WO2021035757A1

WO2021035757A1 - Moon-based environment simulation device

Info

Publication number: WO2021035757A1
Application number: PCT/CN2019/103894
Authority: WO
Inventors: 谢和平; 张国庆; 高明忠; 朱建波; 李存宝
Original assignee: 深圳大学
Priority date: 2019-08-31
Filing date: 2019-08-31
Publication date: 2021-03-04

Abstract

Provided is a moon-based environment simulation device (100), comprising a moon ground simulation system (101) and a moon rock simulation system (103) which are arranged in a connection manner, the moon ground simulation system (101) is used for enabling the simulation device (100) to simulate the moon ground environment, the moon rock simulation system (103) is used for simulating the moon rock environment. Due to considering the simulation of the moon ground and the moon rock environment, the systematic moon simulation environment is provided, the precision influence and the time waste caused by conversion of test objects in the different environments during simulation test can be removed, the test efficiency is improved, and simulation authenticity and precision are improved.

Description

Lunar-based environmental simulation device

Technical field

The invention relates to the technical field of lunar environment simulation, in particular to a lunar-based environment simulation device.

Background technique

The moon is the closest celestial body to the earth and the only natural satellite of the earth. With the advancement of modern science and technology and the development of space activities, the moon has become the first choice for mankind to carry out space exploration. Countries around the world have carried out many studies on the lunar core.

At present, most of the lunar simulation environmental tests carried out on the ground are single-factor test methods. For example, only a certain extreme environment such as vacuum or moon dust is simulated, and the experimental results are not enough to reflect the comprehensive effects of the lunar complex environment and affect the test accuracy.

Summary of the invention

In order to solve the above-mentioned problem, the embodiment of the present invention provides a lunar-based environment simulation device that can improve the accuracy of the test.

A lunar-based environment simulation device includes a lunar ground simulation system and a lunar rock simulation system that are connected to each other. The lunar ground simulation system is used for the simulation device to simulate the lunar ground environment, and the lunar rock simulation system is used for the simulation device to simulate the lunar rock surroundings.

The lunar-based environment simulation device provided by the present invention considers the simulation of the lunar ground environment and the lunar rock environment (underground environment), provides a more systematic lunar simulation environment, improves the simulation authenticity and accuracy, and improves the test accuracy. Because the moon-based environment simulation device eliminates the accuracy impact and time waste caused by the conversion of test objects in different environments during the simulation test, the test efficiency is improved.

Description of the drawings

In order to explain the technical solutions in the embodiments of the present invention more clearly, the following will briefly introduce the drawings that need to be used in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. A person of ordinary skill in the art can obtain other drawings based on these drawings without creative work.

FIG. 1 is a schematic diagram of a three-dimensional assembly of a moon-based environment simulation device provided by a first embodiment of the present invention.

FIG. 2 is a three-dimensional assembly diagram of the moon-based environment simulation device shown in FIG. 1 with a part of the structure removed.

FIG. 3 is a schematic diagram of the moon-based environment simulation device shown in FIG. 1 from another perspective.

4 is a cross-sectional view of the lunar-based environment simulation device shown in FIG. 1.

Fig. 5 is a partial enlarged schematic diagram of the microgravity simulation system of the lunar-based environment simulation device shown in Fig. 1.

6 is a schematic diagram of a three-dimensional assembly of a moon-based environment simulation device provided by a second embodiment of the present invention.

Fig. 7 is a cross-sectional view of the moon-based environment simulation device shown in Fig. 6.

FIG. 8 is a schematic diagram of the moon-based environment simulation device shown in FIG. 6 from another perspective.

FIG. 9 is a three-dimensional assembly diagram of the moon-based environment simulation device shown in FIG. 6 with a part of the structure removed.

Fig. 10 is a partial enlarged schematic diagram of the temperature adjustment system of the moon-based environment simulation device shown in Fig. 6.

FIG. 11 is a partial enlarged schematic diagram of the microgravity simulation system of the lunar-based environment simulation device shown in FIG. 6.

detailed description

The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work shall fall within the protection scope of the present invention.

The first embodiment

Please refer to FIG. 1 and FIG. 2. FIG. 1 is a three-dimensional assembly diagram of a moon-based environment simulation device according to a first embodiment of the present invention. FIG. 2 is a three-dimensional assembly diagram of the moon-based environment simulation device shown in FIG. 1 with a part of the structure removed.

A lunar-based environment simulation device 100 includes a lunar ground simulation system 101 and a lunar rock simulation system 103 connected to each other. The lunar ground simulation system 101 is used to simulate the lunar ground environment. The lunar rock simulation system 103 is used to simulate the lunar rock environment to simulate the lunar underground environment.

The lunar-based environment simulation device 100 provided in this embodiment takes into account the comprehensive and complex environment of the lunar ground and underground, and improves the accuracy of simulating the lunar-based environment on the earth, thereby improving the test accuracy. In addition, because the test object does not need to be switched in different environments, time is saved and test efficiency is improved.

Specifically, the lunar ground simulation system 101 includes a simulation cabin 10, a lunar soil simulation system 20, and a vacuum simulation system 30. Both the lunar soil simulation system 20 and the vacuum simulation system 30 are connected to the simulation cabin 10. The lunar soil simulation system 20 is used to provide the simulation module 10 with a lunar soil simulation environment of the moon, and the vacuum simulation system 30 is used to vacuum the simulation module 10 to simulate the vacuum environment of the moon.

The lunar soil simulation system 20 includes a lunar soil simulation object 21. The simulation cabin 10 is fixedly arranged on the lunar soil simulant 21, and the lunar rock simulation system 103 is arranged on the side of the lunar soil simulant 21 away from the simulation cabin 10. The test subject (not shown in the figure) can walk on the lunar soil simulant 21 for testing. It can be understood that the test object may be other equipment or devices such as a coring system, a spacecraft, etc., which is not limited here.

The lunar soil simulation system 20 also includes a dust sprayer 22, a charged particle accelerator 23, and an ultraviolet generating device 25 fixed on the simulation cabin 10. The dust sprayer 22 is fixed to the simulation cabin 10 and is used to provide a lunar dust simulant in the simulation cabin 10 to simulate the dust environment on the surface of the moon. The charged particle accelerator 23 is used to generate a proton beam to charge the moon dust simulant with static electricity. When the test subject moves on the lunar soil simulant 21, the surface of the test subject can adhere to the raised simulated moon dust. The ultraviolet generating device 23 is used to emit ultraviolet rays into the simulation cabin 10 to simulate the photoelectric effect of moon dust under the action of ultraviolet rays. Since the lunar ground simulation system 101 is provided with a charged particle accelerator 23, an ultraviolet generating device 25, and a dust sprayer 22, it simulates the dust environment on the moon, thereby improving the simulation accuracy of the lunar ground environment. It can be understood that the lunar soil simulation system 20 can omit the dust sprayer 22, the charged particle accelerator 23, and the ultraviolet generating device 25.

In this embodiment, the preparation of the lunar soil simulant 21 can be referred to the following description: the lunar soil simulant 21 is obtained after pretreatment of soil with similar physical and chemical properties as the lunar soil by crushing, size grading, particle size grading, mixing, and outgassing. , The particle size of the lunar soil is very small, and the particles below 1 mm account for more than 95% of the total mass.

The mineral fragments provided in this embodiment (defined here as particles containing more than 80% of a certain mineral, mainly olivine, plagioclase, pyroxene, ilmenite, spinel, etc.), primitive crystalline rock fragments ( Basalt, plagioclase, peridotite, Suchangite, etc.), breccia fragments, various glasses (melted rock, microbreccia, impact glass, yellow or black igneous fragment glass), bonded agglomerates, After pre-processing, meteorite fragments, etc., act as simulants of moon dust and lunar soil.

The lunar rock simulation system 103 includes an insulated container 1031 and a lunar rock simulant 1033 contained in the insulated container 1031. The lunar rock simulant 1033 and the lunar soil simulant 21 are arranged in a layered manner. The lunar rock simulant 1033 is arranged on the side of the lunar soil simulant 21 away from the simulation cabin 10.

In this embodiment, the preparation of the lunar rock simulant 1033 can be referred to the following description: According to the topographic characteristics of the moon, the lunar rock is generally divided into lunar basalt and lunar plagioclase. Therefore, the simulation cabin 10 can use basalt blocks and different The particle size basalt material is mixed and prepared, and the lunar rock simulant 1033 is heated in different regions according to the temperature distribution characteristics of the moon surface at different depths to simulate the most realistic lunar surface environment, that is, the lunar rock simulant 1033 includes at least two regions with different temperatures .

More specifically, the simulation cabin 10 includes a first cabin 11 and a second cabin 13 communicating with the first cabin 11. A cabin door 111 is provided on the first cabin 11. The cabin door 111 is used to open or close the first cabin 11. An observation window 112 is provided on the first cabin 11. The observation window 112 is used for the tester to observe and record the experimental conditions inside the first cabin 11. Among them, the dust sprayer 22, the charged particle accelerator 23 and the ultraviolet generating device 25 are all installed on the second cabin 11.

It can be understood that the number of the cabin doors 111 is not limited. For example, the number of the cabin doors 111 may be one or more than two. It can be understood that the number of observation windows 112 is not limited, for example, the number of observation windows 112 may be one or more than two. It can be understood that the installation position of the observation window 112 is not limited, and the observation window 112 may be arranged on the first cabin 11 and/or the cabin door 111.

Please refer to FIG. 3. FIG. 3 is a schematic diagram of the moon-based environment simulation device shown in FIG. 1 from another perspective. The vacuum simulation system 30 includes a gas storage tank 31, a vacuum pump 32, a Rhodes pump 33, an oil diffusion pump 34 and a pipeline 35, and the gas storage tank 31, the vacuum pump 32, the Rhodes pump 33 and the oil diffusion pump 34 are connected through the pipeline 35 in sequence. The vacuum pump 32, the Roots pump 33, and the oil diffusion pump 35 are used for pumping the simulation cabin 10 to simulate the lunar vacuum environment. It can be understood that the structure of the vacuum simulation system 30 is not limited, as long as it can satisfy the requirements for pumping air in the simulation cabin 10.

Furthermore, the vacuum simulation system 30 further includes a mounting bracket 37, and the vacuum pump 32 and the Roots pump 33 are arranged on the mounting bracket 37.

There is almost no atmosphere and atmospheric activity on the surface of the moon, and the temperature difference between day and night is very large. The temperature is 403-423K during the day and 93-113K at night. With the change of the lunar surface temperature, the lunar surface pressure changes in the range of ^{10 -9} to 10 ^{-13 Pa.} At the poles of the moon, there are meteorite impact craters that are not irradiated by the sun all year round. The temperature is 40-50K, and the water ice content is (66-200)×10 ⁸ t. Please refer to FIGS. 1 and 2 again. In this embodiment, the lunar ground simulation system 101 further includes a temperature adjustment system 40 disposed in the simulation cabin 10 for adjusting the temperature in the simulation cabin 10 to simulate the extreme temperature environment of the moon. It can be understood that the temperature in the simulation cabin 10 at different time points is adjusted by the temperature adjustment system 40.

Further, the inner wall of the first cabin 11 is coated with a heat sink 15 for simulating the extremely cold and extremely dark environment of the moon. The temperature adjustment system 40 includes a gas helium temperature adjustment system 41 and a liquid nitrogen refrigeration system 43 arranged in series with the gas helium temperature adjustment system 41 to realize the temperature adjustment of the heat sink 15. In this embodiment, the liquid nitrogen provided by the liquid nitrogen refrigeration system 43 is further cooled to 70K by the gas helium provided by the gas helium temperature control system 41; in the temperature range of 150-400K, the gas helium temperature control system 41 is used to control the heat sink. 15 temperature. It can be understood that, according to actual requirements, the gas-helium temperature adjustment system 41 and the liquid nitrogen refrigeration system 43 are controlled to adjust the temperature in the simulation cabin 10.

The gas helium temperature control system 41 includes a helium generator 411, a compressor 413, a helium storage device 415 and a gas pipe 417. The compressor 413 is connected to the helium generator 411 through the gas pipe 417, and the helium generator 411 is connected to the helium storage device 415 through the gas pipe 417. Phase connection. The helium generator 411 is used to prepare helium, and the compressor 413 is used to compress the prepared helium and store it in the helium storage device 415.

The liquid nitrogen refrigeration system 43 includes a nitrogen generator 431, a liquid nitrogen storage device 433, a compressor 435, and a gas pipe 437. The compressor 435 is connected to the nitrogen generator 431 through the gas pipe 437, and the nitrogen generator 431 is connected to the liquid nitrogen storage device through the gas pipe 437. 433 is connected. The nitrogen generator 431 is used to produce nitrogen gas, and the compressor 435 is used to compress the produced nitrogen gas and store it in the liquid nitrogen storage device 433.

The temperature adjustment system 40 also includes an array lamp 45 (as shown in FIG. 2). The array lamp 45 is housed in the simulation cabin 10 and is used to simulate the collimated light of the sun. As the array lamp 45 is used to simulate the solar spectrum, heat flux, and altitude angle, the simulation accuracy of the lunar environment device 100 for the lunar environment is further improved. In this embodiment, the array lamp 45 is an infrared lamp array, which can be used as a part of the heat source at the same time to adjust the temperature in the simulation cabin 10.

Please refer to FIGS. 4 and 5. FIG. 4 is a cross-sectional view of the lunar-based environment simulation device shown in FIG. 1, and FIG. 5 is a partial enlarged schematic diagram of the microgravity simulation system of an embodiment of the lunar-based environment simulation device of the present invention.

The lunar ground simulation system 101 also includes a microgravity simulation system 50. The microgravity simulation system 50 is located in the first cabin 11 of the simulation cabin 10 to provide tensile force to the test subject in the simulation cabin 10 and offset part of the earth's gravity received by the test subject , To simulate the microgravity environment of the test object on the moon.

The microgravity simulation system 50 includes a support frame 51 and a mobile suspension device 53. The support frame 51 is fixed on the inner wall of the first cabin 11 for supporting the mobile suspension device 53. The mobile suspension device 53 is movably arranged on the support frame 51. The mobile suspension device 53 includes a first guide rail 511, a second guide rail 512, a mobile platform 513, a connecting member 514, a first driving member 515 and a second driving member 516. The first guide rail 511 is fixedly disposed on the support frame 51, and the first guide rail 511 extends along a first direction (for example, the Y direction). The second guide rail 512 is in sliding contact with the first guide rail 511. The second guide rail 512 extends in the second direction (for example, the X direction). The moving platform 513 is slidably connected to the second guide rail 512. The connecting piece 514 is suspended on the mobile platform 513 and is used to connect with the test object to provide tension to the test object. A hook (not shown) is provided at the end of the connecting piece 514 away from the mobile platform 513. When in use, the traction point of the hook is located at the center of mass of the test object. The first driving member 515 is fixed on the first guide rail 511 for driving the second guide rail 512 to move along the first guide rail 511. The second driving member 515 is fixed on the second guide rail 512 for driving the mobile platform 513 to move along the second guide rail 512. The first driving member 515 and the second driving member 516 can adjust the position of the moving platform 513 according to the motion trajectory of the test object, so as not to affect the motion of the test object.

The microgravity simulation system 50 uses the principle of gravity compensation on the test object, through the combination of guide rails, suspension and other structures and counterweights, to satisfy the completely unconstrained six degrees of freedom, and truly simulate the operation of the lunar surface. It can be understood that the microgravity simulation system 50 is not limited to the structure exemplified in this embodiment, and the microgravity simulation system 50 may also be other structures or devices. For example, the microgravity simulation system 50 may adopt a balloon suspension method.

Please refer to FIG. 2 again. The moon-based environment simulation device 100 further includes a radiation environment simulation system 60. The radiation environment simulation system 60 includes a radiation device 61 and a radiation radiation element 63. The ray device 61 is installed on the second cabin body 13 of the simulation cabin 10 for emitting rays into the simulation cabin 10 to simulate cosmic rays. In this embodiment, the radiation device 61 is used to emit x and y rays. It can be understood that the ray device 61 does not limit the emission of x-rays and y-rays. For example, the ray device 61 may only emit one of x-rays and y-rays or other types of rays. The radiation radiating element 63 is located inside the first cabin 11 of the simulation cabin 10. In this embodiment, the radiation radiating element 63 is a substantially annular radiation radiating ring, the number of the radiating radiating element 63 is two, the two radiating radiating elements 63 are arranged at intervals, and the radiating radiating element 63 passes through a heat insulating layer (not shown) Separate from heat sink 15. The array lamp 45 is located between the two radiating elements 63.

It can be understood that the number of radiation radiating elements 63 may be one, three or more; in order to make the radiation of each position in the simulation cabin 10 uniform, the arrangement density and size of the radiation radiating elements 63 can be improved by increasing the arrangement density and size of the radiation elements 63. In one embodiment, the lunar-based environment simulation device 100 further includes a detector (not shown), the detector is used to detect the radiation intensity in the first cabin 11 of the simulation cabin 10, and the controller is based on the detection by the detector. The radiation intensity is used to control the radiation intensity of the radiation radiation element 63. It can be understood that the radiation environment simulation system 60 includes at least one of a radiation device 61 and a radiation radiation element 63

The lunar-based environment simulation device 100 provided by the first embodiment of the present invention simulates the extreme lunar ground environment such as vacuum, microgravity, extreme temperature difference, high cosmic radiation, and fine dust, and considers the underground environment factors of simulating lunar rock. The authenticity of the simulation of the lunar environment is improved, and the accuracy of the tests such as walking, detection, and coring of the test object on the lunar-based environment simulation device 100 is improved.

Second embodiment

Please refer to FIG. 6 and FIG. 7. FIG. 6 is a three-dimensional assembly diagram of the moon-based environment simulation device provided by the second embodiment of the present invention. Fig. 7 is a cross-sectional view of the moon-based environment simulation device shown in Fig. 6. A lunar-based environment simulation device 200 includes a lunar ground simulation system 201 and a lunar rock simulation system 203 connected to each other. The lunar ground simulation system 201 is used to simulate the lunar ground environment. The lunar rock simulation system 203 is used to simulate the lunar rock environment to simulate the lunar underground environment.

The lunar ground simulation system 201 includes a simulation cabin 70, a lunar soil simulation system 80, and a vacuum simulation system 90. Both the lunar soil simulation system 80 and the vacuum simulation system 90 are connected to the simulation cabin 70. The lunar soil simulation system 80 is used to provide the lunar soil simulation environment of the moon to the simulation module 70, and the vacuum simulation system 90 is used to vacuum the simulation module 70 to simulate the vacuum environment of the moon.

The lunar soil simulation system 80 includes a lunar soil simulant 81, and the lunar soil simulant 81 is housed in the simulation cabin 70.

The lunar ground simulation system 201 also includes an orbit 89 fixed on the surface of the lunar soil simulant 81. The track 89 is used to facilitate the test subject to walk or move other equipment. It can be understood that the installation position and installation direction of the rail 89 are not limited. It can be understood that the number of tracks 89 is not limited. For example, the number of tracks 89 may be one, three or more.

The lunar soil simulation system 80 also includes a dust sprayer 82, a charged particle accelerator 83 and an ultraviolet generating device 85 fixed on the simulation cabin 70. The dust sprinkler 82 is fixed to the simulation cabin 70 and is used to provide a lunar dust simulant in the simulation cabin 10 to simulate the dust environment on the surface of the moon. The charged particle accelerator 83 is used to generate a proton beam to charge the moon dust simulant with static electricity. When the test subject moves on the lunar soil simulant 81, the surface of the test subject can adhere to the raised simulated moon dust. The ultraviolet generating device 85 is used to emit ultraviolet rays into the simulation cabin 70 to simulate the photoelectric effect of moon dust under the action of ultraviolet rays. Since the lunar ground simulation system 201 is provided with a dust sprayer 82, a charged particle accelerator 83 and an ultraviolet generating device 85, it simulates the dust environment on the moon, thereby improving the simulation accuracy of the lunar ground environment.

The lunar rock simulation system 203 is buried in the lunar soil simulant 81. The moon rock simulation system 203 includes an insulated container 2031 and a moon rock simulant 2033 contained in the insulated container 2031. The lunar rock simulant 2033 is separated from the lunar soil simulant 81 by the insulated container 2031. It can be understood that the number of moon rock simulation systems 203 may be two, three or more.

More specifically, the simulation cabin 70 includes a first cabin 71 and a second cabin 73 connected to the first cabin 71. A cabin door 711 is provided on the first cabin body 71. The cabin door 711 is used to open or close the first cabin 71. It can be understood that, in some embodiments, an observation window (not shown in the figure) may be provided on the cabin door 711. The observation window is used for the tester to observe and record the experimental conditions inside the first cabin 11.

It can be understood that the number of cabin doors 711 is not limited. For example, the number of cabin doors 711 may be one or more than two.

Further, the cabin door 711 includes a cabin door frame 7111, a connecting piece 7113, and a cabin door leaf 7115. The door leaf 7115 is slidably connected to the door frame 7111 through the connecting piece 7113, so that the door leaf 7115 can slide along the door frame 7111, which facilitates opening or closing of the first cabin body 71, thereby improving the test efficiency.

Please refer to FIG. 8. FIG. 8 is a schematic diagram of the moon-based environment simulation device shown in FIG. 6 from another perspective. The vacuum simulation system 90 includes a gas storage tank 91, a vacuum pump 92, a Rhodes pump 93, an oil diffusion pump 94 and a pipeline 95. The gas storage tank 91, the vacuum pump 92, the Rhodes pump 93 and the oil diffusion pump 94 are connected through the pipeline 95 in sequence. The vacuum pump 92, the Rhodes pump 93, and the oil diffusion pump 95 are used for pumping the simulation cabin 70 to simulate the lunar vacuum environment. It can be understood that the structure of the vacuum simulation system 90 is not limited, as long as it can meet the requirements for pumping the simulation cabin 70.

Furthermore, the vacuum simulation system 90 further includes a mounting bracket 97, and the vacuum pump 92 and the Roots pump 93 are arranged on the mounting bracket 97.

Please refer to FIGS. 9 and 10. FIG. 9 is a three-dimensional assembly diagram of the moon-based environment simulation device shown in FIG. 6 with a part of the structure removed. Fig. 10 is a partial enlarged schematic diagram of the temperature adjustment system of the moon-based environment simulation device shown in Fig. 6.

In this embodiment, the lunar ground simulation system 201 further includes a temperature adjustment system 130 provided in the simulation cabin 70 for adjusting the temperature in the simulation cabin 70 to simulate the extreme temperature environment of the moon. It can be understood that the temperature of the temperature adjustment system 130 at different time points is controlled by the controller.

Further, the inner wall of the first cabin 71 is coated with a heat sink 75 for simulating the extremely cold and extremely dark environment of the lunar environment. The temperature adjustment system 130 includes a gas helium temperature adjustment system 102 and a liquid nitrogen refrigeration system 104 arranged in series with the gas helium temperature adjustment system 102 to realize the temperature adjustment of the heat sink 75 to adjust the temperature in the simulation cabin 70. In this embodiment, the liquid nitrogen provided by the liquid nitrogen refrigeration system 104 is further cooled to 70K by the gas helium provided by the gas-helium temperature regulating system 102; in the temperature range of 150-400K, the gas-helium temperature regulating system 102 is used to control the heat sink. 75 temperature. It can be understood that the gas-helium temperature adjustment system 102 and the liquid nitrogen refrigeration system 104 are controlled to adjust the temperature in the simulation cabin 70 according to actual needs.

The gas helium temperature control system 102 includes a helium generator 1011, a compressor 1013, a helium storage device 1015, and a gas pipe 1017. The compressor 1013 is connected to the helium generator 1011 through the gas pipe 1017, and the helium generator 1011 is connected to the helium storage device 1015 through the gas pipe 1017. Phase connection. The helium generator 1011 is used to prepare helium, and the compressor 1013 is used to compress the prepared helium and store it in the helium storage device 1015.

The liquid nitrogen refrigeration system 104 includes a nitrogen generator 1035, a liquid nitrogen storage device 1036, a compressor 1037, and a gas pipe 1038. The compressor 1037 is connected to the nitrogen generator 1035 through the gas pipe 1038, and the nitrogen generator 1035 is connected to the liquid nitrogen storage device through the gas pipe 1038. 1036 is connected. The nitrogen generator 1035 is used to produce nitrogen, and the compressor 1037 is used to compress the produced nitrogen and store it in the liquid nitrogen storage device 1036.

The temperature adjustment system 130 also includes an array lamp 105, which is housed in the simulation cabin 70, and is used to simulate the collimated light of the sun. As the array lamp 105 is used to simulate the solar spectrum, heat flux, and altitude angle, the simulation accuracy of the lunar environment device 100 for the lunar environment is further improved. In this embodiment, the array lamp 105 is an infrared lamp array, which can be used as a part of the heat source at the same time to adjust the temperature in the simulation cabin 70.

Please refer to FIGS. 7, 9 and 11 again. FIG. 11 is a partial enlarged schematic diagram of the microgravity simulation system of the lunar-based environment simulation device shown in FIG. 6.

The lunar ground simulation system 201 also includes a microgravity simulation system 110. The microgravity simulation system 110 is located in the first cabin 71 of the simulation cabin 70 to provide tensile force to the test subject in the simulation cabin 70 and offset part of the earth's gravity received by the test subject , To simulate the microgravity environment of the test object on the moon.

The microgravity simulation system 110 includes a support frame 1101 and a mobile suspension device 1103. The support frame 1101 is fixed on the inner wall of the first cabin 71 for supporting the mobile suspension device 1103. The mobile suspension device 1103 is movably arranged on the support frame 1101. The mobile suspension device 1103 includes a first guide rail 1104, a second guide rail 1105, a mobile platform 1106, a connecting member 1107, a first driving member 1108, and a second driving member 1109. The first guide rail 1104 is fixedly disposed on the support frame 1101, and the first guide rail 1104 extends along a first direction (for example, the Y direction). The second guide rail 1105 is in sliding contact with the first guide rail 1104. The second guide rail 1105 extends in the second direction (for example, the X direction). The mobile platform 1106 is slidably connected to the second guide rail 1105. The connecting piece 1107 is suspended on the mobile platform 1106 and is used to connect with the test object to provide tensile force to the test object. A hook (not shown in the figure) is provided at the end of the connecting piece 1107 away from the mobile platform 1106. When in use, the traction point of the hook is located at the center of mass of the test object. The first driving member 1108 is fixed on the first guide rail 1104 and is used to drive the second guide rail 1105 to move along the first guide rail 1104. The second driving member 1109 is fixed on the second guide rail 1105 for driving the mobile platform 1106 to move along the second guide rail 1105. The first driving member 1108 and the second driving member 1109 can adjust the position of the moving platform 513 according to the motion trajectory of the test object, so as not to affect the motion of the test object.

The microgravity simulation system 110 uses the principle of gravity compensation on the test object, through the combination of guide rails, suspension and other structures and counterweights, to satisfy the completely unconstrained six degrees of freedom, and truly simulate the operation of the lunar surface. It can be understood that the microgravity simulation system 110 is not limited to the structure exemplified in this embodiment. The microgravity simulation system 110 may also be other structures or devices. For example, the microgravity simulation system 110 may also be a balloon suspension.

The moon-based environment simulation device 200 further includes a radiation device 121. The ray device 121 is installed in the second cabin 72 of the simulation cabin 70 for emitting rays into the simulation cabin 70 to simulate cosmic rays. In this embodiment, the radiation device 121 is used to emit x and y rays. It can be understood that the radiation device 121 does not limit the emission of x-rays and y-rays. For example, the radiation device 121 may only emit one or other types of x-rays and y-rays.

The lunar-based environment simulation device 200 provided by the second embodiment of the present invention simulates the extreme lunar ground environment such as vacuum, microgravity, extreme temperature difference, high cosmic radiation, and fine dust, as well as the simulation of the underground environment that simulates the lunar rock. The authenticity of the simulation of the lunar environment is improved, and the accuracy of the tests such as walking, detection, and coring of the test object on the lunar-based environment simulation device 200 is improved.

The above are the preferred embodiments of the present invention. It should be pointed out that for those of ordinary skill in the art, without departing from the principle of the present invention, several improvements and modifications can be made, and these improvements and modifications are also considered. This is the protection scope of the present invention.

Claims

A lunar-based environment simulation device, wherein the lunar-based environment simulation device includes a lunar ground simulation system and a lunar rock simulation system that are connected to each other, and the lunar ground simulation system is used to simulate the lunar ground environment. The simulation system is used to simulate the lunar rock environment.
The lunar-based environment simulation device according to claim 1, wherein the lunar ground simulation system includes a simulation cabin, a lunar soil simulant, and a vacuum simulation system, and the inner cavity of the simulation cabin and the lunar soil simulant Connected, the lunar soil simulant is used for the test subject to walk, the lunar rock simulation system is connected with the lunar soil simulant, and the vacuum simulation system is connected with the simulation cabin for pumping the simulation cabin Vacuum to simulate the lunar vacuum environment.
The lunar-based environment simulation device according to claim 2, wherein the simulation cabin is fixedly arranged on the lunar soil simulant, and the lunar rock simulation system is arranged on the lunar soil simulant away from the simulation. One side of the cabin.
3. The lunar-based environment simulation device according to claim 2, wherein the lunar rock simulation system is embedded in the lunar soil simulation object.
The lunar-based environment simulation device according to any one of claims 2 to 4, wherein the lunar rock simulation system comprises an insulated container and a lunar rock simulant contained in the insulated container.
The lunar-based environment simulation device according to claim 2, wherein the lunar ground simulation system further comprises a dust sprayer arranged on the simulation cabin, and the dust sprayer is used to provide moon to the simulation cabin. Dust simulant to simulate the dusty environment of the moon.
The lunar-based environment simulation device according to claim 6, wherein the lunar ground simulation system further comprises a charged particle accelerator fixed to the simulation cabin, and the charged particle accelerator is used to generate a proton beam to make the moon The dust simulant is electrostatically charged.
The lunar-based environment simulation device according to claim 6, wherein the lunar ground simulation system further comprises an ultraviolet generating device, and the ultraviolet generating device is used to emit ultraviolet rays into the simulation cabin to simulate the lunar dust The photoelectric effect occurs under the action of ultraviolet light.
The lunar-based environment simulation device according to claim 2, wherein the lunar ground simulation system further comprises a temperature adjustment system arranged on the simulation cabin for adjusting the temperature in the simulation cabin to simulate the moon Temperature environment.
9. The lunar-based environment simulation device according to claim 9, wherein the temperature adjustment system comprises a gas helium temperature adjustment system and a liquid nitrogen refrigeration system arranged in series with the gas helium temperature adjustment system.
9. The lunar-based environment simulation device according to claim 9, wherein the temperature adjustment system further comprises an array lamp housed in the simulation cabin for simulating the collimated light of the sun.
The lunar-based environment simulation device according to claim 2, wherein the lunar ground simulation system further comprises a microgravity simulation system, the microgravity simulation system is located in the simulation cabin, and is used to provide Pull force to simulate the microgravity environment of the test subject on the moon.
The lunar-based environment simulation device of claim 12, wherein the microgravity simulation system includes a support frame and a mobile suspension device, the support frame is fixed on the inner wall of the simulation cabin, and the mobile suspension The suspension device is movably arranged on the support frame, and the mobile suspension device is used to provide tensile force to the test object located in the simulation cabin.
The moon-based environment simulation device according to claim 13, wherein the mobile suspension device comprises a first guide rail, a second guide rail, a mobile platform, a connecting member, a first driving member and a second driving member, and The first guide rail is fixedly arranged on the support frame, the second guide rail is slidably connected to the first guide rail, the mobile platform is slidably connected to the second guide rail, and the connecting piece is suspended from the mobile On the platform, it is used to connect with the test object.
The lunar-based environment simulation device according to claim 2, wherein the lunar ground simulation system further comprises a radiation environment simulation system, the radiation environment simulation system is located in the simulation cabin, and is used to simulate the effects of the moon Radiation environment, the radiation environment simulation system includes at least one of a ray device and the radiation radiation element.