A dynamic charged planet dust life test system

Abstract

The application is a dynamic charged planet dust life test system. The application relates to the field of planet dust simulation technology, and the application integrates corresponding protocols into a unified sensing system framework to realize comprehensive monitoring of the internal airflow static parameters, dynamic parameters, dust parameters, electromagnetic parameters and mechanical vibration frequency of a Mars atmosphere surface environment simulation cabin. Furthermore, a biological body restraining device can be placed in the container to study the influence of charged planet dust on the biological body.

Description

Technical Field

[0001] This invention relates to the field of planetary dust simulation technology, and is a dynamic charged planetary dust life experiment system. Background Technology

[0002] The effects of planetary dust on living organisms have been studied; for example, lunar dust has impacted the health of astronauts. Lunar dust contains a large number of inhalable particles (<10μm), with approximately 10% of lunar dust particles being inhalable. These coarse, fine, and extremely fine particles can cause varying degrees of impact on different parts of the body. Furthermore, lunar dust is highly chemically reactive and easily reacts with human cells, leading to allergies and other health problems. In addition, Al₂O₃ and SiO₂ in lunar dust are major components contributing to silicosis.

[0003] However, current research on the effects of charged planetary dust on living organisms is still limited. Nevertheless, the fact that planetary dust is charged is a significant phenomenon. For example, on the Moon, due to the extremely low conductivity of the surface materials and the absence of liquid water, the lunar surface is essentially non-conductive, and charges do not transfer. This results in a large potential difference between sunlit and shadowed areas of the Moon. On Mars, frequent atmospheric activity, such as dust storms and dust devils, causes dust particles to constantly migrate, collide, and jump, leading to charge separation between particles and resulting in more frequent electric field activity.

[0004] Therefore, to study the impact of charged planetary dust environments on organisms, this system adopts the following design concept: To create an electric field environment, an ejector is used to generate an initial wind field, with the high-pressure gas supplied by a gas compressor. To create a dust environment, planetary dust (simulating lunar or Martian dust, etc.) is injected into the container. Under the action of the wind field, the dust is driven to move and rub against each other within the container, generating static electricity, which in turn causes charged particles to interact with organisms within the container. This allows for the study of the physiological characteristics of organisms under charged planetary dust, analyzing the sensitivity of organisms to charged particles and corresponding charge threshold parameters. This provides relevant research data and technological reserves for future deep space exploration, manned lunar landing, manned Mars landing, and the establishment of planetary bases. Summary of the Invention

[0005] This invention provides relevant research data and technical reserves for future deep space exploration, manned lunar landing, manned Mars landing, and the establishment of planetary bases.

[0006] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0007] This invention provides a dynamic charged planetary dust life experiment system, and the invention provides the following technical solutions:

[0008] A dynamic charged planetary dust life experiment system, the system comprising: a gas source system, a sand and dust system, a wind speed simulation system, an ejector, and an experimental chamber;

[0009] The ejector is a sub-component of the wind speed simulation system. The air source system and the wind speed simulation system generate an initial wind field through the ejector. The sand and dust system injects planetary dust into the experimental chamber. Under the action of the wind field, the dust is driven to move and rub against each other in the experimental chamber and generate static electricity, so that the charged particles interact with the organisms in the container. This allows for the study of the physiological characteristics of organisms under charged planetary dust, and the analysis of the organisms' sensitivity to charged particles and the corresponding charge threshold parameters.

[0010] Preferably, the gas source system includes a manual valve, a pressure gauge, and a gas compressor, wherein the gas compressor is connected to the pressure gauge, and the pressure gauge is connected to the manual valve.

[0011] Preferably, the sand and dust system includes: a sand and dust concentration meter, a screw feeder, a sand and dust flow scale, a pressure gauge, a pressure reducing valve, and a Venturi injector;

[0012] The pressure reducing valve is connected to the manual valve, the pressure gauge is connected to the pressure reducing valve, the Venturi ejector is connected to the pressure gauge, the Venturi ejector is connected to the sand and dust flow scale, the sand and dust flow scale is connected to the screw feeder, the Venturi ejector is connected to the sand and dust concentration meter, and the sand and dust concentration meter is connected to the ejector.

[0013] Preferably, the wind speed simulation system includes: a front-end pressure gauge, a flow meter, a middle-end pressure gauge, a regulating valve, a return valve, a tail-end pressure gauge, a pressure stabilizing valve, and an electric ball valve;

[0014] The electric ball valve is connected to the tail section pressure gauge, the tail section pressure gauge is connected to the air source system, the electric ball valve is connected to the pressure stabilizing valve, the pressure stabilizing valve is connected to the return air valve, the return air valve is connected to the regulating valve, the regulating valve is connected to the intermediate section pressure gauge, the intermediate section pressure gauge is connected to the flow meter, the flow meter is connected to the front section pressure gauge, and the front section pressure gauge is connected to the ejector.

[0015] Preferably, the experimental chamber is equipped with a sensor array and a mouse cage;

[0016] The rat cage includes a movable fan, a grid, a cylindrical pin, a rat cage support, and bolts. The rat cage support fixes the rat cage to the bottom of the experimental chamber with bolts. The rat cage is surrounded by a grid, and the upper end of the rat cage is connected to the movable fan through a cylindrical pin.

[0017] Preferably, the sensor group includes a pressure sensor,

[0018] Temperature sensor, wind direction sensor, wind speed sensor, Faraday cup charge sensor, surface potentiometer, and dust concentration sensor;

[0019] The pressure sensors are arranged diagonally when viewed from above, and are distributed equidistantly at 0.25m intervals laterally in the frontal view.

[0020] The temperature sensors are platinum resistance thermometers, arranged diagonally when viewed from above, and distributed at equal intervals of 0.5m when viewed from the front.

[0021] The wind speed sensors are arranged diagonally when viewed from above, and are distributed equidistantly at 0.5m intervals laterally in the space when viewed from the front.

[0022] The wind direction sensor monitors the direction of airflow inside the cabin. It is arranged diagonally from above and distributed equidistantly at 0.5m intervals laterally in the frontal view.

[0023] The dust concentration sensors are arranged diagonally from above, and are distributed at equal intervals of 0.5m laterally in the space when viewed from the front.

[0024] The Faraday cup charge sensors are arranged diagonally when viewed from above, and are distributed equidistantly at 0.5m intervals laterally in the frontal view.

[0025] The surface potentiometers are arranged diagonally when viewed from above, and are distributed equidistantly at 0.5m intervals when viewed from the front.

[0026] Preferably, the wind speed sensor, wind direction sensor, dust concentration sensor, Faraday cup charge sensor, and surface potentiometer measuring points are located on the side wall of the experimental chamber, in two groups: four in the upper middle layer and four in the lower middle layer.

[0027] Preferably, the pressure sensor and temperature sensor are located on the top of the experimental chamber, in a set of four.

[0028] Preferably, the pressure sensor is a cylindrical column with a diameter of 1m and a total height of 1m.

[0029] Preferably, the rat cage is equipped with a biosensor to detect the animal's heart rate and body temperature.

[0030] The present invention has the following beneficial effects:

[0031] This invention addresses the research needs regarding the effects of planetary dust on living organisms by proposing a dynamic charged planetary dust life experiment system. The effects of planetary dust on living organisms have been studied previously; for example, lunar dust has impacted the health of astronauts. Lunar dust contains a large number of inhalable particles (<10μm), with approximately 10% of lunar dust particles being inhalable. These coarse, fine, and extremely fine particles can cause varying degrees of impact on different parts of the human body. Furthermore, lunar dust is highly chemically reactive and readily reacts with human cells, potentially leading to allergies and other health problems. In addition, Al₂O₃ and SiO₂ in lunar dust are major components contributing to silicosis.

[0032] This invention addresses the above-mentioned monitoring by integrating them into a unified sensing system architecture through corresponding protocols. This enables comprehensive monitoring of static and dynamic parameters of airflow, dust parameters, electromagnetic parameters, and mechanical vibration frequencies within a Martian atmospheric surface environment simulation chamber. Furthermore, biological restraint devices can be placed inside the container to study the effects of charged planetary dust on living organisms.

[0033] The biological restraint device (mouse cage) is the core component of this invention, and related biosensors are also arranged on it, including those for detecting the animal's heart rate and body temperature. Taking the mouse cage shown in the attached figure as an example, the top uses a cylindrical pin as a movable flap for placing the mouse, and the bottom has four pins, with bolts used to fix the support. The cage wall uses a grid structure, which facilitates the entry of dust and also allows for observation of the mouse's activity. Attached Figure Description

[0034] Figure 1 This is a schematic diagram of the system structure;

[0035] Figure 2 This is a top-view diagram of the system;

[0036] Figure 3 This is a schematic diagram of the system's three-dimensional structure. Detailed Implementation

[0037] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0038] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0039] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0040] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other. Specific Implementation Example 1:

[0042] according to Figures 1 to 3 As shown, the specific optimized technical solution adopted by the present invention to solve the above-mentioned technical problems is: The present invention relates to a dynamic charged planetary dust life test system.

[0043] A dynamic charged planetary dust life experiment system, the method comprising the following steps:

[0044] The system includes: an air source system, a sand and dust system, a wind speed simulation system, an ejector, and an experimental chamber;

[0045] The ejector is a sub-component of the wind speed simulation system, which includes multiple components such as the ejector, air valve, air supply pipe, and air distribution block. The air source system includes components such as an air compressor, air tank, and refrigerated dryer. The wind field is generated by the combined operation of the air source system and the wind speed simulation system. The dust system injects planetary dust into the experimental chamber. Under the action of the wind field, the dust is driven to move and rub against each other within the experimental chamber, generating static electricity. This causes charged particles to interact with organisms within the container, allowing for the study of the physiological characteristics of organisms under charged planetary dust, and the analysis of the organisms' sensitivity to charged particles and the corresponding charge threshold parameters. Specific Implementation Example 2:

[0047] The only difference between Embodiment 2 and Embodiment 1 of this application is that:

[0048] The gas supply system includes a manual valve, a pressure gauge, and a gas compressor. The gas compressor is connected to the pressure gauge, and the pressure gauge is connected to the manual valve. Specific Implementation Example 3:

[0050] The only difference between Embodiment 3 and Embodiment 2 of this application is that:

[0051] The sand and dust system includes: a sand and dust concentration meter, a screw feeder, a sand and dust flow scale, a pressure gauge, a pressure reducing valve, and a Venturi injector;

[0052] The pressure reducing valve is connected to the manual valve, the pressure gauge is connected to the pressure reducing valve, the Venturi ejector is connected to the pressure gauge, the Venturi ejector is connected to the sand and dust flow scale, the sand and dust flow scale is connected to the screw feeder, the Venturi ejector is connected to the sand and dust concentration meter, and the sand and dust concentration meter is connected to the ejector. Specific Implementation Example 4:

[0054] The only difference between Embodiment 4 and Embodiment 3 of this application is that:

[0055] The wind speed simulation system includes: a front-end pressure gauge, a flow meter, a middle-end pressure gauge, a regulating valve, a return valve, a tail-end pressure gauge, a pressure stabilizing valve, and an electric ball valve;

[0056] The electric ball valve is connected to the tail section pressure gauge, the tail section pressure gauge is connected to the air source system, the electric ball valve is connected to the pressure stabilizing valve, the pressure stabilizing valve is connected to the return air valve, the return air valve is connected to the regulating valve, the regulating valve is connected to the intermediate section pressure gauge, the intermediate section pressure gauge is connected to the flow meter, the flow meter is connected to the front section pressure gauge, and the front section pressure gauge is connected to the ejector. Specific Implementation Example 5:

[0058] The only difference between Embodiment 5 and Embodiment 4 of this application is that:

[0059] The experimental chamber is equipped with sensor arrays and a mouse cage;

[0060] The rat cage includes a movable fan, a grid, a cylindrical pin, a rat cage support, and bolts. The rat cage support fixes the rat cage to the bottom of the experimental chamber with bolts. The rat cage is surrounded by a grid, and the upper end of the rat cage is connected to the movable fan through a cylindrical pin. Specific Implementation Example Six:

[0062] The only difference between Embodiment Six and Embodiment Five of this application is that:

[0063] The sensor group includes a pressure sensor,

[0064] Temperature sensor, wind direction sensor, wind speed sensor, Faraday cup charge sensor, surface potentiometer, and dust concentration sensor;

[0065] The pressure sensors are arranged diagonally when viewed from above, and are distributed equidistantly at 0.25m intervals laterally in the frontal view.

[0066] The temperature sensors are platinum resistance thermometers, arranged diagonally when viewed from above, and distributed at equal intervals of 0.5m when viewed from the front.

[0067] The wind speed sensors are arranged diagonally when viewed from above, and are distributed equidistantly at 0.5m intervals laterally in the space when viewed from the front.

[0068] The wind direction sensor monitors the direction of airflow inside the cabin. It is arranged diagonally from above and distributed equidistantly at 0.5m intervals laterally in the frontal view.

[0069] The dust concentration sensors are arranged diagonally from above, and are distributed at equal intervals of 0.5m laterally in the space when viewed from the front.

[0070] The Faraday cup charge sensors are arranged diagonally when viewed from above, and are distributed equidistantly at 0.5m intervals laterally in the frontal view.

[0071] The surface potentiometers are arranged diagonally when viewed from above, and are distributed equidistantly at 0.5m intervals when viewed from the front.

[0072] This invention addresses the research needs regarding the effects of planetary dust on living organisms by proposing a dynamic charged planetary dust life experiment system. The effects of planetary dust on living organisms have been studied previously; for example, lunar dust has impacted the health of astronauts. Lunar dust contains a large number of inhalable particles (<10μm), with approximately 10% of lunar dust particles being inhalable. These coarse, fine, and extremely fine particles can cause varying degrees of impact on different parts of the human body. Furthermore, lunar dust is highly chemically reactive and readily reacts with human cells, potentially leading to allergies and other health problems. In addition, Al₂O₃ and SiO₂ in lunar dust are major components contributing to silicosis.

[0073] This invention addresses the above-mentioned monitoring by integrating them into a unified sensing system architecture through corresponding protocols. This enables comprehensive monitoring of static and dynamic parameters of airflow, dust parameters, electromagnetic parameters, and mechanical vibration frequencies within a Martian atmospheric surface environment simulation chamber. Furthermore, biological restraint devices can be placed inside the container to study the effects of charged planetary dust on living organisms. Specific Implementation Example 7:

[0075] The only difference between Embodiment 7 and Embodiment 6 of this application is that:

[0076] The wind speed sensor, wind direction sensor, dust concentration sensor, Faraday cup charge sensor, and surface potentiometer measuring points are located on the side wall of the experimental chamber. There are two groups in total, with four in the upper middle layer and four in the lower middle layer. Specific Implementation Example 8:

[0078] The difference between Embodiment 8 and Embodiment 7 of this application lies only in:

[0079] The pressure and temperature sensors are located on the top of the experimental chamber, in a set of four. Specific Implementation Example Nine:

[0081] The difference between Embodiment Nine and Embodiment Eight in this application lies only in:

[0082] The pressure sensor is a cylindrical column with a diameter of 1m and a total height of 1m. Specific Implementation Example 10:

[0084] The only difference between Embodiment 10 and Embodiment 9 of this application is that:

[0085] The rat cage is equipped with biosensors to detect the rat's heart rate and body temperature. Specific Implementation Example Eleven:

[0087] The only difference between Embodiment Eleven and Embodiment Ten of this application is that:

[0088] The sensor parameters of the dynamic charged Martian dust life experiment system are shown below.

[0089] Gas static parameters: gas pressure and temperature.

[0090] Dynamic airflow parameters: wind speed and wind direction.

[0091] Dust parameters: dust concentration.

[0092] Electromagnetic parameters: static charge of dust, electrostatic potential.

[0093] The following sensor arrangement was implemented based on the above parameters. Temperature and pressure detection points are located at the same location on the top of the container, in a single group of four. Wind speed, wind direction, dust concentration, dust electrostatic charge, and electrostatic discharge sensors are located at the same points on the side walls of the container, in two groups: one group of four in the upper middle layer and another group of four in the lower middle layer.

[0094] The pressure monitoring measurements are displayed using a digital pressure gauge. The space is considered to be a cylindrical column with a diameter of 1m and a total height of 1m. The column is arranged diagonally when viewed from above, and is distributed at equal intervals of 0.25m when viewed from the front.

[0095] Temperature monitoring uses platinum resistance thermometers. Considering the large space inside the cabin, they are arranged diagonally from above and distributed equidistantly at 0.5m intervals from the front.

[0096] Wind speed monitoring uses ultrasonic anemometers / pitot tube sensors. Considering that the design purpose of the simulation cabin is to simulate Martian dust devils, there are requirements for the speed range. The sensors are arranged diagonally from above and distributed equidistantly at 0.5m intervals from the front view.

[0097] Wind direction monitoring uses wind direction sensors. Considering the need to simulate dust devils, it is necessary to monitor the airflow direction inside the cabin. The sensors are arranged diagonally from above, and when viewed from the front, they are distributed at equal intervals of 0.5m laterally.

[0098] The dust concentration inside the cabin is monitored using dust sensors. These sensors are arranged diagonally from above, and when viewed from the front, they are distributed at equal intervals of 0.5m laterally.

[0099] Static electricity is generated within the chamber due to dust movement. Negatively charged, lighter dust particles rise during convection, while positively charged, heavier dust particles remain near the surface. This charge separation results in a dipole moment and associated dipole electric field within the dust storm. Therefore, Faraday charge sensors are used to monitor the electrostatic charge within the chamber to ensure the safe operation of the equipment. The sensors are arranged diagonally from above, and equidistantly at 0.5m intervals laterally when viewed from above.

[0100] Static electricity is generated inside the chamber due to dust movement. Therefore, a surface potentiometer is used to monitor the electrostatic potential inside the chamber to ensure the safe operation of the equipment. The arrangement is diagonal when viewed from above, and evenly distributed laterally at 0.5m intervals when viewed from the front.

[0101] To address the above monitoring requirements, a unified sensing system architecture is established through corresponding protocols, enabling comprehensive monitoring of static and dynamic parameters of airflow, dust parameters, electromagnetic parameters, and mechanical vibration frequencies within the Martian atmospheric surface environment simulation chamber. Furthermore, biological restraint devices can be placed inside the container to study the effects of charged planetary dust on living organisms.

[0102] The biological restraint device is the core of this invention, and related biosensors are also arranged on it, including those for detecting the animal's heart rate and body temperature. Taking the mouse cage shown in the attached figure as an example, the top uses a cylindrical pin as a movable flap for placing the mouse, and the bottom has four pins, with bolts used to fix the support. The cage wall uses a grid structure, which facilitates the entry of dust and also allows for observation of the mouse's activity.

[0103] In the description of this specification, references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or N embodiments or examples. Furthermore, those skilled in the art can combine and integrate the different embodiments or examples described in this specification and the features of different embodiments or examples without contradiction. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of the present invention, "N" means at least two, such as two, three, etc., unless otherwise explicitly specified. Any process or method description in the flowchart or otherwise herein can be understood as representing a module, segment, or portion of code comprising one or more N executable instructions for implementing custom logic functions or processes, and the scope of preferred embodiments of the invention includes additional implementations in which functions may be performed not in the order shown or discussed, including substantially simultaneously or in reverse order depending on the functions involved, as should be understood by those skilled in the art to which embodiments of the invention pertain.

[0104] The above description is merely a preferred embodiment of a dynamic charged planetary dust life testing system. The scope of protection for such a system is not limited to the above embodiments; all technical solutions falling within this conceptual framework are within the scope of protection of this invention. It should be noted that for those skilled in the art, any improvements and variations made without departing from the principles of this invention should also be considered within the scope of protection of this invention.

Claims

1. A dynamic charged planet dust life test system characterized by: The dynamic electrified planet dust life test system comprises a gas source system, a sand dust system, a wind speed simulation system, an ejector and a test cabin. The ejector is a subcomponent of the wind speed simulation system, the gas source system and the wind speed simulation system generate an initial wind field through the ejector, and the sand dust system injects planet dust into the test cabin. The gas source system comprises a manual valve, a first pressure gauge and a gas compressor. The sand dust system comprises a sand dust concentration instrument, a spiral feeder, a sand dust flow scale, a second pressure gauge, a pressure reducing valve and a Venturi ejector. The pressure reducing valve is connected to the manual valve, the second pressure gauge is connected to the pressure reducing valve, the Venturi ejector is connected to the second pressure gauge, the Venturi ejector is connected to the sand dust flow scale, the sand dust flow scale is connected to the spiral feeder, the Venturi ejector is connected to the sand dust concentration instrument, and the sand dust concentration instrument is connected to the ejector. The wind speed simulation system comprises a front pressure gauge, a flow meter, a middle pressure gauge, an adjusting valve, a gas return valve, a tail pressure gauge, a pressure stabilizing valve and an electric ball valve. The electric ball valve is connected to the tail pressure gauge, the tail pressure gauge is connected to the gas source system, the electric ball valve is connected to the pressure stabilizing valve, the pressure stabilizing valve is connected to the gas return valve, the gas return valve is connected to the adjusting valve, the adjusting valve is connected to the middle pressure gauge, the middle pressure gauge is connected to the flow meter, the flow meter is connected to the front pressure gauge, and the front pressure gauge is connected to the ejector. The test cabin is provided with a sensor group and a mouse cage. The mouse cage comprises a movable fan, a grid, a cylindrical pin, a mouse cage support and a bolt. The mouse cage is provided with a biological sensor for detecting the heart rate and body temperature of a mouse. The sensor group comprises a pressure sensor, a temperature sensor, a wind direction sensor, a wind speed sensor, a Faraday cup charge quantity sensor, a surface potential instrument and a dust concentration sensor. The pressure sensor is diagonally arranged in a top view and is distributed at an equal distance of 0.25 m in a front view. The temperature sensor is a platinum resistance thermometer and is diagonally arranged in a top view and is distributed at an equal distance of 0.5 m in a front view. The wind speed sensor is diagonally arranged in a top view and is distributed at an equal distance of 0.5 m in a front view. The wind direction sensor monitors the flow direction of the airflow in the test cabin and is diagonally arranged in a top view and is distributed at an equal distance of 0.5 m in a front view. The dust concentration sensor is diagonally arranged in a top view and is distributed at an equal distance of 0.5 m in a front view. The Faraday cup charge quantity sensor is diagonally arranged in a top view and is distributed at an equal distance of 0.5 m in a front view. The surface potential instrument is diagonally arranged in a top view and is distributed at an equal distance of 0.5 m in a front view. The wind speed sensor, the wind direction sensor, the dust concentration sensor, the Faraday cup charge quantity sensor and the surface potential instrument are located on the side wall of the test cabin. The pressure sensor and the temperature sensor are located on the top of the test cabin.

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