment of Mars, but also accurately control extreme temperature conditions, making it a comprehensive experimental system. The system will support electrohydrodynamic experiments, plasma physics experiments, and comprehensive performance tests of small aerospace facilities such as the Mars UAV.

[0004] In the past 20 years, research institutions around the world have designed corresponding test benches for the Martian environment. In the early stages of research on unmanned Martian exploration equipment, simulation was the mainstream method chosen by researchers, but simulation experiments can reflect the dynamic performance of drones from a more intuitive perspective and make up for the possible irrationality of the model and inaccuracy of the results of numerical simulation methods.

[0005] In summary, in terms of simulation devices, according to the differences in the main environmental parameters between Mars and the Earth's surface, the Mars test bench should meet the requirements of atmospheric environment and temperature simulation. Currently, the United States, Japan, China and other countries have successively carried out research and design of Mars drone test benches.

[0006] (1) Ames Research Center Tower Test Bench: In 2001, the Ames Research Center in the United States initially demonstrated the feasibility of using the vertical take-off and landing characteristics of a rotary-wing UAV to explore the rugged terrain on the surface of Mars. The test bench was set up in the vacuum environment of the Ames Planetary Aeolus Laboratory. The gas density in the vacuum chamber was pumped to a level consistent with the Martian atmosphere for experiments, but the temperature and gas composition simulation were not further integrated, and the authenticity of the environmental simulation was insufficient.

[0007] (2) Stanford University Lever Test Bench: In 2003, Stanford University in the United States designed a test bench based on the principle of leverage to measure the lift of UAV rotors. The test environment was a surface environment with normal temperature and pressure, and no simulation of the Martian environment was performed.

[0008] (3) Tokyo University Pendulum Experimental Platform: In 2004, Tokyo University conducted a study on the feasibility of a Mars drone. The experimental device was set up in a vacuum chamber with a diameter of 2.40m and a height of 2.73m. The experimental process did not reflect the simulation of gas composition and temperature.

[0009] (4) University of Maryland Tower Test Bench: In 2015, the University of Maryland tested the hovering performance of a small-scale Mars drone. The test bench was built in a vacuum chamber at a height of approximately 0.91 m. The experimental process did not reflect the simulation of gas composition and temperature.

[0010] (5) Harbin Institute of Technology lever test bench: Harbin Institute of Technology has made a lot of achievements in the aerodynamic characteristics test device of Mars UAV. For example, based on the lever test bench of Stanford University, the lift generated by the rotor was accurately measured through the balance plate and bearing. At the same time, a lot of improvements were made on the pendulum test bench of the University of Tokyo. However, all the achievements were only for the measurement and simulation of the pressure and CO2 environment of Mars, and the application of simulation of other environments was limited.

[0011] (6) Ingenuity Mars UAV Testbed: In 2021, NASA's Mars UAV Ingenuity achieved autonomous flight on Mars for the first time. The test environment simulation process simulated the Martian atmosphere in a vacuum chamber by filling it with carbon dioxide, and verified through analysis that the experimental results under room temperature conditions were close to the actual aerodynamic performance under low temperature conditions on Mars.

[0012] It can be seen that most test benches can meet the simulation of the low atmospheric density of Mars. For the simulation of atmospheric composition, most research institutions chose air as the gas in the airtight chamber, while Harbin Institute of Technology and the Jet Propulsion Laboratory of California Institute of Technology chose carbon dioxide, which is absolutely dominant on Mars, for simulation, which undoubtedly makes the simulated gas environment closer to the real Martian atmosphere. However, most test benches have not been able to simulate the low and high temperature environments of 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 impact on equipment performance, such as:

[0014] (1) The low-pressure, CO2 atmosphere horizontal thermal vacuum container developed by the Beijing Satellite Environment Engineering Research Institute is an important device for the current domestic Mars probe testing and development. The container has a diameter of 4200 mm and a length of 5000 mm. The device can simulate a stable CO2 atmosphere and a low-pressure environment, but cannot simulate an extreme temperature environment.

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

[0016] (3) The JPL 10-foot space environment simulator in the United States was used to test the "Wanderer", "Spirit" and "Opportunity" Mars rovers. The space environment simulator is equipped with a temperature-controlled cold plate to simulate space temperature. The main indicators are an atmospheric temperature range of -130 to 20°C and a nitrogen gas pressure of 100 to 1300 Pa. The subsequent "Curiosity" Mars rover performed thermal tests in a 25ft space environment simulator with an outer diameter of 7.5m and a height of 21m. The inner test space has a diameter of 6m and a height of 7.5m. The heat sink temperature is -180 to 100°C. Unfortunately, the temperature simulation capability of this simulator does not reach the upper limit of the Martian temperature.

[0017] To sum up, although the existing test benches have their own characteristics, they generally have the deficiency of not fully simulating the Martian environment, especially in terms of temperature simulation. Summary of the invention

[0018] In order to solve the problem that the existing test benches are not able to simulate the Martian environment temperature, the present invention proposes a low-pressure temperature-controlled test chamber and test method for Martian environment simulation testing. The present invention can fully simulate the Martian surface temperature, gas environment and pressure environment, fill the gap in my country's Martian environment ground simulation experimental equipment, and provide basic experimental equipment support for aerospace, Mars exploration and other fields.

[0019] The present invention proposes a low-pressure temperature-controlled experimental cabin for Mars environment simulation testing, which specifically includes an experimental cabin upper cover, an experimental cabin inner cavity and an experimental cabin outer cavity, wherein the experimental cabin upper cover is arranged at the upper end of the experimental cabin outer cavity; the experimental cabin inner cavity is arranged inside the experimental cabin outer cavity and is hoisted under the experimental cabin upper cover; the experimental cabin upper cover includes an upper end cover, on which a refrigeration expander and an inner cavity connected vacuum baffle valve are arranged; the inner cavity is connected to the vacuum baffle valve and communicates with the experimental cabin inner cavity, and the refrigeration expander and the experimental cabin inner cavity are connected ; The outer cavity of the experimental cabin includes an outer layer cavity, on which are provided 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, the outer cavity connecting vacuum baffle valve and the outer cavity air inlet channel are both connected with the interior of the outer layer cavity, and the inner cavity air inlet channel is connected with the inner cavity of the experimental cabin; the inner cavity of the experimental cabin includes an inner cavity, on which are provided several condensers, on which are provided heaters, and inside of the inner cavity is provided a copper cold screen, and the refrigeration expander, condenser and copper cold screen are connected in sequence.

[0020] Furthermore, the condenser is provided with a vacuum bellows.

[0021] Furthermore, the copper cold screen is suspended in the inner cavity by bolts, and a cold screen door is provided on the copper cold screen.

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

[0023] Furthermore, the inner cavity is connected to the vacuum baffle valve and is communicated with the inner cavity through a vacuum air path steel pipe, and an expansion bend structure is provided on the vacuum air path steel pipe, the inner cavity air inlet channel and the outer cavity air inlet channel.

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

[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.

[0026] Furthermore, the outer cavity is provided with an experimental cabin door, and the experimental cabin door is provided with an outer cavity main vacuum observation window.

[0027] Furthermore, the upper end cover is provided with a high-voltage electric vacuum plug, a low-voltage electric vacuum plug, a top-view vacuum observation window and a pressure gauge, and the low-voltage electric vacuum plug is connected to the heater; the lower surface of the upper end cover is connected to the inner cavity through a number of threaded suspension rods.

[0028] An experimental method using the above-mentioned low-pressure temperature-controlled experimental chamber for Mars environment simulation testing comprises the following steps:

[0029] Place the experimental object in the copper cold screen, evacuate the inner cavity and the outer cavity respectively, and fill with CO2 gas after reaching the vacuum degree required by the experiment; stop filling 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, turn off the refrigeration expander or heater, wait until the cabin temperature returns to room temperature, and after the gas enters the cavity, open the cabin door and take out the experimental piece.

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

[0033] (1) The low-pressure temperature-controlled test chamber and test method for Mars environment simulation test described in the present invention overcome the problem that the existing test bench is insufficient in simulating the Mars environment temperature. The chamber vacuum can achieve an ultra-low vacuum degree. The chamber inside the test chamber and the chamber outside the test chamber are evacuated by a molecular pump. The ultimate vacuum of the chamber outside the test chamber is 2.6×10 -4 Pa, the ultimate vacuum in the experimental chamber is 3.4×10 -4 Pa, from atmospheric pressure to 5.0×10 -3 Pa is less than 35min; in terms of temperature control, it can achieve wide-span temperature control. The refrigeration expander transfers the cold to the condenser through the flexible copper cold belt, and the condenser transfers the cold to the copper cold screen to cool the test area. The heat generated by the heater is transferred to the copper cold screen through the condenser to heat the test area. The temperature range in the cavity of the test cabin is from low temperature -150℃ to high temperature 120℃, and the temperature change rate is less than 1℃ / min;

[0034] (2) A low-pressure temperature-controlled experimental chamber and experimental method for Mars environment simulation testing described in the present invention supports the input of various gas components and can flexibly control the gas components according to the space environment in the chamber, such as the Mars environment gas component dominated by carbon dioxide;

[0035] (3) The low-pressure temperature-controlled experimental chamber and experimental method for Mars environment simulation testing described in the present invention can actively dismantle the chamber inside the experimental chamber and use only the chamber outside the experimental chamber to operate when the temperature control system is not used to obtain a larger and more intuitive experimental operation space. The low-voltage electric vacuum plug reserved in the chamber supports the power supply of various sensors inside the chamber, and the high-voltage electric vacuum plug can meet the high voltage experiment within 30kV in the chamber. BRIEF 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 illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0037] In the attached picture:

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

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

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

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

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

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

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

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

[0046] Fig. 9 It is a left view of the inner cavity of a low-pressure temperature-controlled experimental chamber for Mars environment simulation testing according to the present invention;

[0047] Fig.10 The present invention is a low-pressure temperature-controlled experimental chamber for Mars environment simulation testing. Figure 4 Cross-section at AA in the middle;

[0048] Fig.11 The present invention is a low-pressure temperature-controlled experimental chamber for Mars environment simulation testing. Figure 5 Cross-section at the middle BB;

[0049] Among them: 1-experimental cabin cover, 2-experimental cabin inner cavity, 3-experimental cabin outer cavity, 101-outer cavity, 102-upper end cover, 103-experimental cabin door, 104-outer cavity main view vacuum observation window, 105-top view vacuum observation window, 106-refrigeration expander, 107-high voltage electric vacuum aviation plug, 108-low voltage electric vacuum aviation plug, 109-inner cavity connected vacuum baffle valve, 110-outer cavity connected vacuum baffle valve, 111-pressure gauge, 112-lifting ring, 113-cabin door hinge, 114-reserved interface, 115-outer cavity rear view Vacuum observation window, 116-inner cavity air inlet channel, 117-external cavity air inlet channel, 201-experimental chamber inner cavity, 202-experimental inner cavity door, 203-inner cavity main view vacuum observation window, 204-inner cavity top view vacuum observation window, 205-inner cavity rear view vacuum observation window, 206-low voltage vacuum aviation plug, 207-high voltage vacuum aviation plug, 208-heater, 209-condenser, 210-vacuum bellows, 211-lifting ear, 212-copper cold screen, 213-cold screen door, 214-vacuum airway steel pipe, 215-threaded lifting rod. DETAILED DESCRIPTION

[0050] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0051] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are 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 on the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0052] In the description of the invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "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 a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the invention can be understood according to specific circumstances.

[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 implementation method 1: See Figure 1-Figure 11 The present embodiment is described in detail. The low-pressure temperature-controlled experimental chamber for Mars environment simulation test described in the present embodiment specifically comprises an experimental chamber upper cover 1, an experimental chamber inner cavity 2 and an experimental chamber outer cavity 3, wherein the experimental chamber upper cover 1 is arranged at the upper end of the experimental chamber outer cavity 3; the experimental chamber inner cavity 2 is arranged inside the experimental chamber outer cavity 3 and hoisted under the experimental chamber upper cover 1; the experimental chamber inner cavity 2 is the main component for realizing environmental temperature control, and if the experimental environment does not require temperature control (only conduct experiments at room temperature), the experimental chamber inner cavity 2 can be removed from the lower end of the experimental chamber upper cover 1, and only the experimental chamber composed of the experimental chamber upper cover 1 and the experimental chamber outer cavity 3 can be used to expand the experimental section capacity in the vacuum chamber.

[0055] The upper cover 1 of the experimental cabin includes an upper end cover 102, on which a refrigeration expansion machine 106 and an inner cavity connected vacuum baffle valve 109 are arranged, and the refrigeration expansion machine 106 is packaged on the upper end plate 102 through a vacuum flange; the inner cavity is connected to the vacuum baffle valve 109 and is connected to the inner cavity 2 of the experimental cabin, and the interior of the inner cavity 2 of the experimental cabin is evacuated through the inner cavity connected to the vacuum baffle valve 109 to control the vacuum degree in the inner cavity 201; the refrigeration expansion machine 106 is connected to the external GM refrigerator, and the refrigeration expansion machine 106 is connected to the inner cavity 2 of the experimental cabin, and the interior of the inner cavity 2 of the experimental cabin is cooled through the refrigeration expansion machine 106; the cavity walls of the inner cavity 2 of the experimental cabin and the outer cavity 3 of the experimental cabin and the upper end cover 102 are made of 10 mm thick steel plates.

[0056] The outer cavity 3 of the experimental cabin includes an outer cavity 101, on which an outer cavity connected 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. The outer cavity connected vacuum baffle valve 110 and the outer cavity air inlet channel 117 are both connected to the interior of the outer cavity 101. The outer cavity connected vacuum baffle valve 110 evacuates the interior of the outer cavity 101 to control the vacuum degree in the outer cavity 101; experimental gas is introduced into the outer cavity 101 through the outer cavity air inlet channel 117; the inner cavity air inlet channel 116 is connected to the inner cavity 2 of the experimental cabin, and experimental gas is introduced into the inner cavity 2 of the experimental cabin through the inner cavity air inlet channel 116; the inner cavity air inlet channel 116 and the outer cavity air inlet channel 117 are both composed of needle valves, vacuum flanges and stainless steel vacuum tubes. The inner cavity connected vacuum baffle valve 109 and the outer cavity connected vacuum baffle valve 110 are both connected to an external molecular combination pump with a fore-stage pump.

[0057] The inner cavity 2 of the experimental module includes an inner cavity body 201. A number of condensers 209 are provided on the inner cavity body 201, and heaters 208 are provided on the condensers 209. A copper cold shield 212 is arranged inside the inner cavity body 201. The flange position at the first-stage cold head of the refrigeration expander 106 is connected to the condenser 209 on the inner cavity body 201 through a flexible copper cold-conducting belt, and the connection is fixed with bolts. The condenser 209 and the copper cold shield 212 inside the inner cavity body 201 are fixed with bolts; the copper cold shield 212 is of a box structure and is welded by copper plates with a thickness of 5 mm. The cold generated by the gas compression and expansion of the refrigerator is transmitted to the condenser 209 located on the inner cavity body 201 through the first-stage cold head of the refrigeration expander 106 and the flexible copper cold-conducting belt, and finally the cold is evenly conducted into the copper cold shield 212, and the low-temperature uniform control of the experimental area is realized through radiation heat transfer and natural convection heat transfer. The heat generated by the heater 208 is evenly conducted into the copper cold shield 212 through the condenser 209, and the high-temperature uniform control of the experimental area is realized through radiation heat transfer and natural convection heat transfer.

[0058] A vacuum bellows 210 is sleeved on the condenser 209, and the condenser 209 exposed outside the inner cavity body 201 is isolated from the internal space of the outer cavity 101 through the vacuum bellows 210.

[0059] The copper cold shield 212 is suspended inside the inner cavity body 201 through bolts up, down, left and right, and the distance between the copper cold shield 212 and the inner wall of the inner cavity body 201 is 3 - 5 mm; a cold shield door 213 is provided on the copper cold shield 212.

[0060] The inner cavity connecting vacuum baffle valve 109 is communicated with the inner cavity body 201 through a vacuum gas pipeline 214. Expansion bends are provided on the vacuum gas pipeline 214, the inner cavity air inlet channel 116 and the outer cavity air inlet channel 117, that is, there is at least one "匚"-shaped pipeline in the vertical direction of the pipeline. Since in actual experiments, the problem of thermal expansion and contraction caused by temperature changes often needs to be faced. By bending the pipeline to form an expansion bend, this problem can be effectively solved. This design allows the pipeline to freely expand and contract when the temperature changes without causing damage to the pipeline system.

[0061] 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; through holes are provided on the copper cold shield 212 corresponding to the positions of the inner cavity front-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 window on the inner cavity body 201. Through holes for electrical connection and gas pipeline passing are also provided on the copper cold shield 212; 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 aero plug 206 and a high-voltage vacuum aero 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 aero plug 206 and the high-voltage vacuum aero 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 door 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 plug 107, a low-voltage electric vacuum plug 108, a top-view vacuum observation window 105, a pressure gauge 111 and a plurality of lifting 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 pipeline, 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, and 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 by the pressure gauge 111. The experimental equipment in the outer cavity 101 is powered by a high-voltage electric vacuum plug 107 and a low-voltage electric vacuum plug 108, wherein the heater 208 is electrically connected to the outside of the experimental chamber through the pins of the low-voltage electric vacuum plug 108, so as to control 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 also provided with a reserved interface 114 .

[0067] An experimental method using the above-mentioned low-pressure temperature-controlled experimental chamber for Mars environment simulation testing comprises 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 respectively. After reaching the vacuum degree required by the experiment, CO2 gas is filled in; and the inflation is stopped after reaching the predetermined pressure;

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

[0070] After the experiment is over, the refrigeration expander 106 or the heater 208 is turned off, and the cabin temperature is allowed to return to room temperature, and the gas enters the cavity before the cabin door is opened to take out the experimental piece.

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

[0072] Detailed operation process under refrigeration conditions:

[0073] The refrigeration condition simulates the low temperature environment of Mars, the working fluid is CO2, and the pressure is 1000Pa.

[0074] Open the experimental chamber door 103, open the experimental inner chamber door 202 and the cold screen door 213 in sequence, put the experimental object into the copper cold screen 212, and then lock the cold screen door 213, the experimental inner chamber door 202 and the experimental chamber door 103. It is recommended to cover the external cavity main vacuum observation window 104 and the top view vacuum observation window 105 during the experiment, and open the light window for observation or lighting as needed.

[0075] Connect the high-voltage electric vacuum aviation plug 107, the temperature display, the vacuum gauge, the heater 208 and the low-voltage electric vacuum aviation plug 108 to ensure that the electrical equipment is correctly connected.

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

[0077] The compressor is turned on, and the refrigeration expander 106 is started to start the refrigeration operation. The temperature is monitored by a temperature display. If a higher temperature is required, the power can be controlled by adjusting the input voltage through the heater 208.

[0078] After the experiment is over, the compressor is turned off, and the temperature of the cabin is returned to room temperature. The inner cavity connected vacuum baffle valve 109 is slowly opened, and the cabin door is opened after the gas enters the cavity to take out the experimental piece.

[0079] Detailed operation process under heating conditions:

[0080] This embodiment demonstrates the operation process of the device in a heated state, simulating the high temperature environment of Mars, with the working fluid being CO2 and the pressure being 1000Pa.

[0081] Open the experimental cabin door 103, the experimental inner cavity door 202 and the cold screen door 213, put the experimental object into the copper cold screen 212, then lock all the doors, cover the outer cavity main view vacuum observation window 104 and the top view vacuum observation window 105 to reduce light and heat interference.

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

[0083] The heater 208 is turned on, and the temperature change is monitored by a temperature display instrument. 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, wait for the temperature to naturally drop to room temperature, slowly open the inner cavity connected vacuum baffle valve 109, and open the hatch after the gas enters the cavity.

[0085] During the above 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 cabin. 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 introduction and turn off the vacuum pump. The experiment is conducted 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. The experiment is conducted after the pressure is stabilized. 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 is for performing experiments without using an inner cavity, in order 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 201 is removed, the upper end cover 102 is reset and the experimental door 103 is locked. After confirming that all valves are closed, the vacuum and gas environment are adjusted according to the experimental requirements, and the experimental operation is started.

[0091] After the experiment is over, the outer cavity connected to the vacuum baffle valve 110 is slowly opened according to the safety process to restore the outer cavity 101 to normal pressure, and the experimental piece is taken out.

[0092] To summarize the above implementation cases, the low-pressure temperature-controlled experimental chamber and experimental method for Mars environment simulation test described in the present invention overcome the problem that the existing experimental platform is insufficient in simulating the Martian environmental temperature, and can achieve ultra-low vacuum in the chamber vacuum. The chamber 2 in the experimental chamber and the chamber 3 outside the experimental chamber are evacuated by a molecular pump, and the ultimate vacuum of the chamber 3 outside the experimental chamber is 2.6×10 -4 Pa, the ultimate vacuum of cavity 2 in the experimental chamber is 3.4×10 -4 Pa, from atmospheric pressure to 5.0×10 -3 Pa is less than 35min; in terms of temperature control, a wide range of temperature control can be achieved, the refrigeration expander 106 transfers the cold to the condenser 209 through the flexible copper cold belt, and the condenser 209 transfers the cold to the copper cold screen to cool the test area, and 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 in the cavity 2 in the experimental cabin is from a low temperature of -150°C to a high temperature of 120°C, and the temperature change rate is less than 1°C / min; the low-pressure temperature-controlled 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 regulate the gas components according to the space environment in the cavity, such as the Mars environment gas component mainly composed of carbon dioxide; the low-pressure temperature-controlled experimental cabin and experimental method for Mars environment simulation test described in the present invention can actively disassemble the cavity in the experimental cabin and only use the cavity outside the experimental cabin to operate when the temperature control system is not used to obtain a larger and more intuitive experimental operation space. The low-voltage vacuum plug reserved in the cavity supports the power supply of various sensors inside the cavity, and the high-voltage vacuum plug can meet the high voltage experiments within 30kV in the cavity.

[0093] The specific embodiments described above further illustrate the purpose, technical solutions and beneficial effects of the present invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the invention. It can also be a reasonable combination of the features recorded in the above implementation methods. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A low-pressure temperature-controlled experimental chamber for Mars environment simulation testing, characterized in that: The experimental cabin upper cover (1) comprises an experimental cabin inner cavity (2) and an experimental cabin outer cavity (3), wherein the experimental cabin upper cover (1) is arranged at the upper end of the experimental cabin outer cavity (3); the experimental cabin inner cavity (2) is arranged inside the experimental cabin outer cavity (3) and is hoisted below the experimental cabin upper cover (1); the experimental cabin upper cover (1) comprises an upper end cover (102), and a refrigeration expansion machine (106) and an inner cavity connection vacuum baffle valve (109) are arranged on the upper end cover (102); the inner cavity connection vacuum baffle valve (109) is communicated with the experimental cabin inner cavity (2), and the refrigeration expansion machine (106) is connected to the experimental cabin inner cavity (2); The outer cavity (3) of the experimental cabin comprises an outer cavity (101), and the outer cavity (101) is provided with 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); the outer cavity connecting vacuum baffle valve (110) and the outer cavity air inlet channel (117) are both in communication with the interior of the outer cavity (101), and the inner cavity air inlet channel (116) is in communication with the inner cavity (2) of the experimental cabin; The inner cavity (2) of the experimental chamber comprises an inner cavity (201), a plurality of condensers (209) are arranged on the inner cavity (201), a heater (208) is arranged on the condenser (209), a copper cold screen (212) is arranged inside the inner cavity (201), and a refrigeration expansion machine (106), a condenser (209) and a copper cold screen (212) are connected in sequence.

2. The low-pressure temperature-controlled experimental chamber for Mars environment simulation testing according to claim 1, characterized in that: The condenser (209) is sleeved with a vacuum bellows (210).

3. The low-pressure temperature-controlled experimental chamber for Mars environment simulation testing according to claim 1, characterized in that: The copper cold screen (212) is suspended in the inner cavity (201) by means of bolts, and a cold screen door (213) is provided on the copper cold screen (212).

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

5. The low-pressure temperature-controlled experimental chamber for Mars environment simulation testing according to claim 1, characterized in that: The inner cavity is connected to the vacuum baffle valve (109) and is communicated with the inner cavity body (201) via a vacuum air path steel pipe (214); and an expansion bend structure is provided on the vacuum air path steel pipe (214), the inner cavity air inlet channel (116) and the outer cavity air inlet channel (117).

6. The low-pressure temperature-controlled experimental chamber for Mars environment simulation testing according to claim 1, characterized in that: 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 front-view vacuum observation window (203).

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

8. The low-pressure temperature-controlled experimental chamber for Mars environment simulation testing according to claim 1, characterized in that: The outer cavity (101) is provided with an experimental cabin door (103), and the experimental cabin door (103) is provided with an outer cavity main vacuum observation window (104).

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

10. An experimental method using the low-pressure temperature-controlled experimental chamber for Mars environment simulation test according to claim 1, characterized in that: The following steps are involved: The experimental object is placed in the copper cold shield (212), and the inner cavity (201) and the outer cavity (101) are evacuated respectively. After the vacuum degree required by the experiment is reached, CO gas is filled in; and the filling is stopped after the predetermined pressure is reached; Starting the refrigeration expander (106) to start a refrigeration operation or starting the heater (208) to start a heating operation; After the experiment is over, the refrigeration expander (106) or the heater (208) is turned off, and the cabin temperature is restored to room temperature, and the gas enters the cavity before the cabin door is opened to take out the experimental piece.

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