102 results about "Planet Mars" patented technology

The invention discloses a Mars transverse wind ridging few-sample remote sensing interpretation method and system based on an SAM model. According to the method, contrast stretching preprocessing is carried out on an original Mars image, a dual-branch feature fusion framework based on VIT and CNN is constructed to extract and fuse image features, a position coding generator is introduced to support input of any size, a fine-tuning SAM strategy of a selective freezing encoder and a trainable mask decoder is adopted, and LoRA low-rank adaptation optimization calculation is combined, so that the Mars image is obtained. And a double-branch prompt generation module is used for fusing labeled and unlabeled data to generate a high-precision prompt, and finally, an interpretation result is output through a mask decoder and connected component analysis is carried out, so that instance-level labeling is realized. The system comprises an image preprocessing module, a double-branch feature extraction and fusion module, an image embedding generation module, a model fine tuning module, a prompt embedding generation module and an interpretation module. According to the method, the recognition precision and robustness of the mars transverse wind ridge formation under the condition of few samples are effectively improved.

The invention relates to a method for verifying a Mars sky radiance simulation result based on a Mars real-shot photo, and belongs to the technical field of Mars sky background radiance. Comprises: image acquisition; performing radiation calibration; correcting dark current; performing flat field correction; converting a radiation value; and geometric correction. The Mars sky radiance simulation method breaks through the dependence of an existing model on idealized hypothesis, performs dynamic verification by using actual shot image data, remarkably improves the authenticity and reliability of a Mars sky radiance simulation result, and effectively solves the problem of systematic deviation under a specific wave band; by constructing a complete process from image acquisition, radiation calibration, geometric modeling to brightness inversion and comparison verification, dynamic feedback and closed-loop correction of a theoretical radiation model are realized, model adaptability is improved, and fine modeling under multi-temporal and multi-meteorological conditions is supported; the method can be applied to an existing Mars rover navigation camera and an image processing link of the Mars rover navigation camera, does not need additional modification, has good engineering practicability and task compatibility, and is convenient to popularize and apply.

The application relates to a deformable wheel with non-pneumatic load bearing intended to equip a vehicle for rolling under extreme conditions such as those encountered on the Moon and on Mars, comprising a hub, an annular tread intended to be in contact with the soil, positioned around the hub which is concentric therewith and comprising a layer of composite material coated with at least one protective layer, and a plurality of metal cables whose outer diameter is comprised between 0.2 mm and 5 mm, each cable connecting the hub to the tread while being fixed, on the one hand by an external end to the tread, and on the other hand by an internal end to the hub by an elastic member making it possible to modulate the radial stiffness of the cables, each elastic member being associated with an abutment able to limit its deformation.

The embodiment of the invention discloses an automatic rock extraction method and system based on deep learning and Mars rover camera images, and aims to solve the problems that an existing Mars rock segmentation algorithm is insufficient in generalization ability under a complex earth surface background, high in model calculation load and difficult to deploy on satellite-borne edge equipment. The core of the method is that a lightweight encoder-decoder network is constructed, and the network integrates three key modules: a frequency-assisted enhancement Mama module, which accurately captures rock texture and contour by fusing the global sequence modeling capability of Mama and the frequency domain enhancement of wavelet transform; the multi-scale feature intensifier is used for adaptively fusing multi-level features by using a parallel double attention mechanism; and the boundary perception auxiliary branch improves the integrity of the segmented contour through an explicit edge supervision and feature decoupling mechanism. According to the method, the rock extraction precision is remarkably improved, meanwhile, the model complexity and the calculation overhead are greatly reduced, the method is suitable for outer space exploration scenes with limited communication bandwidth and calculation resources such as Mars rovers, and effective balance of high precision and light weight is achieved.

The invention belongs to the technical field of data processing, and discloses a Mars probe temperature monitoring method and system based on time control factor optimization, and the method comprises the steps: obtaining simulated fire soil, and carrying out the screening processing and dense state preparation processing, and obtaining a plurality of relatively dense state samples; performing simulated temperature monitoring on the plurality of samples in the relatively dense state to obtain a plurality of temperature-time curves, and performing piecewise linear fitting to obtain thermal response characteristics of the simulated fire soil; performing optimal monitoring time period analysis and optimal monitoring duration analysis according to the thermal response characteristics to obtain an optimal passive monitoring time window and duration strategy; and determining target to-be-monitored fire soil, and performing real temperature monitoring on the target to-be-monitored fire soil according to the optimal passive monitoring time window and the duration strategy to obtain an optimal temperature monitoring result. According to the invention, the temperature of the fire soil to be measured can be accurately monitored, so that the assessment precision of the passing ability of the Mars rover is effectively improved, and the driving safety of the Mars rover is ensured.

A deformable wheel with non-pneumatic load bearing intended to equip a vehicle for rolling under extreme conditions such as those encountered on the moon and on Mars, includes a hub, a laminated annular strip including a plurality of concentric ferrules which are assembled with the interposition of interposing layers each composed of a material whose Young's modulus is 600,000 to 1,000 times lower than that of the ferrules, and a plurality of metal cables. Each cable connects the hub to the laminated strip while being fixed, on the one hand by an external end to the laminated strip, and on the other hand by an internal end to the hub by means of an elastic member making it possible to modulate the radial stiffness of the cables. Each elastic member is associated with an abutment able to limit its deformation.

The invention relates to the technical field of planet remote sensing data processing and three-dimensional reconstruction, and discloses a Mars three-dimensional terrain reconstruction method based on feature enhancement and multi-view stereo matching, which comprises the following steps: firstly, obtaining and preprocessing Mars stereo image data; secondly, extracting texture features based on a gray-level co-occurrence matrix, and performing region segmentation by using local entropy to distinguish a high texture region from a low texture region; then, parameters such as the size of a matching block and a similarity threshold value are adaptively adjusted according to a segmentation result, and a multi-dimensional mixed feature descriptor is generated to perform homonymy point matching; a coupling threshold model of the solar incident angle and the terrain roughness is constructed, and parallax calculation of the shadow and the steep terrain is optimized; and finally, combining cross-scale parallax propagation and global bundle adjustment to reconstruct a three-dimensional terrain model. According to the method, the technical problems that the matching reliability of areas such as weak textures and shadows on the surface of Mars is insufficient and the model is discontinuous are solved, and the integrity, the self-adaptability and the global precision of the reconstruction model are improved.

The application relates to a Mars spacecraft temperature control system and method, and relates to a temperature control system and method. In order to solve the problem that an existing Mars spacecraft temperature control system cannot guarantee accurate planning and flexible operation of the Mars spacecraft under the condition of limited energy budget, cannot maximize temperature control energy, and cannot meet the corresponding allowable temperature limit of different temperature control modes in a variable temperature control scene, the temperature control system comprises a base station subsystem, a spacecraft subsystem and an operating environment system; the base station subsystem is composed of a first temperature measurement module, a first temperature adjustment module and a base station control module; and the spacecraft subsystem is composed of a second temperature control module, a second temperature adjustment module and a spacecraft control module. The application belongs to the technical field of spacecraft thermal management.

The application provides a device and a method for in-situ preparation of methane propellant applied to a Mars surface. The device for in-situ preparation of methane propellant comprises a gas distribution system, a reaction gas pretreatment system, a Sabatier reaction system and a product collection system. The gas distribution system is used for conveying carbon dioxide and hydrogen gas prepared on the Mars surface to the reaction gas pretreatment system after pretreatment; the reaction gas pretreatment system is used for mixing and heating the carbon dioxide and the hydrogen gas to form preheated mixed reaction gas and conveying the preheated mixed reaction gas to the Sabatier reaction system; the Sabatier reaction system is used for generating methane and water through a Sabatier reaction of the preheated mixed reaction gas, and the Sabatier reaction system comprises a Sabatier reactor and a circulating air assembly for stabilizing a temperature field in the Sabatier reactor; and the product collection system is used for separating and collecting the methane and the water generated through the Sabatier reaction. The Sabatier reactor is equipped with the circulating air assembly for stabilizing the temperature field in the Sabatier reactor, so that the Sabatier reactor has a stable temperature field and a flow field under different reaction gas flow rates.

The invention relates to a deformable wheel (2) with non-pneumatic load bearing intended to equip a vehicle for driving under extreme conditions, such as those encountered on the moon and Mars, comprising: a hub (4), an annular tread (6) intended to come into contact with the soil, and a plurality of metal cables (8), the invention relates to a pneumatic tire comprising a hub (4), an annular tread arranged around the hub concentric therewith and comprising a layer of composite material coated with at least one protective layer, a plurality of metal cables having an outer diameter of between 0.2 mm and 5 mm, each cable connecting the hub (4) to the tread, each cable being fixed to the tread by an outer end (8a), and each cable being fixed to the tread by an outer end (8b). On the other hand, the cable is fixed to the hub by means of an inner end (8b) by means of an elastic member (18) capable of adjusting the radial stiffness of the cables, each elastic member being associated with a stop surface (12, 14) capable of limiting its deformation.

The application provides a hybrid control method for a six-bar tensegrity robot for Mars surface exploration, which firstly models the six-bar tensegrity robot used, defines the coordinates and adjacency relationship of each face, and pre-establishes an energy landscape graph. Then in the process of controlling the six-bar tensegrity robot, the environment data is synchronously collected, and the rolling or jumping mode is switched according to the robot state and the environment data. In the rolling mode, the A algorithm is used to search for an energy-optimal face conversion sequence, and based on the adaptive thrust of the quadratic programming, the optimal motor thrust distribution is obtained by solving a constrained optimization problem for each face conversion in the face conversion sequence. In the jumping mode, a safe margin height is reserved, the size and angle of the motor thrust are adjusted to overcome the Mars gravity, and the terrain adaptability of the six-bar tensegrity robot is improved. The combination of the two solves the problems of low marching efficiency, high energy loss and weak maneuverability of the prior art on the complex surface of Mars.

The application provides a Mars crater detection method and system, relates to the technical field of planetary remote sensing image processing and target detection, and comprises the following steps: constructing a CAFE-Net network based on a YOLO single-stage detection model, integrating a multi-scale context perception module, a feature enhancement unit and an efficient feature fusion network, training the model after pre-processing MDCD and DACD data sets, and outputting visualized and structured detection results through model inference and non-maximum suppression post-processing, so that the problems of high false detection rate of craters and dome structures and high missing detection rate of small craters in the prior art are effectively solved, the precision and recall rate are improved, the method is suitable for deep space exploration scenes such as Mars probe landing site selection and Mars geological age determination, and can be automatically processed in an end-to-end mode and is convenient to deploy.

The invention provides a ventilation wall test system and method for Mars aircraft testing, and the system comprises a space environment simulator which can simulate the low-pressure and low-temperature environment of Mars, a gravity unloading device which is installed in the space environment simulator, a ventilation wall assembly which is used for generating a controllable simulation wind field, and a ventilation wall driving device. The wind wall assembly is arranged in a wind guide structure of the space environment simulator and comprises a plurality of fan array units, each fan array unit is of a multi-layer series connection structure, the distance between the adjacent fan array units can be adjusted according to the wind speed of the controllable simulation wind field, and each fan array unit comprises a plurality of fans arranged at non-equal intervals. The Mars transient wind field where the to-be-tested unmanned aerial vehicle is located is accurately simulated, and accurate simulation of distribution of the Mars wind field in time and space and low gravity of the Mars is achieved.

The present application belongs to the technical field of Mars radar vehicle data processing, and particularly relates to a double-scale data fusion imaging method for Mars radar vehicle data, which fuses RIMFAX and RoPeR double-source data to realize collaborative imaging of shallow precision and deep thickness in a depth range of more than 100 meters. Through grid alignment and Gaussian weight transition, stitching artifacts are eliminated, and the processing efficiency and imaging quality are significantly improved. The present application can overcome the defects in the existing Mars radar data processing, such as the single load being unable to consider the detection depth and resolution, and the double-source heterogeneous data being difficult to realize collaborative imaging, and provides a double-scale data fusion imaging method. Through differential filtering, unified grid registration and depth domain weighted fusion of RIMFAX shallow high-resolution data and RoPeR deep large-penetration data, integrated imaging of Mars shallow structure from shallow fine to deep profile is realized.

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

The invention relates to particular formulations combining a biodegradable matrix and a regolith filler usable in 3D printing, in particular for the manufacture of objects during extraterrestrial missions, for example on the moon or on Mars.

The invention discloses a Mars surface nuclear energy utilization system for comprehensive thermoelectric hydrogen storage and production, and relates to a Mars surface nuclear energy utilization system. The invention aims to solve the problem that the Mars base needs an efficient and reliable energy system. The system comprises a Brayton thermoelectric conversion device, one side of the Brayton thermoelectric conversion device is connected with a high-temperature electrolytic hydrogen production device, the other side of the Brayton thermoelectric conversion device is connected with a laser wireless energy transmission device, and the Brayton thermoelectric conversion device is further connected with a heat supply device and a Carnot battery energy storage device; the heat supply device provides heat for the Mars base, and the Brayton thermoelectric conversion device provides power for power utilization facilities, the high-temperature electrolytic hydrogen production device and the laser wireless capacity transmission device of the Mars base. The invention belongs to the technical field of nuclear energy comprehensive utilization.

This invention proposes a method and system for classifying Martian impact crater degradation based on a comprehensive analysis of morphology and erosion characteristics, relating to the fields of planetary remote sensing and planetary geomorphology. The method includes acquiring high-resolution Martian remote sensing images, using a three-point circle method to outline impact craters, identifying impact craters in the study area, excluding secondary impact craters in the study area, and selecting ten descriptive factors to describe the impact craters in the study area: impact ejecta, crater rim gap, crater rim sharpness, crater rim damage degree, crater bottom filling material, sand ripple area ratio, crater bottom elevation variation coefficient, depth-to-diameter ratio, crater rim roughness, and abundance of superimposed impact craters. Based on these ten descriptive factors, the method analyzes the grading criteria for impact crater degradation, classifying the Martian impact crater degradation process into seven degradation levels. This invention classifies the degree of impact crater degradation solely based on morphological characteristics, eliminating the need for extensive and complex calculations and remaining unaffected by the heterogeneity of the pre-impact terrain and the irregularity of the impact crater morphology.

The invention discloses a Mars atmosphere braking energy control set prediction correction guidance method in an uncertain environment, and belongs to the technical field of deep space exploration. The implementation method of the invention comprises the following steps: respectively establishing a dynamic model of an atmospheric braking process detector flying outside the atmosphere and a dynamic model of an atmospheric braking process detector flying inside the atmosphere; the influence of environmental parameter uncertainty on a detector reachable set is considered, a reachable set under the influence of different parameter uncertainty is calculated, and a reachable union set is solved. And solving a corresponding near fire point heat flux density set according to the reachable union set, and judging whether the far fire point needs maneuvering or not according to the relationship between the near fire point heat flux density set and the atmospheric braking corridor. The influence of environmental parameter uncertainty on a detector energy control set is considered, an energy control set under the influence of different parameter uncertainty is calculated, and an energy control intersection is solved. And solving a set of far fire point speed increments used for correcting a near fire point state by the energy control intersection, and realizing Mars atmospheric braking energy control set prediction correction guidance in an uncertain environment according to the selected far fire point maneuvering speed increment.

The application belongs to the technical field of data processing, and discloses a Mars probe temperature monitoring method and system based on time control factor optimization, which comprises the following steps: obtaining simulated soil, and performing screening treatment and dense state preparation treatment to obtain a plurality of relatively dense state samples; performing simulated temperature monitoring on the plurality of relatively dense state samples to obtain a plurality of temperature-time curves, and performing piecewise linear fitting to obtain the thermal response characteristics of the simulated soil; performing optimal monitoring time period analysis and optimal monitoring time length analysis according to the thermal response characteristics to obtain an optimal passive monitoring time window and time length strategy; determining a target to-be-measured soil, and performing real temperature monitoring on the target to-be-measured soil according to the optimal passive monitoring time window and time length strategy to obtain the best temperature monitoring result. The application can realize accurate monitoring of the temperature of the to-be-measured soil, thereby effectively improving the evaluation accuracy of the passability of the Mars rover and ensuring the driving safety of the Mars rover.

The utility model belongs to the technical field of teaching aids, and particularly relates to an assembled four-star instrument teaching aid, which comprises a detachable and assembled part assembly, and the part assembly comprises a cross-shaped buckle, a civil star disc, a Mars disc, a pointer disc, a golden star disc and a four-star instrument disc. The civil star disc is the largest disc body, the Mars disc, the pointer disc, the golden star disc and the four-star instrument disc are sequentially stacked on the civil star disc from bottom to top, and the centers of the disc bodies are fixedly connected through the cross-shaped buckles. The disc bodies are provided with scale marks, the scale marks comprise year scales, date scales and direction indication scales, and the scale marks are used for achieving the dynamic position prediction function of golden stars, Mars stars, wood stars and earth stars through scale matching between the disc bodies. And the teaching efficiency is improved, and practicability and interestingness are both considered.

The present application relates to a kind of preparation methods for different characteristic Mars weathered layer simulation object, comprising: obtaining the chemical element information of real Mars weathered layer, selecting the brown red volcanic rock with approximate chemical characteristics as raw material and drying;The dry raw material is pulverized, classified and screened, and a plurality of particle size components are obtained;Design different types of target particle size grading, to simulate the typical mechanical properties of different regions on the surface of Mars, each grading can be used as dry state regolith sample.Add water or salt solution to dry state regolith sample, and form frozen sample by low temperature, to simulate high latitude or shallow ice frozen environment on Mars.In addition, secondary mineral powder can also be added to simulate the surface environment of Mars after acidification or salinization weathering, to realize more complex chemical characteristics demand.The present application is simple in process, suitable for mass production, and the simulation object and Mars weathered layer have good correspondence in chemical composition, physical and mechanical properties, and simulation regolith can be produced to cope with various working conditions.

The present application relates to a Mars surface sample collector and method based on differential bevel gears and rope driving, and belongs to the technical field of Mars sampling and returning. It comprises a connecting bracket for installing a driving assembly, the output end of the driving assembly being connected with a differential motion assembly for driving the differential motion assembly, the differential motion assembly driving a rope-driven grabbing assembly to act, and the rope-driven grabbing assembly being used for grabbing and releasing samples. The present application designs a Mars surface sample collector based on differential bevel gears and flexible rope driving, which can realize the actions of sampling point adjustment, jaw clamping and arm recovery fixation under the driving of three motors, reduces the number of driving motors while ensuring the adaptability of the sampling device to the position error of the docking point, simplifies the action of sample collection, improves the reliability of sample collection of the sampling device in the autonomous running state, and reduces the launch mass of the equipment.

The application discloses a kind of multi-sky-oriented space environment data three-dimensional coordinate adaptive conversion and rendering method and system, it is related to space environment data visualization technical field.The application establishes the scene radius and real radius of each sky by establishing sky parameter registry, proposes double radius parameter adaptive coordinate conversion formula, so that the same set of conversion logic adapts to earth, moon, Mars and other arbitrary sky.Using three-dimensional scene graph parent-child level mechanism, particle system is mounted as sky grid subnode, and data points automatically follow sky movement.The application proposes a dynamic near clipping plane adaptive algorithm based on sight distance, and solves the problem of small sky invisibility through double camera synchronous setting strategy.Independent instantiation of multi-sky particle system and on-demand switching in single frame are realized.The application solves the technical problems of coordinate conversion and sky coupling, height mapping distortion and small sky invisibility in the prior art, and is suitable for three-dimensional visualization of multi-sky space environment model results.

The invention belongs to the technical field of Mars unmanned aerial vehicles, and particularly relates to a dynamic unlocking mechanism for multiple Mars aerial vehicles. The mechanism is composed of a horizontal telescopic assembly, a bottom plate, a frame, a vertical lifting assembly and a lower support. The horizontal telescopic assembly is used for carrying an aircraft and can extend outwards through linear movement of a second-stage propelling plate and a third-stage carrying platform to push the aircraft outwards, and unlocking and locking of the third-stage carrying platform are achieved at the beginning and the end of extension through an electric push rod. The horizontal telescopic assembly stretches out and draws back through a driven pull rope, and the pull rope is driven by a wire wheel and a servo motor. A lead screw of the vertical lifting assembly is driven by a servo motor, the frame and the bottom plate move relatively through the rotating lead screw, and the horizontal telescopic assembly which is not stretched is located in the frame. The horizontal telescopic assembly and the vertical lifting assembly are installed on the bottom plate and the lower support. According to the mechanism, rapid and efficient fire surface detection operation without taking-off site requirements can be realized, and the large-scale detection efficiency of the fire surface is remarkably improved.

The invention discloses a Mars entering section trajectory tracking self-adaptive guidance method and a Mars entering section trajectory tracking self-adaptive guidance system. The method comprises the steps that a current state vector entering an aircraft and a pre-stored reference trajectory are obtained, and the current state vector at least comprises the position, the speed, the flight path angle and the course angle; calculating a longitudinal height error state variable based on the current state vector and the reference trajectory, the longitudinal height error state variable comprising a height error and a height error change rate; and based on the height error state variable, constructing a terminal sliding mode surface, and based on the terminal sliding mode surface and the current state vector, generating a first guidance instruction for controlling the cosine of the heeling angle of the entering aircraft, so that the state of the entering aircraft converges to the reference trajectory within finite time. The method solves the technical problem that the Mars probe is inaccurate in guidance under the uncertain conditions of atmospheric density, lift-drag ratio and the like.

The application provides a method for in-orbit calibration and reflectivity determination of a Mars in-situ exploration spectrum. The method comprises the following steps: under the same detection condition, a first calibration plate and a second calibration plate carried by a short-wave infrared spectrometer in a Mars surface component detector are used to obtain a first remote sensing image pixel brightness value corresponding to the first calibration plate and a second remote sensing image pixel brightness value corresponding to the second calibration plate; a regression analysis method is used to determine the in-orbit radiation calibration coefficient ratio of each wave band according to the first remote sensing image pixel brightness value and the second remote sensing image pixel brightness value; for a target detection object, the short-wave infrared spectrometer in the Mars surface component detector is used to obtain a third remote sensing image pixel brightness value corresponding to the target detection object; and the target reflectivity is determined according to the in-orbit radiation calibration coefficient ratio and the third remote sensing image pixel brightness value.

This invention discloses a method for predicting the high-Mach aerodynamic characteristics of a Mars orbiter based on FLUENT, belonging to the aerospace field. This invention establishes a symmetrical geometric model of the Mars orbiter and uses a dual-temperature model based on FLUENT to achieve numerical simulation of the Mars orbiter under high-Mach conditions in CO2 medium. By setting a boundary layer based on O-Block mesh coupling, it achieves unified simulation prediction for different velocities and angles of attack, reducing the computational burden of re-partitioning the mesh for different conditions, thereby improving the efficiency of aerodynamic characteristic prediction. Simultaneously, it can accurately simulate and analyze the aerodynamic characteristics of the Mars orbiter under different conditions, enabling the corresponding aerodynamic performance evaluation of the Mars orbiter. This invention can analyze and construct the hypersonic aerodynamic characteristics of the Mars orbiter under different high-Mach conditions upon entering the Martian atmosphere, assisting in the optimization of the Mars orbiter and guidance and control commands.

This invention relates to a mass-optimized geogrid system and method for stabilizing regolith and other granular soils in extraterrestrial and extreme Earth environments. Mass reduction is achieved both locally—within individual geogrid layers through optimization of lattice geometry, variable mesh density, and reinforcement at stress concentrations—and globally, by varying the spacing and distribution of layers according to structural demands. The geogrid may be fabricated from materials that are locally sourced or compositionally traceable to in-situ resource utilization (ISRU) processes in environments such as the Moon, Mars, or terrestrial polar and desert regions where conventional construction materials are limited or costly to transport. The method includes restructuring the regolith by size-sorting and compaction to produce a particle-size distribution proportionally matched to the mesh openings, enhancing mechanical interlock and shear resistance. Structural efficiency can be tuned and verified through physical testing and finite-element analysis for scalable, repeatable construction.

This disclosure discloses a simulation system for rock weathering in an extreme environment of Mars. The simulation system for rock weathering in an extreme environment of Mars includes a vacuum chamber, a storage structure, a temperature simulation unit, a gas circulation simulation unit, a wind speed simulation unit, and an illumination simulation unit. This disclosure further discloses a simulation test method for rock weathering in an extreme environment of Mars. Compared with the prior art, the simulation system for rock weathering in an extreme environment of Mars prepared by this disclosure can synchronously simulate extreme environments such as a vacuum environment, an atmospheric environment, a temperature environment, an illumination environment, and a sand and dust environment on a surface of Mars, monitors changes such as mass, porosity, and surface deformation of the sample in the weathering process in the extreme environment of Mars of the simulation system.