1. The utility model provides a test device of water molecule migration in simulation planet soil which characterized in that: the device consists of a body arranged in a vacuum chamber (20), a data acquisition system and a star surface simulation environment control system which are arranged outside the vacuum chamber (20); the body comprises a horizontal base (1), a weighing system, a sample cabin and a split type inductance frequency modulation displacement sensor connected with the vacuum cabin (20); leveling bolts (3) which are in contact with a flat plate arranged on a liquid nitrogen pipe in the vacuum cabin (20) are distributed at four corners of the lower surface of the horizontal base (1), a horizontal liquid bubble (2), an inductive frequency modulation displacement sensor support (4) and a weighing support are respectively arranged on the upper surface of the horizontal base, and the split type inductive frequency modulation displacement sensor is arranged on the inductive frequency modulation displacement sensor support (4); the weighing system is arranged on the weighing support, and a sample cabin is arranged on the weighing system and is connected with the split type inductance frequency modulation displacement sensor; the weighing system, the split type inductance frequency modulation displacement sensor and the star catalogue simulation environment control system are respectively connected with the data acquisition system.

2. The test device for simulating water molecule migration in planetary soil as claimed in claim 1, wherein: the weighing support is composed of a platform plate (7) and a pair of vertical supporting legs (6) arranged at the bottom of the platform plate (7); the vertical supporting legs (6) are perpendicular to the horizontal base (1); and threading holes (8) are distributed at the central position of the platform plate (7).

3. The test device for simulating water molecule migration in planetary soil as claimed in claim 1, wherein: the weighing system comprises a lower spring support (12) arranged on a platform plate (7) in the weighing support, an upper spring support (11) connected with the lower spring support (12) through a weak temperature-sensitive spring (10), and an object bearing plate (9) arranged on the upper spring support (11); the upper surface of the platform plate (7) is provided with a lower pulley block (14); an upper pulley group (13) is arranged on the lower surface of the object bearing plate (9); a wire tying column (15) is arranged on the platform plate (7), and a non-elastic soft string (16) is connected to the wire tying column (15); the springless soft string (16) sequentially passes through the pulleys of the upper pulley block (13) and the lower pulley block (14) and passes through the threading hole (8) of the platform plate (7) to be connected with the upper end of an inductance frequency modulation displacement sensor measuring rod (17) of the split inductance frequency modulation displacement sensor; the sample cabin is arranged on the object bearing plate (9); the side surfaces of the object bearing plate (9) and the platform plate (7) are respectively connected with the data acquisition system.

4. A test device for simulating the migration of water molecules in planetary soil as claimed in claim 3, wherein: the four corners of the lower surface of the object bearing plate (9) are fixed with the upper spring support (11).

5. A test device for simulating the migration of water molecules in planetary soil as claimed in claim 3, wherein: the upper pulley block (13), the lower pulley block (14), the thread tying column (15), the thread passing hole (8) and the center of the object bearing plate (9) are distributed in a central symmetry manner.

6. The test device for simulating water molecule migration in planetary soil as claimed in claim 1, wherein: the split type inductance frequency modulation displacement sensor comprises an inductance frequency modulation displacement sensor measuring rod (17) and an inductance frequency modulation displacement sensor external part (18), wherein the inductance frequency modulation displacement sensor measuring rod is arranged in an inductance frequency modulation displacement sensor sleeve (5); the inductance frequency modulation displacement sensor sleeve (5) is vertical to the horizontal base (1), and the inductance frequency modulation displacement sensor sleeve (5) is embedded into the center of the inductance frequency modulation displacement sensor support (4); the bottom of the inductance frequency modulation displacement sensor sleeve (5) is connected with the external part (18) of the inductance frequency modulation displacement sensor and the data acquisition system through a cable (19); the top of the inductance frequency modulation displacement sensor measuring rod (17) is connected with a non-elastic soft string (16) of the weighing system.

7. The test device for simulating water molecule migration in planetary soil as claimed in claim 1, wherein: the sample chamber comprises an upper sample tank (23) and a lower sample tank (24) which are connected through a thread (27) and are used for filling star surface simulation covering materials; sensor holes (26) are formed in the side surfaces of the upper sample tank (23) and the lower sample tank (24); the top of the lower sample tank (24) is open, and the bottom of the lower sample tank is closed; the top of the upper sample tank (23) is open, and the bottom of the upper sample tank is open and provided with a superfine mesh steel net (29); and a low-temperature-resistant sealing ring (28) is arranged at the joint of the upper sample tank (23) and the lower sample tank (24).

8. The test device for simulating water molecule migration in planetary soil as claimed in claim 1, wherein: the data acquisition system comprises a temperature sensor (25) arranged in a sensor hole (26) on the side surface of the sample cabin, a concentration sensor (34) arranged on the top of the sample cabin, a cable (19) for transmitting an electric signal, a coil section cable (35), an aviation plug wall-penetrating unit (21) positioned on the vacuum cabin (20), a data acquisition module (22) and a data processing terminal (36); two ends of the coil segment cable (35) are respectively fixed on the side surfaces of an object bearing plate (9) and a platform plate (7) of the weighing system through wire fixing clamps (37); the aviation plug wall-penetrating unit (21) is respectively connected with the coil section cable (35), the data acquisition module (22), the inductance frequency modulation displacement sensor sleeve (5) of the split inductance frequency modulation displacement sensor and the external part (18) of the inductance frequency modulation displacement sensor through the cable (19); the temperature sensor (25) and the concentration sensor (34) are respectively connected with the data acquisition module (22), and the data acquisition module (22) is connected with the data processing terminal (36).

9. The test device for simulating water molecule migration in planetary soil as claimed in claim 1, wherein: the star catalogue simulation environment control system consists of a vacuum pump set (30) connected with an air outlet of the vacuum cabin (20), a liquid nitrogen pipe which is connected with a liquid nitrogen cabin through a circulating pump (31) and is coiled on the inner wall of the vacuum cabin (20), a thermal light source (32) which is positioned at the top of the inner wall of the vacuum cabin (20) and matched with the vacuum cabin (20), and an environment model test cabin control terminal (33); a vacuum gauge is arranged on the vacuum pump set (30); a temperature controller is arranged on the liquid nitrogen pipe; the thermal light source (32), the vacuum gauge and the temperature control gauge are respectively connected with the environmental model test chamber control terminal (33).

10. The use method of the test device for simulating water molecule migration in the planetary soil as claimed in claim 1, comprising the following steps:

the method comprises the steps of loading ice or liquid water into a lower sample tank (24), penetrating a temperature sensor (25) into the lower sample tank (24) through a tank body side wall sensor hole (26), sealing, and hermetically connecting an upper sample tank (23) with the lower sample tank (24) through threads (27);

filling a star surface simulation covering into the upper sample tank (23) according to test requirements, and penetrating a temperature sensor (25) into the upper sample tank (23) through a tank side wall sensor hole (26) according to the test requirements and then sealing;

placing the body in the vacuum cabin (20), placing the horizontal vacuole (2) on the horizontal base (1), and taking out the horizontal vacuole (2) after adjusting the leveling bolt (3) to the horizontal position of the horizontal base (1);

placing the sample cabin obtained in the second step into a liquid nitrogen tank arranged outside a vacuum cabin (20), taking out the sample cabin from liquid nitrogen and placing the sample cabin in the center of an object bearing plate (9) after the temperature of the sample is reduced to-196 ℃ under the condition that liquid nitrogen is controlled not to enter the sample, and closing a cabin door of the vacuum cabin (20);

the star surface simulation environment control terminal (33) and the vacuum pump set (30) are sequentially turned on, and after the environment pressure in the vacuum cabin (20) meets the requirement for starting the circulating pump (31), the circulating pump (31) is turned on to control the temperature in the vacuum cabin (20); then gradually controlling the ambient temperature and the pressure to meet the preset test requirements; if the test process needs to simulate the environmental visible radiation, after the environmental vacuum degree and the sample temperature in the vacuum chamber (20) are lower than the temperature point required by the test, a heat light source (32) is turned on, and the temperature, the pressure and the visible radiation in the vacuum chamber (20) are gradually controlled to reach the target star surface simulation environment;

when the temperature, the pressure and the radiation conditions of the star catalogue simulation environment in the vacuum cabin (20) are stable, a data acquisition module (22) and a data processing terminal (36) are opened, and a curve of displacement data measured by the split type inductance frequency modulation displacement sensor along with time change is drawn; when the slope of the curve is basically stable, the moisture loss process enters a stable state, and the position of the measuring rod (17) of the inductance frequency modulation displacement sensor is obtainedxContinuously monitoring and collecting data of each sensor in a stable state to obtain the elapsed timeThe displacement of a measuring rod (17) of the rear inductance frequency modulation displacement sensor is；

Changing visible light radiation conditions and temperature conditions of the star catalogue simulation environment according to test requirements to test a water loss process of the star catalogue simulation environment under a dynamic change condition, and setting matched sensor acquisition frequency according to the change condition of the star catalogue simulation environment;

and after the test is finished, firstly closing the vacuum pump set (30), gradually closing the circulating pump (31) when the condition that the circulating pump (31) is closed is reached, finally closing the heat light source (32), and collating the test data.

Background

With the continuous diffusion of human civilization to the interplanetary, the human deep space exploration technology is continuously developed, the problems of in-situ exploration and utilization of extraterrestrial resources are gradually obvious, human beings have more knowledge on the surface environment of the extraterrestrial objects through scientific calculation and satellite exploration methods, and a large number of scientific calculation and spacecraft exploration results show that some extraterrestrial planets have available resources. In the aspect of water resource space detection, environmental simulation is carried out on the earth surface of the star surface environment, and the dispersion process of moisture in the corresponding environment is researched to become an effective means for determining the retention area and the burial depth of volatile minerals such as the potential moisture of the corresponding star surface. By carrying out experimental research on the moisture loss process of the covering under the conditions of different compactness, different mineral components, different particle diameters and different covering thicknesses in the star surface environment, theoretical basis and experimental data support can be provided for the numerical analysis solving process of the potential occurrence areas and depths of the moisture-level volatile minerals in the relevant star surface environment.

At present, the volatile gas diffusion test device is commonly used, such as: the device can be only used in the surface environment and cannot be used in the environment conditions of simulated stars, such as the measurement of the water diffusion coefficient and the radon gas diffusion coefficient under the fixed temperature condition in the surface environment temperature and air pressure range, and the test of the water diffusion process in the simulated environment of a complex star catalogue cannot be carried out. The main problems hindering the use of the prior art in the star catalogue simulation environment are as follows: part of sensors suitable for the earth surface environment cannot survive in the star catalogue simulation environment, parameters such as moisture loss rate and the like in the star catalogue simulation environment cannot be accurately, effectively and continuously measured in the prior art, or a test device is too large in size and cannot be used in a vacuum chamber.

Disclosure of Invention

The invention aims to solve the technical problem of providing a diffusion test device of water in a satellite surface soil body, which has strong operability and can realize effective monitoring.

In order to solve the problems, the test device for simulating the water molecule migration in the planet soil is characterized in that: the device consists of a body arranged in a vacuum chamber, a data acquisition system and a star catalogue simulation environment control system which are arranged outside the vacuum chamber; the body comprises a horizontal base, a weighing system, a sample cabin and a split type inductance frequency modulation displacement sensor connected with the vacuum cabin; leveling bolts which are contacted with a flat plate arranged on a liquid nitrogen pipe in the vacuum chamber are distributed at four corners of the lower surface of the horizontal base, a horizontal vacuole, an inductive frequency modulation displacement sensor support and a weighing support are respectively arranged on the upper surface of the horizontal base, and the split type inductive frequency modulation displacement sensor is arranged on the inductive frequency modulation displacement sensor support; the weighing system is arranged on the weighing support, and a sample cabin is arranged on the weighing system and is connected with the split type inductance frequency modulation displacement sensor; the weighing system, the split type inductance frequency modulation displacement sensor and the star catalogue simulation environment control system are respectively connected with the data acquisition system.

The weighing support is composed of a platform plate and a pair of vertical supporting legs arranged at the bottom of the platform plate; the vertical supporting legs are perpendicular to the horizontal base; and threading holes are distributed in the center of the platform plate.

The weighing system comprises a lower spring support arranged on a platform plate in the weighing support, an upper spring support connected with the lower spring support through a weak temperature-sensitive spring and an object bearing plate arranged on the upper spring support; the upper surface of the platform plate is provided with a lower pulley block; the lower surface of the object bearing plate is provided with an upper pulley block; the platform plate is provided with a bolt wire column, and the bolt wire column is connected with a non-elastic soft string; the springless soft string sequentially passes through the pulleys of the upper pulley block and the lower pulley block and passes through the threading hole of the platform plate to be connected with the upper end of the inductance frequency modulation displacement sensor measuring rod of the split type inductance frequency modulation displacement sensor; the sample cabin is arranged on the object bearing plate; the side surfaces of the object bearing plate and the platform plate are respectively connected with the data acquisition system.

The four corners of the lower surface of the object bearing plate are fixedly provided with the upper spring support.

The center of the upper pulley block, the lower pulley block, the thread tying column, the thread hole and the object bearing plate is in central symmetry distribution.

The split type inductance frequency modulation displacement sensor comprises an inductance frequency modulation displacement sensor measuring rod and an inductance frequency modulation displacement sensor external part, wherein the inductance frequency modulation displacement sensor measuring rod is arranged in an inductance frequency modulation displacement sensor sleeve; the inductance frequency modulation displacement sensor sleeve is vertical to the horizontal base, and is embedded into the center of the inductance frequency modulation displacement sensor support; the bottom of the inductance frequency modulation displacement sensor sleeve is connected with the external part of the inductance frequency modulation displacement sensor and the data acquisition system through cables; the top of the measuring rod of the inductance frequency modulation displacement sensor is connected with a non-elastic soft string of the weighing system.

The sample cabin comprises an upper sample tank and a lower sample tank, wherein the upper sample tank and the lower sample tank are connected through threads and used for filling star surface simulation covering materials; sensor holes are formed in the side surfaces of the upper sample tank and the lower sample tank; the top of the lower sample tank is open, and the bottom of the lower sample tank is closed; the top of the upper sample tank is provided with an opening, and the bottom of the upper sample tank is provided with an opening and is provided with a superfine hole steel mesh; and a low-temperature-resistant sealing ring is arranged at the joint of the upper sample tank and the lower sample tank.

The data acquisition system comprises a temperature sensor arranged in a sensor hole on the side surface of the sample cabin, a concentration sensor arranged on the top of the sample cabin, a cable for transmitting an electric signal, a coil section cable, an aviation plug wall-penetrating unit positioned on the vacuum cabin, a data acquisition module and a data processing terminal; two ends of the coil section cable are respectively fixed on the side surfaces of an object bearing plate and a platform plate of the weighing system through wire fixing clamps; the aviation plug wall-through unit is respectively connected with the coil section cable, the data acquisition module, an inductance frequency modulation displacement sensor sleeve of the split inductance frequency modulation displacement sensor and an external part of the inductance frequency modulation displacement sensor through the cable; the temperature sensor and the concentration sensor are respectively connected with the data acquisition module, and the data acquisition module is connected with the data processing terminal.

The star catalogue simulation environment control system consists of a vacuum pump set connected with an air outlet of the vacuum chamber, a liquid nitrogen pipe which is connected with a liquid nitrogen chamber through a circulating pump and is coiled on the inner wall of the vacuum chamber, a thermal light source which is positioned at the top of the inner wall of the vacuum chamber and matched with the vacuum chamber, and an environment model test chamber control terminal; a vacuum gauge is arranged on the vacuum pump set; a temperature controller is arranged on the liquid nitrogen pipe; the thermal light source, the vacuum gauge and the temperature control gauge are respectively connected with the environmental model test chamber control terminal.

The use method of the test device for simulating the water molecule migration in the planetary soil comprises the following steps:

the method comprises the steps of loading ice or liquid water into a lower sample tank, penetrating a temperature sensor into the lower sample tank through a sensor hole in the side wall of a tank body, sealing, and hermetically connecting an upper sample tank with the lower sample tank through threads;

filling a star surface simulation covering into the upper sample tank according to test requirements, and penetrating a temperature sensor into the upper sample tank through a sensor hole in the side wall of the tank body and then sealing the temperature sensor according to the test requirements;

thirdly, the body is placed in the vacuum cabin, the horizontal vacuole is placed on the horizontal base, and the horizontal vacuole is taken out after the leveling bolt is adjusted to be horizontal to the horizontal base;

placing the sample cabin obtained in the second step into a liquid nitrogen tank arranged outside the vacuum cabin, taking out the sample cabin from liquid nitrogen and placing the sample cabin in the center of an object bearing plate after the temperature of the sample is reduced to-196 ℃ under the condition that liquid nitrogen is controlled not to enter the sample, and closing a cabin door of the vacuum cabin;

fifthly, opening the star surface simulation environment control terminal and the vacuum pump set in sequence, and after the environment pressure in the vacuum chamber meets the requirement for starting the circulating pump, opening the circulating pump to control the temperature in the vacuum chamber; then gradually controlling the ambient temperature and the pressure to meet the preset test requirements; if the test process needs to simulate the environmental visible radiation, after the environmental vacuum degree and the sample temperature in the vacuum chamber are lower than the temperature points required by the test, a thermal light source is turned on, and the temperature, the pressure and the visible radiation in the vacuum chamber are gradually controlled to reach the target star catalogue simulation environment;

when the temperature, the pressure and the radiation conditions of the star catalogue simulation environment in the vacuum cabin are stable, opening a data acquisition module and a data processing terminal, and drawing a curve of displacement data measured by the split type inductance frequency modulation displacement sensor along with time change; when the slope of the curve is basically stable, the moisture loss process enters a stable state, and the position of the measuring rod of the inductance frequency modulation displacement sensor is obtainedxContinuously monitoring and collecting data of each sensor in a stable state to obtain the elapsed timeThen, the displacement of the measuring rod of the inductance frequency modulation displacement sensor is；

Changing visible light radiation conditions and temperature conditions of the star catalogue simulation environment according to test requirements to test a water loss process of the star catalogue simulation environment under a dynamic change condition, and setting matched sensor acquisition frequency according to the change condition of the star catalogue simulation environment;

and after the test is finished, firstly closing the vacuum pump set, gradually closing the circulating pump when the condition that the circulating pump is closed is met, finally closing the heat light source, and finishing the test data.

Compared with the prior art, the invention has the following advantages:

1. the invention utilizes the pulley block, the weak temperature-sensitive spring and the inductance frequency modulation displacement sensor to form a weighing system, and can monitor the material loss process in the diffusion test process in real time by combining with a related data acquisition device, thereby solving the main technical problem of the diffusion test of moisture in the star surface covering layer under the environment of simulating the star surface.

2. The invention properly solves the technical problem that the traditional weighing sensor can not survive in a star catalogue simulation environment, and utilizes the high-precision inductance frequency modulation displacement sensor which can still stably work in a complex environment to accurately monitor the water dispersion loss, so that the key parameters of the water migration test in the star catalogue simulation environment can be effectively and timely obtained.

3. The test body is arranged in the vacuum chamber, and provides a corresponding operation flow, so that the research on the migration process of water molecules in the simulated satellite surface covering under the simulated satellite surface environment is implemented. Meanwhile, by combining the calculation method provided by the invention, the influence of parameters such as the thickness, dry density and porosity of different satellite surface covering layers on the water migration process in the satellite surface environment can be researched, and a reasonable model of the migration of water molecules in the satellite surface covering layers in the satellite surface environment is established.

4. The invention has wide application range, and a user can establish a corresponding test scheme according to research requirements and carry out detailed research.

Drawings

The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.

FIG. 1 is a schematic structural diagram of the present invention.

Fig. 2 is a schematic view of a weighing system of the present invention.

FIG. 3 is a schematic view of a sample tank of the present invention.

Fig. 4 is a schematic diagram of a split type inductance frequency modulation displacement sensor in the invention.

In the figure: 1-a horizontal base; 2-horizontal vacuole; 3-leveling bolt; 4-inductive frequency modulation displacement sensor support; 5-inductance frequency modulation displacement sensor sleeve; 6, vertical supporting legs; 7-a platform plate; 8-threading hole; 9-carrying plate; 10-weak temperature sensitive spring; 11-spring support; 12-lower spring support; 13-an upper pulley set; 14-a lower pulley block; 15-bolt wire column; 16-no-elastic soft string; 17-inductance frequency modulation displacement sensor measuring rod; 18-external part of inductance frequency modulation displacement sensor; 19-a cable; 20-vacuum chamber; 21-aviation plug wall-through unit; 22-a data acquisition module; 23, mounting a sample tank; 24-lower sample tank; 25-a temperature sensor; 26-sensor hole; 27-a thread; 28-low temperature resistant sealing ring; 29-superfine mesh steel net; 30-a vacuum pump group; 31-a circulation pump; 32-a thermal light source; 33-environmental model test chamber control terminal; 34-concentration sensor; 35-a coil segment cable; 36-data processing terminal; 37-wire fixing clip.

Detailed Description

As shown in figures 1-4, the test device for simulating the water molecule migration in the planet soil comprises a body arranged in a vacuum chamber 20, a data acquisition system arranged outside the vacuum chamber 20 and a star surface simulation environment control system.

The body comprises a horizontal base 1, a weighing system, a sample cabin and a split type inductance frequency modulation displacement sensor connected with a vacuum cabin 20; leveling bolts 3 which are contacted with a flat plate arranged on a liquid nitrogen pipe in the vacuum chamber 20 are distributed at four corners of the lower surface of the horizontal base 1, a horizontal liquid bubble 2, an inductive frequency modulation displacement sensor support 4 and a weighing support are respectively arranged on the upper surface of the horizontal base, and a split type inductive frequency modulation displacement sensor is arranged on the inductive frequency modulation displacement sensor support 4; the weighing support is provided with a weighing system, and the weighing system is provided with a sample cabin and is connected with the split type inductance frequency modulation displacement sensor; the weighing system, the split type inductance frequency modulation displacement sensor and the star catalogue simulation environment control system are respectively connected with the data acquisition system.

Wherein: the weighing support is composed of a platform plate 7 and a pair of vertical supporting legs 6 arranged at the bottom of the platform plate 7; the vertical supporting legs 6 are vertical to the horizontal base 1; the center position of the platform plate 7 is distributed with a threading hole 8.

The weighing system comprises a lower spring support 12 arranged on a platform plate 7 in a weighing support, an upper spring support 11 connected with the lower spring support 12 through a weak temperature-sensitive spring 10 and an object bearing plate 9 arranged on the upper spring support 11; the upper surface of the platform plate 7 is provided with a lower pulley block 14; the lower surface of the object bearing plate 9 is provided with an upper pulley block 13; a bolt line column 15 is arranged on the platform plate 7, and a non-elastic soft string 16 is connected to the bolt line column 15; the springless soft string 16 sequentially passes through the pulleys of the upper pulley block 13 and the lower pulley block 14 and passes through the threading hole 8 of the platform plate 7 to be connected with the upper end of the inductance frequency modulation displacement sensor measuring rod 17 of the split inductance frequency modulation displacement sensor; a sample cabin is arranged on the object bearing plate 9; the side surfaces of the object bearing plate 9 and the platform plate 7 are respectively connected with a data acquisition system.

The non-elastic soft string 16, the upper pulley block 13 and the lower pulley block 14 amplify displacement data of the weak temperature-sensitive spring 10 in the weighing system, so that the displacement amplification effect is achieved. The soft rope 16 without elasticity alternately passes through the upper pulley block 13 and the lower pulley block 14, and the soft rope 16 without elasticity is kept in a vertical state, the magnification is integral multiple, and the corresponding test precision is high.

Preferably, when an oblique line threading scheme is adopted, the magnification of a system consisting of the upper pulley block 13, the lower pulley block 14 and the soft string 16 without elasticity to the displacement is larger, the magnification is variable, and accurate calibration is required in actual use.

The four corners of the lower surface of the object bearing plate 9 are fixed with upper spring supports 11. The centers of the upper pulley block 13, the lower pulley block 14, the thread-tying column 15, the thread-tying hole 8 and the object-bearing plate 9 are distributed in central symmetry, so that the weak temperature-sensitive springs 10 distributed at four corners of the object-bearing plate 9 are ensured to be in a synchronous compression state.

The weak temperature-sensitive spring 10 can reduce the influence of temperature on the test precision to the greatest extent, and can be selected under the corresponding temperature condition according to the target test temperature in actual use.

The split type inductance frequency modulation displacement sensor comprises an inductance frequency modulation displacement sensor measuring rod 17 and an inductance frequency modulation displacement sensor external part 18, wherein the inductance frequency modulation displacement sensor measuring rod 17 is arranged in an inductance frequency modulation displacement sensor sleeve 5; the inductance frequency modulation displacement sensor sleeve 5 is vertical to the horizontal base 1, and the inductance frequency modulation displacement sensor sleeve 5 is embedded in the center of the inductance frequency modulation displacement sensor support 4; the bottom of the inductance frequency modulation displacement sensor sleeve 5 is connected with an inductance frequency modulation displacement sensor external part 18 and a data acquisition system through a cable 19; the top of the rod 17 of the inductance frequency modulation displacement sensor is connected with a springless soft string 16 of the weighing system. Namely: the electric signal of the inductance frequency modulation displacement sensor sleeve 5 is sequentially transmitted to the external part 18 of the inductance frequency modulation displacement sensor through the aviation plug wall-penetrating unit 21 arranged on the vacuum chamber 20 through the cable 19, and then the electric signal is transmitted to be connected with the data acquisition module 22 through the cable 19.

The inductance frequency modulation displacement sensor measuring rod 16 and the inductance frequency modulation displacement sensor sleeve 5 are one of displacement measuring components, and the external part 18 of the inductance frequency modulation displacement sensor refers to a component which fails or cannot survive in extreme environments such as vacuum and low temperature in a conventional inductance frequency modulation circuit. Through the amplification of the displacement of the bearing plate 9 by the pulley set, the inductance frequency modulation displacement sensor assembly can accurately acquire the water dispersion loss.

The sample chamber comprises an upper sample tank 23 for filling star catalogue simulation covering and a lower sample tank 24 for bearing ice or liquid water which are connected through threads 27; the side surfaces of the upper sample tank 23 and the lower sample tank 24 are both provided with sensor holes 26; the top of the lower sample tank 24 is open, and the bottom thereof is closed; the upper sample tank 23 is open at the top and is open at the bottom and is provided with a superfine mesh steel net 29; a low-temperature-resistant sealing ring 28 is arranged at the joint of the upper sample tank 23 and the lower sample tank 24. Reach sealed effect through low temperature resistant sealing washer 28, the jar body of corresponding height can be selected for use according to the experimental demand to the last sample jar 23 in the specific use.

The data acquisition system comprises a temperature sensor 25 arranged in a sensor hole 26 on the side surface of the sample cabin, a concentration sensor 34 arranged on the top of the sample cabin, a cable 19 for transmitting an electric signal, a coil section cable 35, an aviation plug wall-penetrating unit 21 positioned on the vacuum cabin 20, a data acquisition module 22 and a data processing terminal 36; two ends of the coil segment cable 35 are respectively fixed on the side surfaces of the object bearing plate 9 and the platform plate 7 of the weighing system through wire fixing clamps 37; the aviation plug wall-penetrating unit 21 is respectively connected with the coil segment cable 35, the data acquisition module 22, the inductance frequency modulation displacement sensor sleeve 5 of the split inductance frequency modulation displacement sensor and the inductance frequency modulation displacement sensor external part 18 through the cable 19; the temperature sensor 25 and the concentration sensor 34 are respectively connected with the data acquisition module 22, and the data acquisition module 22 is connected with the data processing terminal 36.

The star catalogue simulation environment control system consists of a vacuum pump set 30 (comprising a mechanical pump, a molecular pump and the like) connected with an air outlet of the vacuum chamber 20, a liquid nitrogen pipe which is connected with a liquid nitrogen chamber through a circulating pump 31 and is coiled on the inner wall of the vacuum chamber 20, a heat light source 32 which is positioned at the top of the inner wall of the vacuum chamber 20 and matched with the vacuum chamber 20, and an environment model test chamber control terminal 33; a vacuum gauge for controlling the pressure of the vacuum chamber 20 is arranged on the vacuum pump unit 30; a temperature controller for controlling the temperature of the vacuum chamber 20 is arranged on the liquid nitrogen pipe; the thermal light source 32, the vacuum gauge and the temperature control gauge are respectively connected with an environmental model test chamber control terminal 33.

The working principle of the invention is as follows:

the environment in the vacuum chamber 20 is controlled to be a star surface simulation environment, under the star surface simulation environment, moisture in the lower sample tank 24 is volatilized through a star surface simulation covering in the upper sample tank 23, the compressed springs 10 at the four corners under the object bearing platform 9 are gradually released, the object bearing platform 9 rises, the measuring rod 17 of the inductance frequency modulation displacement sensor is driven to rise, and the moisture is converted into an electric signal through the inductance frequency modulation displacement sensor sleeve 5 and the external part 18 of the inductance frequency modulation displacement sensor and recorded in the data acquisition module 22.

The use method of the device for testing the diffusion of the moisture in the satellite surface soil body comprises the following steps:

the use method of the test device for simulating water molecule migration in the planet soil comprises the following steps:

first, ice or liquid water is loaded into a lower sample tank 24, a temperature sensor 25 is sealed after penetrating the lower sample tank 24 through a tank sidewall sensor hole 26, and then an upper sample tank 23 and the lower sample tank 24 are hermetically connected by a screw 27.

And secondly, filling the star surface simulation covering into the upper sample tank 23 according to the test requirement, and penetrating the temperature sensor 25 into the upper sample tank 23 through the tank side wall sensor hole 26 and then sealing the upper sample tank 23 according to the test requirement.

Thirdly, the body is placed in the vacuum chamber 20, the horizontal vacuole 2 is placed on the horizontal base 1, and the horizontal vacuole 2 is taken out after the leveling bolt 3 is adjusted to be horizontal to the horizontal base 1, so that the test instrument is prevented from being damaged due to the breakage of the horizontal vacuole 2 when the environment pressure is simulated.

And fourthly, placing the sample cabin obtained in the second step into a liquid nitrogen tank arranged outside the vacuum cabin 20, reducing the temperature of the sample to-196 ℃ under the condition that liquid nitrogen does not enter the sample, taking out the sample cabin from the liquid nitrogen, placing the sample cabin in the center of the object bearing plate 9, and closing the cabin door of the vacuum cabin 20.

Fifthly, the star catalogue simulation environment control terminal 33 and the vacuum pump set 30 are sequentially turned on, and after the environmental pressure in the vacuum chamber 20 meets the requirement for starting the circulating pump 31, the circulating pump 31 is turned on to control the temperature in the vacuum chamber 20; then gradually controlling the ambient temperature and the pressure to meet the preset test requirements; if the test process needs to simulate the environmental visible radiation, after the environmental vacuum degree and the sample temperature in the vacuum chamber 20 are lower than the temperature point required by the test, the heat light source 32 is turned on, and the temperature, the pressure and the visible radiation in the vacuum chamber 20 are gradually controlled to the target star surface simulation environment.

When the temperature, the pressure and the radiation conditions of the star catalogue simulation environment in the vacuum cabin 20 are stable, the data acquisition module 22 and the data processing terminal 36 are opened, and a curve of displacement data measured by the split type inductance frequency modulation displacement sensor along with time change is drawn; when the slope of the curve is basically stable, the moisture loss process enters a stable state, and the position of the measuring rod 17 of the inductance frequency modulation displacement sensor is obtainedxContinuously monitoring and collecting data of each sensor in a stable state to obtain the elapsed timeThen, the displacement of the rod 17 of the FM displacement sensor is。

And changing visible light radiation conditions and temperature conditions of the star catalogue simulation environment according to test requirements to test the water loss process of the star catalogue simulation environment under the dynamic change condition, and setting matched sensor acquisition frequency according to the change condition of the star catalogue simulation environment.

After the test is finished, the vacuum pump set 30 is firstly closed, the circulating pump 31 is gradually closed when the condition that the circulating pump 31 is closed is met, and finally the heat light source 32 is closed, and the test data is collated.

The method for calculating the loss rate after the device test is finished is as follows:

for convenience of explanation, the present invention will be explained by using the embodiment shown in fig. 2, as shown in fig. 2, the thickness of the upper spring pad 11 is the same as the height of the axle center of the upper pulley set 13, and is a, and the heights of the axle centers of the lower spring pad 12 and the lower pulley set 14 are the same; the elastic coefficient of the weak temperature-sensitive spring 10 is k, the distance between the axle centers of the upper and lower pulley sets is L, as can be seen from fig. 2, when the vertical displacement of the object bearing table 9 is L, the displacement of the pulley set system is amplified, 12 times of the displacement is measured by the inductance frequency-modulation displacement sensor,

setting a certain time periodtThe displacement variation measured by the internal inductance frequency modulation displacement sensor isxThen the object-bearing platform 9 is vertically displaced by(ii) a The weak temperature-sensitive spring 10 is subjected to a pressure reduction of。

The following equation can be established between the sample water dispersion amount of the object bearing table 9 and the rope amount of the weak temperature-sensitive spring 10:

water content in sample tank in time period tThe loss mass m is:

moisture loss rate under star catalogue simulation environmentvComprises the following steps:

temperature sensors are buried in the sample, the larger the volume of the upper sample tank is, the poorer the temperature uniformity of the upper sample tank is, and the more obvious the corresponding temperature gradient is, and the moisture diffusion parameters in the corresponding simulation covering under the environment of simulating the star surface in the upper sample tank can be further deeply researched by combining the humidity sensors arranged on the surface of the sample.