CN110539900A - Moon-based environment simulation device - Google Patents
Moon-based environment simulation device Download PDFInfo
- Publication number
- CN110539900A CN110539900A CN201910819525.0A CN201910819525A CN110539900A CN 110539900 A CN110539900 A CN 110539900A CN 201910819525 A CN201910819525 A CN 201910819525A CN 110539900 A CN110539900 A CN 110539900A
- Authority
- CN
- China
- Prior art keywords
- lunar
- simulation
- environment
- simulation system
- chamber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000004088 simulation Methods 0.000 title claims abstract description 222
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 title claims description 44
- 238000012360 testing method Methods 0.000 claims abstract description 50
- 239000011435 rock Substances 0.000 claims abstract description 36
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 58
- 239000002689 soil Substances 0.000 claims description 39
- 239000001307 helium Substances 0.000 claims description 36
- 229910052734 helium Inorganic materials 0.000 claims description 36
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 36
- 230000005855 radiation Effects 0.000 claims description 34
- 239000007789 gas Substances 0.000 claims description 31
- 229910052757 nitrogen Inorganic materials 0.000 claims description 28
- 239000000428 dust Substances 0.000 claims description 27
- 230000005486 microgravity Effects 0.000 claims description 26
- 239000007788 liquid Substances 0.000 claims description 17
- 239000002245 particle Substances 0.000 claims description 15
- 239000000725 suspension Substances 0.000 claims description 15
- 230000007613 environmental effect Effects 0.000 claims description 13
- 230000001105 regulatory effect Effects 0.000 claims description 8
- 230000000694 effects Effects 0.000 claims description 6
- 238000005057 refrigeration Methods 0.000 claims description 5
- 238000004891 communication Methods 0.000 claims description 3
- 238000006243 chemical reaction Methods 0.000 abstract description 2
- 230000009897 systematic effect Effects 0.000 abstract description 2
- 239000002699 waste material Substances 0.000 abstract description 2
- 238000003860 storage Methods 0.000 description 12
- 238000009792 diffusion process Methods 0.000 description 6
- JJWKPURADFRFRB-UHFFFAOYSA-N carbonyl sulfide Chemical compound O=C=S JJWKPURADFRFRB-UHFFFAOYSA-N 0.000 description 4
- 230000001276 controlling effect Effects 0.000 description 4
- 230000005484 gravity Effects 0.000 description 4
- 239000011521 glass Substances 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 229910001873 dinitrogen Inorganic materials 0.000 description 2
- 230000004907 flux Effects 0.000 description 2
- 229910052500 inorganic mineral Inorganic materials 0.000 description 2
- 239000011707 mineral Substances 0.000 description 2
- 229910052609 olivine Inorganic materials 0.000 description 2
- 239000010450 olivine Substances 0.000 description 2
- 229910052655 plagioclase feldspar Inorganic materials 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 238000001228 spectrum Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000010433 feldspar Substances 0.000 description 1
- YDZQQRWRVYGNER-UHFFFAOYSA-N iron;titanium;trihydrate Chemical compound O.O.O.[Ti].[Fe] YDZQQRWRVYGNER-UHFFFAOYSA-N 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 229910052611 pyroxene Inorganic materials 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 229910052596 spinel Inorganic materials 0.000 description 1
- 239000011029 spinel Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
The invention provides a lunar ground environment simulation device which comprises a lunar ground simulation system and a lunar rock simulation system which are connected, wherein the lunar ground simulation system is used for simulating a lunar ground environment by the simulation device, and the lunar rock simulation system is used for simulating a lunar rock environment. Because the simulated lunar ground and lunar rock environment are considered, a more systematic lunar simulated environment is provided, the problems of precision influence and time waste caused by conversion in different environments during the simulation test of a test object are solved, the test efficiency is improved, and the simulation authenticity and precision are improved.
Description
Technical Field
The invention relates to the technical field of lunar environment simulation, in particular to a lunar environment simulation device.
Background
The moon is the celestial body closest to the earth and is the only natural satellite of the earth. With the progress of modern science and technology and the development of space activities, the moon becomes the first choice target for people to carry out space exploration, and countries in the world now carry out a lot of research aiming at lunar coring.
At present, most of lunar simulation environment tests carried out on the ground are single-factor test methods, for example, only one extreme environment such as vacuum or lunar dust is simulated, and the test result is not enough to reflect the comprehensive action condition of the complex environment of the lunar, so that the test precision is influenced.
Disclosure of Invention
In order to solve the above problem, embodiments of the present invention provide a lunar environment simulation apparatus capable of improving test accuracy.
The lunar ground simulation system is used for simulating the lunar ground environment by the simulation device, and the lunar rock simulation system is used for simulating the lunar ground environment by the simulation device.
The lunar environment simulation device provided by the invention considers the simulated 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. The moon-based environment simulation device solves the problems of precision influence and time waste caused by conversion in different environments during simulation test of test objects, and improves the test efficiency.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic perspective assembly view of a lunar environment simulation apparatus according to a first embodiment of the present invention.
Fig. 2 is a perspective assembly view of the environment simulator with a portion removed from the structure of the environment simulator shown in fig. 1.
FIG. 3 is another perspective view of the environmental simulator shown in FIG. 1.
FIG. 4 is a cross-sectional view of the lunar environment simulator shown in FIG. 1.
Fig. 5 is a partially enlarged schematic view of the microgravity simulation system of the moon-based environmental simulation apparatus shown in fig. 1.
Fig. 6 is a schematic perspective assembly diagram of a moon-based environmental simulation apparatus according to a second embodiment of the present invention.
FIG. 7 is a cross-sectional view of the lunar environment simulator shown in FIG. 6.
FIG. 8 is a schematic view of the environmental simulator shown in FIG. 6 from another perspective.
Fig. 9 is a perspective assembly view of the environment simulator with a portion removed from the structure of the environment simulator shown in fig. 6.
Fig. 10 is a partially enlarged schematic view of the temperature control system of the environmental simulator shown in fig. 6.
Fig. 11 is a partially enlarged schematic view of the microgravity simulation system of the moon-based environmental simulation apparatus shown in fig. 6.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
First embodiment
Referring to fig. 1 and fig. 2, fig. 1 is a schematic perspective assembly view of a lunar environment simulation apparatus according to a first embodiment of the present invention. Fig. 2 is a perspective assembly view of the environment simulator with a portion removed from the structure of the environment simulator shown in fig. 1.
A moon-based environmental simulation device 100 comprises a moon ground simulation system 101 and a lunar rock simulation system 103 which are connected. The lunar surface simulation system 101 is used to simulate a lunar surface environment. The lunar rock simulation system 103 is used to simulate a lunar rock environment to simulate a lunar subsurface environment.
The lunar environment simulation apparatus 100 according to the present embodiment considers comprehensive complex environments of the lunar ground and the underground, and improves the accuracy of simulating the lunar environment on the earth, thereby improving the test accuracy. In addition, because the test object does not need to be converted in different environments, the time is saved, and the test efficiency is improved.
Specifically, the lunar surface simulation system 101 includes a simulation chamber 10, a lunar soil simulation system 20, and a vacuum simulation system 30. The lunar soil simulation system 20 and the vacuum simulation system 30 are both communicated with the simulation cabin 10. The lunar soil simulation system 20 is used to provide a lunar soil simulation environment for the moon to the simulation chamber 10, and the vacuum simulation system 30 is used to evacuate the simulation chamber 10 to simulate the vacuum environment of the moon.
Lunar soil simulation system 20 includes lunar soil simulant 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 lunar soil simulant 21 at the side far away from the simulation cabin 10. The test subject (not shown) may walk over the lunar soil simulant 21 for testing. It is to be understood that the test subject may be other devices or apparatuses such as a corer system, spacecraft, etc., and is not limited thereto.
The lunar soil simulation system 20 further includes a dust sprayer 22, a charged particle accelerator 23, and an ultraviolet ray generation device 25 fixed to the simulation chamber 10. The dust applicator 22 is secured to the simulation chamber 10 for providing a lunar dust simulant into the simulation chamber 10 for simulating a mote environment on the surface of the moon. The charged particle accelerator 23 is used to generate a proton beam to electrostatically charge the lunar dust simulant. When the test object moves on the lunar soil simulant 21, the surface of the test object can be adhered with raised simulated lunar dust. The ultraviolet generating device 23 is used for emitting ultraviolet rays into the simulation chamber 10 so as to simulate the photoelectric effect of the lunar dust under the action of the ultraviolet rays. Since the lunar ground simulation system 101 is provided with the charged particle accelerator 23, the ultraviolet ray generation device 25 and the dust sprayer 22, the environment of the tiny dust on the moon is simulated, thereby improving the simulation precision of the lunar ground environment. It is understood that the lunar soil simulation system 20 may omit the dust sprinklers 22, the charged particle accelerators 23, and the ultraviolet light generating devices 25.
In this embodiment, the preparation of the lunar soil simulant 21 can be described as follows: the lunar soil simulant 21 is obtained by adopting soil with similar physical and chemical properties with lunar soil after crushing, size grading, particle size grading, mixing and air-out pretreatment, the particle size of the lunar soil is very small, wherein the particles below 1 mm account for more than 95% of the total mass.
The mineral clasts (defined herein as particles containing more than 80% of a mineral, mainly olivine, plagioclase, pyroxene, ilmenite, spinel, etc.), primary crystalline rock clasts (basalt, plagioclase, olivine, peridotite, etc.), conglomerate clasts, various glasses (lava, micro-conglomerate, bump glass, yellow or black pyroclastic glass), cohesive conglomerate, merle clasts, etc., provided in this example, after pretreatment, serve as a simulant of lunar soil.
The lunar rock simulation system 103 includes a thermally insulated container 1031 and a lunar rock simulant 1033 contained within the thermally insulated container 1031, the lunar rock simulant 1033 being disposed in a stacked arrangement with the lunar soil simulant 21. A lunar rock simulant 1033 is arranged on the side of the lunar soil simulant 21 facing away from the simulation cabin 10.
In this embodiment, the preparation of the lunar rock simulant 1033 can be described as follows: according to lunar topographic features, lunar basalt is generally divided into lunar basalt and lunar paleo-feldspar, so that basalt blocks and basalt materials with different particle sizes can be mixed in the simulation cabin 10, and the lunar rock simulant 1033 is heated in regions according to temperature distribution features of different depths of a lunar surface so as to simulate the most real lunar surface environment, namely, the lunar rock simulant 1033 comprises 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. The first cabin 11 is provided with a cabin door 111. The hatch 111 is used to open or close the first cabin 11. The first cabin 11 is provided with an observation window 112. The observation window 112 is used for the experimenter to observe and record the experimental condition inside the first cabin 11. The dust sprayer 22, the charged particle accelerator 23 and the ultraviolet generating device 25 are disposed on the second chamber 11.
It is understood that the number of the hatches 111 is not limited, and for example, the hatches 111 may be one or more than two. It is understood that the number of the observation windows 112 is not limited, and for example, one or more than two observation windows 112 may be provided. It is understood that the position of the observation window 112 is not limited, and the observation window 112 may be disposed on the first cabin 11 and/or the door 111.
Referring to fig. 3, fig. 3 is a schematic view of the lunar environment simulation apparatus shown in fig. 1 from another perspective. The vacuum simulation system 30 includes an air tank 31, a vacuum pump 32, a lorentz pump 33, an oil diffusion pump 34, and a pipe 35, and the air tank 31, the vacuum pump 32, the lorentz pump 33, and the oil diffusion pump 34 are sequentially communicated through the pipe 35. The vacuum pump 32, the Lotz pump 33 and the oil diffusion pump 35 are used for exhausting the simulation chamber 10 to simulate a lunar vacuum environment. It is to be understood that the vacuum simulation system 30 is not limited in structure, and may be configured to evacuate the simulation chamber 10.
Further, the vacuum simulation system 30 further includes a mounting bracket 37, and the vacuum pump 32 and the lorentz pump 33 are disposed on the mounting bracket 37.
The lunar surface almost has no atmospheric layer and atmospheric activity, the temperature difference between day and night is large, the day temperature is 403-423K, and the night temperature is 93-113K. Along with the change of the surface temperature of the moon, the lunar surface air pressure is changed within the range of 10 < -9 > to 10 < -13 > Pa. Meteorite impact pits which cannot be irradiated by the sun all the year round exist at the two poles of the moon, the temperature is 40-50K, and the water ice content is (66-200) multiplied by 108 t. Referring to fig. 1 and fig. 2 again, in the present 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 will be appreciated that the temperature at various points in time within the simulation chamber 10 is regulated by the temperature regulation system 40.
Further, the inner wall of the first cabin 11 is coated with a heat sink 15 for simulating a very cold and very black environment of the moon environment. The temperature adjusting system 40 comprises a gas helium temperature adjusting system 41 and a liquid nitrogen refrigerating system 43 which is connected in series with the gas helium temperature adjusting system 41, so as to realize temperature adjustment and control of the heat sink 15. In the present embodiment, the gas helium provided by the gas helium temperature adjustment system 41 further cools the liquid nitrogen provided by the liquid nitrogen refrigeration system 43 to 70K; and controlling the temperature of the heat sink 15 by adopting a gas helium temperature regulating system 41 within the temperature range of 150-400K. It can be understood that the temperature in the simulation chamber 10 can be regulated and controlled by controlling the gas helium temperature regulating system 41 and the liquid nitrogen refrigerating system 43 according to actual requirements.
The gas helium temperature control system 41 includes a helium production machine 411, a compressor 413, a helium storage device 415, and a gas pipe 417, wherein the compressor 413 is connected to the helium production machine 411 through the gas pipe 417, and the helium production machine 411 is connected to the helium storage device 415 through the gas pipe 417. The helium generator 411 is used for generating helium gas, and the compressor 413 is used for compressing the generated helium gas and storing the compressed helium gas in the helium storage device 415.
The liquid nitrogen refrigerating system 43 comprises a nitrogen making machine 431, a liquid nitrogen storage device 433, a compressor 435 and an air pipe 437, wherein the compressor 435 is connected with the nitrogen making machine 431 through the air pipe 437, and the nitrogen making machine 431 is connected with the liquid nitrogen storage device 433 through the air pipe 437. The nitrogen generator 431 is used for generating nitrogen, and the compressor 435 is used for compressing the generated nitrogen and storing the compressed nitrogen in the liquid nitrogen storage 433.
The temperature regulation system 40 further includes an array of lights 45 (shown in fig. 2), the array of lights 45 being housed within the simulated compartment 10 for simulating collimated light of the sun. Because the array lamp 45 is adopted to simulate the solar spectrum, the heat flux and the altitude angle, the simulation accuracy of the moon environment device 100 to the moon environment is further improved. In the present embodiment, the array lamp 45 is an infrared lamp array, and can be used as a part of the heat source at the same time to adjust the temperature in the simulation chamber 10.
Referring to fig. 4 and 5, fig. 4 is a cross-sectional view of the lunar environment simulation apparatus shown in fig. 1, and fig. 5 is a partially enlarged schematic view of a microgravity simulation system according to an embodiment of the lunar environment simulation apparatus of the present invention.
The lunar ground simulation system 101 further includes a microgravity simulation system 50, and the microgravity simulation system 50 is located in the first chamber body 11 of the simulation chamber 10 to provide a pulling force for the test object in the simulation chamber 10, so as to counteract partial earth gravity borne by the test object, and realize the microgravity environment of the test object in the moon.
The microgravity simulation system 50 includes a support frame 51 and a movable suspension device 53. The support frame 51 is fixed to the inner wall of the first cabin 11 and supports the mobile suspension device 53. The movable suspension device 53 is movably disposed on the supporting frame 51. The moving suspension 53 includes a first guide rail 511, a second guide rail 512, a moving 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 (e.g., Y direction). The second guide rail 512 is slidably connected to the first guide rail 511. The second guide rail 512 extends in a second direction (e.g., the X direction). The movable platform 513 is slidably connected to the second rail 512. The connecting member 514 is suspended on the moving platform 513 and is used for connecting with the test object so as to provide tension for the test object. The end of the connecting element 514 facing away from the movable platform 513 is provided with a hook (not shown), and when in use, the traction point of the hook is located at the centroid position of the test object. The first driving member 515 is fixed to the first guide rail 511, and drives the second guide rail 512 to move along the first guide rail 511. The second driving member 515 is fixed on the second guiding rail 512, and is used for driving the moving platform 513 to move along the second guiding rail 512. The first driving element 515 and the second driving element 516 can adjust the position of the moving platform 513 according to the motion track of the test object, so as not to influence the motion of the test object.
The microgravity simulation system 50 utilizes the principle of gravity compensation on a test object, and meets the requirement of complete unrestrained six-degree-of-freedom by combining structures such as a guide rail, a suspension and the like and adding a balance weight, thereby truly simulating the operation of the surface of the moon. It is understood that the microgravity simulation system 50 is not limited to the structure illustrated in this embodiment, and the microgravity simulation system 50 may be other structures or devices, for example, the microgravity simulation system 50 may be in a balloon suspension manner.
Referring again to fig. 2, the lunar environment simulation apparatus 100 further includes a radiation environment simulation system 60. The radiation environment simulation system 60 includes a radiation device 61 and a radiation emitting element 63. The ray device 61 is installed on the second chamber 13 of the simulation chamber 10 and is used for emitting rays into the simulation chamber 10 to simulate cosmic rays. In this embodiment, the radiation device 61 is used to emit x and y rays. It is to be understood that the radiation device 61 is not limited to emitting x-and y-rays, for example, the radiation device 61 may emit only one of x-and y-rays or other types of rays. The radiation emitting elements 63 are located inside the first body 11 of the simulation chamber 10. In the present embodiment, the radiation members 63 are substantially annular radiation rings, the number of the radiation members 63 is two, the two radiation members 63 are spaced apart, and the radiation members 63 are spaced apart from the heat sink 15 by a heat insulating layer (not shown). The array lamp 45 is located between two radiation emitting members 63.
It is understood that the number of the radiation members 63 may be one, three or more; in order to make the radiation uniform at each position in the simulation chamber 10, the arrangement density and the size of the radiation emitting members 63 can be increased. In one embodiment, the lunar-based environmental simulation apparatus 100 further comprises a detector (not shown) for detecting the intensity of the radiation in the first body 11 of the simulation chamber 10, and the controller controls the intensity of the radiation emitted from the radiation emitting member 63 according to the intensity of the radiation detected by the detector. It is understood that the radiation environment simulation system 60 includes at least one of the radiation device 61 and the radiation emitting member 63
According to the lunar environment simulation device 100 provided by the first embodiment of the invention, due to the fact that extreme lunar ground environments such as vacuum, microgravity, extreme temperature difference, high cosmic radiation and tiny dust are simulated, and underground environment factors simulating lunar rocks are considered, the reality of lunar environment simulation is improved, and the accuracy of tests such as walking, detecting and coring of a test object in the lunar environment simulation device 100 is improved.
Second embodiment
Referring to fig. 6 and 7, fig. 6 is a schematic perspective assembly view of a lunar environment simulation apparatus according to a second embodiment of the present invention. Fig. 7 is a sectional view of the moon environment simulator shown in fig. 6. A moon-based environmental simulation device 200 comprises a moon ground simulation system 201 and a lunar rock simulation system 203 which are connected. The lunar surface simulation system 201 is used to simulate a lunar surface environment. The lunar rock simulation system 203 is used to simulate a lunar rock environment to simulate a lunar subsurface environment.
The lunar ground simulation system 201 includes a simulation pod 70, a lunar soil simulation system 80, and a vacuum simulation system 90. The lunar soil simulation system 80 and the vacuum simulation system 90 are both communicated with the simulation chamber 70. The lunar soil simulation system 80 is used to provide a lunar soil simulation environment for the moon to the simulation chamber 70, and the vacuum simulation system 90 is used to evacuate the simulation chamber 70 to simulate the vacuum environment of the moon.
The lunar soil simulation system 80 includes a lunar soil simulant 81, the lunar soil simulant 81 being housed in the simulation chamber 70.
The lunar ground simulation system 201 also includes a rail 89 secured to the surface of the lunar soil simulant 81. The track 89 is used to facilitate the test subject walking or moving other equipment. It is understood that the arrangement position and the arrangement direction of the rails 89 are not limited. It will be appreciated 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 further includes a dust sprayer 82, a charged particle accelerator 83, and an ultraviolet ray generation device 85 fixed to the simulation chamber 70. The dust applicator 82 is secured to the simulation chamber 70 for providing a lunar dust simulant into the simulation chamber 10 for simulating a mote environment on the surface of the moon. The charged particle accelerator 83 is used to generate a proton beam to electrostatically charge the lunar dust simulant. When the test object moves on the lunar soil simulant 81, the surface of the test object can adhere raised simulated lunar dust. The ultraviolet generating device 85 is used for emitting ultraviolet rays into the simulation chamber 70 so as to simulate the photoelectric effect of the lunar dust under the action of the ultraviolet rays. Since the lunar ground simulation system 201 is provided with the dust sprayer 82, the charged particle accelerator 83 and the ultraviolet ray generation device 85, the environment of the tiny dust on the moon is simulated, and the simulation precision of the lunar ground environment is improved.
The lunar rock simulation system 203 is buried within the lunar soil simulant 81. The lunar rock simulation system 203 includes a thermally insulated container 2031 and a lunar rock simulation 2033 housed in the thermally insulated container 2031. The lunar rock simulant 2033 is isolated from the lunar soil simulant 81 by an insulated container 2031. It is understood that the lunar rock simulation system 203 can be two, three, and more.
More specifically, the simulation chamber 70 includes a first chamber 71 and a second chamber 73 in communication with the first chamber 71. The first cabin 71 is provided with a cabin door 711. The hatch 711 is used to open or close the first cabin 71. It is understood that in some embodiments, a viewing window (not shown) may be provided in the hatch 711. The observation window is used for the experimenter to observe and record the experimental condition inside the first cabin 11.
It is understood that the number of the hatches 711 is not limited, and for example, the hatches 711 may be one or more than two.
Further, the door 711 includes a door frame 7111, a connector 7113, and door fans 7115. The cabin door leaf 7115 is slidably connected to the cabin door frame 7111 through a connecting member 7113, so that the cabin door leaf 7115 can slide along the cabin door frame 7111, the first cabin body 71 is conveniently opened or closed, and the test efficiency is improved.
Referring to fig. 8, fig. 8 is a schematic view of the lunar environment simulation apparatus shown in fig. 6 from another perspective. The vacuum simulation system 90 includes an air tank 91, a vacuum pump 92, a lorentz pump 93, an oil diffusion pump 94, and a pipe 95, and the air tank 91, the vacuum pump 92, the lorentz pump 93, and the oil diffusion pump 94 are sequentially communicated through the pipe 95. The vacuum pump 92, the lorentz pump 93 and the oil diffusion pump 95 are used for pumping the simulation chamber 70 to simulate the lunar vacuum environment. It is to be understood that the vacuum simulation system 90 is not limited in structure, and may be configured to evacuate the simulation chamber 70.
Further, the vacuum simulation system 90 further includes a mounting bracket 97, and the vacuum pump 92 and the lorentz pump 93 are disposed on the mounting bracket 97.
Referring to fig. 9 and 10, fig. 9 is a schematic perspective assembly view of the removed portion of the environmental simulator shown in fig. 6. Fig. 10 is a partially enlarged schematic view of the temperature control system of the environmental simulator shown in fig. 6.
In this embodiment, the lunar ground simulation system 201 further includes a temperature adjustment system 130 disposed in the simulation chamber 70 for adjusting the temperature in the simulation chamber 70 to simulate the extreme temperature environment of the moon. It is understood that the temperature of the temperature regulating system 130 at different points in time is controlled by the controller.
Further, the inner wall of the first cabin 71 is coated with a heat sink 75 for simulating a very cold and very black environment of the moon environment. The temperature adjusting system 130 includes a gas helium temperature adjusting system 102 and a liquid nitrogen refrigerating system 104 connected in series with the gas helium temperature adjusting system 102 to adjust and control the temperature of the heat sink 75, so as to adjust the temperature in the simulation chamber 70. In the embodiment, the gas helium provided by the gas helium temperature regulation system 102 further cools the liquid nitrogen provided by the liquid nitrogen refrigeration system 104 to 70K; and controlling the temperature of the heat sink 75 by adopting the gas helium temperature regulating system 102 within the temperature range of 150-400K. It is understood that the temperature in the simulation chamber 70 can be controlled by controlling the gas helium temperature adjustment system 102 and the liquid nitrogen refrigeration system 104 according to actual requirements.
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, wherein 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. The helium generator 1011 is used for generating helium gas, and the compressor 1013 is used for compressing the generated helium gas and storing the compressed helium gas 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, wherein 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 1036 through the gas pipe 1038. The nitrogen generator 1035 is used to produce nitrogen gas, and the compressor 1037 is used to compress and store the produced nitrogen gas in the liquid nitrogen storage device 1036.
The temperature regulating system 130 further includes an array light 105, the array light 105 being housed within the simulation chamber 70 for simulating collimated light of the sun. Because the array lamp 105 is adopted to simulate the solar spectrum, the heat flux and the altitude angle, the simulation accuracy of the moon environment device 100 to the moon environment is further improved. In this embodiment, the array lamp 105 is an infrared lamp array, and can be used as a part of the heat source at the same time to adjust the temperature in the simulation chamber 70.
Referring to fig. 7, 9 and 11 again, fig. 11 is a partially enlarged schematic view of the microgravity simulation system of the lunar environment simulation apparatus shown in fig. 6.
The lunar ground simulation system 201 further includes a microgravity simulation system 110, and the microgravity simulation system 110 is located in the first chamber body 71 of the simulation chamber 70 to provide a pulling force for the test object in the simulation chamber 70, so as to counteract partial earth gravity borne by the test object, and realize the simulation of the microgravity environment of the test object in the moon.
The microgravity simulation system 110 includes a support frame 1101 and a mobile suspension device 1103. A support 1101 is fixed to the inner wall of the first chamber 71 for supporting the mobile suspension device 1103. The movable suspension device 1103 is movably disposed on the supporting frame 1101. Moving suspension 1103 includes first guide 1104, second guide 1105, moving platform 1106, connector 1107, first drive 1108, and second drive 1109. The first guide rail 1104 is fixedly disposed on the support frame 1101, and the first guide rail 1104 extends in a first direction (e.g., Y direction). Second guide 1105 is in sliding engagement with first guide 1104. The second guide track 1105 extends in a second direction (e.g., the X direction). The moving platform 1106 is slidably coupled to the second guide 1105. A connecting member 1107 is suspended from the movable platform 1106 for connecting with the test object to provide tension to the test object. The end of the connecting piece 1107 facing away from the moving platform 1106 is provided with a hook (not shown), and when in use, the traction point of the hook is located at the centroid position of the test object. A first drive 1108 is secured to the first rail 1104 for driving the second rail 1105 along the first rail 1104. A second driving member 1109 is fixed on the second guiding rail 1105 and is used for driving the moving platform 1106 to move along the second guiding rail 1105. The first driving element 1108 and the second driving element 1109 can adjust the position of the moving platform 513 according to the motion track of the test object, so as not to influence the motion of the test object.
The microgravity simulation system 110 utilizes the principle of gravity compensation on a test object, and meets the requirement of complete unrestrained six-degree-of-freedom by combining structures such as a guide rail and a suspension and adding a counterweight, thereby truly simulating the operation of the surface of the moon. It is understood that the microgravity simulation system 110 is not limited to the structure illustrated in this embodiment, and the microgravity simulation system 110 may be other structures or devices, for example, the microgravity simulation system 110 may be a balloon suspension.
Moon environment simulator 200 also includes ray set 121. The ray device 121 is installed in the second chamber 72 of the simulation chamber 70 for emitting rays into the simulation chamber 70 to simulate cosmic rays. In this embodiment, the radiation device 121 is used to emit x and y rays. It is to be understood that the radiation device 121 is not limited to emitting x-and y-rays, for example, the radiation device 121 may emit only one of x-and y-rays or the type thereof.
The lunar environment simulation device 200 provided in the second embodiment of the present invention, because extreme lunar ground environments such as vacuum, microgravity, extreme temperature difference, high cosmic radiation, and tiny dust are simulated, and the simulation of the underground environment of the simulated lunar rock is considered, the reality of lunar environment simulation is improved, and the accuracy of tests such as walking, detecting, coring and the like on the test object in the lunar environment simulation device 200 is improved.
While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention.
Claims (15)
1. The moon-based environment simulation device is characterized by comprising a moon ground simulation system and a lunar rock simulation system which are connected, wherein the moon ground simulation system is used for simulating a moon ground environment, and the lunar rock simulation system is used for simulating a lunar rock environment.
2. The lunar ground simulation device according to claim 1, wherein the lunar ground simulation system comprises a simulation chamber, a lunar soil simulator, an inner cavity of the simulation chamber is in communication with the lunar soil simulator, the lunar soil simulator is used for a test subject to walk, the lunar rock simulation system is connected with the lunar soil simulator, and the vacuum simulation system is in communication with the simulation chamber and is used for vacuumizing the simulation chamber to simulate a lunar vacuum environment.
3. The lunar environment simulation apparatus as defined in claim 2, wherein the simulation pod is fixedly disposed on the lunar soil simulant and the lunar rock simulation system is disposed on a side of the lunar soil simulant facing away from the simulation pod.
4. The lunar environment simulation apparatus as defined in claim 2, wherein the lunar rock simulation system is buried in the lunar soil simulant.
5. The lunar environment simulation apparatus according to any one of claims 2 to 4, wherein the lunar rock simulation system comprises an insulated container and a lunar rock simulator accommodated in the insulated container.
6. The lunar environment simulation apparatus as defined in claim 2, wherein the lunar surface simulation system further comprises a dust sprayer disposed on the simulation chamber, the dust sprayer for providing a lunar dust simulant to the simulation chamber to simulate a micro-dust environment of the moon.
7. The lunar ground simulation apparatus according to claim 6, wherein the lunar ground simulation system further comprises a charged particle accelerator fixed to the simulation pod, the charged particle accelerator for generating a proton beam to electrostatically charge a lunar dust simulant.
8. The lunar ground simulation system according to claim 6, further comprising an ultraviolet ray generating device for emitting ultraviolet rays into the simulation chamber to simulate a photoelectric effect of lunar dust under the effect of the ultraviolet rays.
9. The lunar environment simulation apparatus as defined in claim 2, wherein the lunar ground simulation system further comprises a temperature regulation system disposed on the simulation chamber for regulating a temperature within the simulation chamber to simulate a temperature environment of the moon.
10. The lunar environment simulation apparatus according to claim 9, wherein the temperature regulation system comprises a gas helium attemperation system and a liquid nitrogen refrigeration system arranged in series with the gas helium attemperation system.
11. The lunar environment simulation apparatus as defined in claim 9, wherein said temperature regulation system further comprises an array of lights housed within said simulation chamber for simulating collimated light of the sun.
12. The lunar environment simulation apparatus 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 chamber and is used for providing a pulling force to the test object to simulate the microgravity environment of the test object on the moon.
13. The environmental simulation apparatus according to claim 12, wherein the microgravity simulation system comprises a support frame fixed on an inner wall of the simulation chamber, and a movable suspension device movably disposed on the support frame, the movable suspension device being configured to provide a pulling force to the test object located in the simulation chamber.
14. The environmental simulation apparatus according to claim 13, wherein the movable suspension device comprises a first rail, a second rail, a movable platform, a connecting member, a first driving member and a second driving member, the first rail is fixedly disposed on the supporting frame, the second rail is slidably connected to the first rail, the movable platform is slidably connected to the second rail, and the connecting member is suspended from the movable platform and is used for connecting to the test object.
15. The lunar environment simulation apparatus as defined in claim 2, wherein the lunar ground simulation system further comprises a radiation environment simulation system, the radiation environment simulation system being located within the simulation chamber for simulating a radiation environment to which the moon is subjected, the radiation environment simulation system comprising at least one of a ray device and the radiation emitting member.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910819525.0A CN110539900A (en) | 2019-08-31 | 2019-08-31 | Moon-based environment simulation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910819525.0A CN110539900A (en) | 2019-08-31 | 2019-08-31 | Moon-based environment simulation device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110539900A true CN110539900A (en) | 2019-12-06 |
Family
ID=68711030
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910819525.0A Pending CN110539900A (en) | 2019-08-31 | 2019-08-31 | Moon-based environment simulation device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110539900A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112046799A (en) * | 2020-07-20 | 2020-12-08 | 中国人民解放军63919部队 | Weightlessness-simulated dry-leaching device |
| CN112937930A (en) * | 2021-02-03 | 2021-06-11 | 哈尔滨工业大学 | Vacuum system for simulating lunar large dust distribution environment |
| CN113345309A (en) * | 2021-05-07 | 2021-09-03 | 哈尔滨工业大学 | Lunar dust sprinkling device for lunar multi-factor comprehensive environment simulation |
| CN113391374A (en) * | 2021-05-26 | 2021-09-14 | 哈尔滨工业大学 | Lunar soil water ice pole simulation experiment device and experiment method thereof |
| CN113689752A (en) * | 2021-07-06 | 2021-11-23 | 哈尔滨工业大学 | Moon multi-factor comprehensive environment simulation device |
| CN113920804A (en) * | 2021-09-26 | 2022-01-11 | 哈尔滨工业大学 | Large-scale multi-factor space irradiation environment integrated simulation device and simulation method |
| CN114131924A (en) * | 2021-11-08 | 2022-03-04 | 北京卫星制造厂有限公司 | Low-energy-consumption lunar soil solidification simulation forming device and method suitable for lunar surface environment |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1096431A (en) * | 1963-03-04 | 1967-12-29 | Ass Elect Ind | Improvements relating to devices for simulating radiation from celestial bodies |
| CN102156304A (en) * | 2010-12-30 | 2011-08-17 | 中国航天科技集团公司第五研究院第五一○研究所 | Small-sized comprehensive simulation system of lunar environment |
| CN102564784A (en) * | 2011-12-20 | 2012-07-11 | 北京卫星环境工程研究所 | Ground walking test system of lunar surface inspection device |
| CN104122381A (en) * | 2014-07-08 | 2014-10-29 | 北京航空航天大学 | High and low temperature vacuum lunar soil environment simulator |
| CN211167476U (en) * | 2019-08-31 | 2020-08-04 | 深圳大学 | Moon-based environment simulation device |
-
2019
- 2019-08-31 CN CN201910819525.0A patent/CN110539900A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1096431A (en) * | 1963-03-04 | 1967-12-29 | Ass Elect Ind | Improvements relating to devices for simulating radiation from celestial bodies |
| CN102156304A (en) * | 2010-12-30 | 2011-08-17 | 中国航天科技集团公司第五研究院第五一○研究所 | Small-sized comprehensive simulation system of lunar environment |
| CN102564784A (en) * | 2011-12-20 | 2012-07-11 | 北京卫星环境工程研究所 | Ground walking test system of lunar surface inspection device |
| CN104122381A (en) * | 2014-07-08 | 2014-10-29 | 北京航空航天大学 | High and low temperature vacuum lunar soil environment simulator |
| CN211167476U (en) * | 2019-08-31 | 2020-08-04 | 深圳大学 | Moon-based environment simulation device |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112046799A (en) * | 2020-07-20 | 2020-12-08 | 中国人民解放军63919部队 | Weightlessness-simulated dry-leaching device |
| CN112937930A (en) * | 2021-02-03 | 2021-06-11 | 哈尔滨工业大学 | Vacuum system for simulating lunar large dust distribution environment |
| CN113345309A (en) * | 2021-05-07 | 2021-09-03 | 哈尔滨工业大学 | Lunar dust sprinkling device for lunar multi-factor comprehensive environment simulation |
| CN113345309B (en) * | 2021-05-07 | 2023-01-03 | 哈尔滨工业大学 | Lunar dust sprinkling device for lunar multi-factor comprehensive environment simulation |
| CN113391374A (en) * | 2021-05-26 | 2021-09-14 | 哈尔滨工业大学 | Lunar soil water ice pole simulation experiment device and experiment method thereof |
| CN113689752A (en) * | 2021-07-06 | 2021-11-23 | 哈尔滨工业大学 | Moon multi-factor comprehensive environment simulation device |
| CN113689752B (en) * | 2021-07-06 | 2024-01-19 | 哈尔滨工业大学 | Moon multifactor comprehensive environment simulation device |
| CN113920804A (en) * | 2021-09-26 | 2022-01-11 | 哈尔滨工业大学 | Large-scale multi-factor space irradiation environment integrated simulation device and simulation method |
| CN114131924A (en) * | 2021-11-08 | 2022-03-04 | 北京卫星制造厂有限公司 | Low-energy-consumption lunar soil solidification simulation forming device and method suitable for lunar surface environment |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110539900A (en) | Moon-based environment simulation device | |
| CN211167476U (en) | Moon-based environment simulation device | |
| Yair | New results on planetary lightning | |
| Smith et al. | Ballooning for biologists: mission essentials for flying life science experiments to near space on NASA large scientific balloons | |
| CN113636115B (en) | Solar system multi-factor comprehensive environment simulation device | |
| Gan et al. | Experiments on the electrostatic transport of charged anorthite particles under electron beam irradiation | |
| Gaier et al. | Lunar simulation in the lunar dust adhesion bell jar | |
| WO2021035757A1 (en) | Moon-based environment simulation device | |
| Sullivan | Catalog of Apollo experiment operations | |
| Clarke | Auroral processes on Jupiter and Saturn | |
| Duke et al. | Lunar surface reference missions: A description of human and robotic surface activities | |
| Thangavelautham et al. | An on-orbit CubeSat centrifuge for asteroid science and exploration | |
| LIU et al. | Ionospheric investigations conducted by Chinese mainland scientists in 2020–2021 | |
| Adams et al. | Asteroid in situ exploration using planetary object geophysical observer (POGO) | |
| Müller-Wodarg et al. | The thermosphere of Venus and its exploration by a Venus Express Accelerometer Experiment | |
| Mari et al. | Potential futures in human habitation of martian lava tubes | |
| Formisano et al. | Pfs: the planetary fourier spectrometer for mars express | |
| Quadrelli et al. | E-Glider: Active Electrostatic Flight for Airless Body Exploration | |
| Manoharan et al. | Regular solar radio imaging at arecibo: space weather perspective of evolution of active regions | |
| Lara et al. | Our Future? Space Colonization and Exploration | |
| Johnson et al. | Effects of the lunar environment on optical telescopes and instruments | |
| Johnson et al. | Required technologies for lunar astronomical observatories | |
| Duke et al. | Scientific investigations at a lunar base | |
| GAO et al. | Space research plan of China’s Space Station | |
| Hibbs | The Exploration of the Moon, the Planets, and Interplanetary Space |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |