214 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 invention provides a Mars mineral abundance inversion method and system. The Mars mineral abundance inversion method comprises the steps of firstly obtaining target Mars hyperspectral reflectivity data; and then generating simulated Mars hyperspectral image data based on the target Mars hyperspectral reflectivity data. Secondly, training the constructed mineral abundance inversion deep learning model based on the simulated Mars hyperspectral image data, and determining the trained mineral abundance inversion deep learning model; thirdly, acquiring to-be-processed Mars hyperspectral image data, and performing preprocessing; and finally, performing mineral abundance inversion on the preprocessed to-be-processed Mars hyperspectral image data through the trained mineral abundance inversion deep learning model to obtain a mineral abundance inversion result. Therefore, the weight distribution of each wave band of the hyperspectral image can be enhanced through the mineral abundance inversion deep learning model, and the non-linear modeling capability and the wave band characteristic response capability of abundance inversion are improved, so that the accuracy and the efficiency of Mars mineral abundance inversion can be effectively improved.

The invention discloses a cross-scale planet impact crater detection method and system, and belongs to the technical field of remote sensing image intelligent identification. The method comprises the following steps: collecting and preprocessing a planet surface remote sensing image, and constructing an impact crater detection data set; a Transform-based detection model is constructed, the model comprises a multi-scale attention gating fusion feature extraction backbone module, a small target feature enhancement pyramid module and a target detection module, and the detection capability of the small-size impact crater is improved through multi-scale feature fusion and detail enhancement; pre-training the model by using the universal target detection data, and performing fine tuning optimization on the impact crater data; and finally deploying the model to an edge computing device or a remote sensing terminal to realize real-time detection. The method solves the problem of insufficient precision in cross-scale and weak texture impact crater detection of a traditional method, has the advantages of end-to-end and no need of post-processing, and is suitable for automatic image analysis of planet surfaces such as the moon and the Mars.

The invention relates to a Mars mineral identification method and device, electronic equipment and a storage medium. The method comprises the following steps: acquiring a Mars surface image in a preset wavelength range; acquiring a plurality of mineral pattern spots of the Mars surface image in a pixel-by-pixel manner; extracting deep spatial spectral features of different mineral pattern spots through a pre-trained multi-scale adaptive convolutional neural network; and classifying minerals contained in the Mars surface image according to the deep spatial spectral features of all mineral pattern spots to obtain a classification result. According to the method, the Mars surface image is obtained by combining near-infrared hyperspectral imaging, deep spatial spectral features of different mineral pattern spots are extracted based on the pre-trained multi-scale adaptive convolutional neural network, and rapid, lossless and accurate identification of Mars minerals can be realized.

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 invention discloses a hydrous mineral detection method and system based on the hyperspectrum of a Mars orbiter, and relates to the technical field of hyperspectral data processing and analys.The method comprises the steps that a distribution area of hydrous minerals is obtained based on Mars hyperspectral data; performing automatic end member extraction on the distribution area to obtain an image end member; and performing spectral feature inspection on the image end members, and performing unmixing based on an image end member library to obtain a hydrous mineral abundance map. According to the method, the characteristics of the water-containing minerals can be automatically identified, the mineral distribution range can be accurately positioned, meanwhile, the de-mixing end member library can be automatically constructed, the end members can be checked, and manual participation is reduced; the end member library is automatically constructed from the image based on the qualitative recognition result, and through overlay analysis and comparison with other unmixing end member construction methods, it is shown that the method has high credibility in the aspect of reflecting the distribution of the hydrous minerals and the abundance of the minerals.

The invention relates to a Mars mineral spectrum identification method and device based on deep learning. According to the Mars mineral spectrum recognition method based on deep learning, through four-dimensional constraints of standard deviation, spectral length, absorption depth and overall reflectivity, a background spectrum in an image is adaptively recognized, a ratio spectrum is calculated by taking a dynamic background spectrum as a reference, and interference of non-target factors such as atmospheric scattering and instrument noise can be effectively eliminated. The end member spectrum is directly extracted from the hyperspectral image, and the second ratio spectrum is combined with the preset standard spectrum library to construct the mixed spectrum library containing the Mars specific minerals, so that the data insufficiency of the preset standard spectrum library is made up, and the problem of poor regional adaptability caused by directly adopting the preset standard spectrum library is also avoided; that is, direct use of the earth spectrum library may not accurately reflect the Mars surface features, so that the adaptability of the model to the Mars surface is improved, and it is ensured that the model has higher recognition accuracy in a specific environment of Mars.

The invention provides a deep space exploration simulation test system and method.The deep space exploration simulation test system comprises a thermal interface structure, a cryogenic subsystem and a heating structure, the cryogenic subsystem can refrigerate and cool the thermal interface structure, and the heating structure can heat the thermal interface structure; the deep cooling subsystem comprises a low-temperature refrigeration assembly and a gas cooling assembly, the low-temperature refrigeration assembly transmits cold energy to the thermal interface structure in a one-way mode, and the gas cooling assembly cools the thermal interface structure through cooling gas. The continuous temperature regulation in the range of 300K to 423K is realized through the combination of air cooling and electric heating, and the continuous temperature regulation in the range of 38K to 300K is realized through the combination of a G-M low-temperature refrigerator and electric heating; compared with the existing space environment simulation equipment, the temperature zone can be expanded to 38K to 423K, and the extreme temperature zone environment required by deep space exploration including the lunar surface polar zone and the Mars can be completed; meanwhile, the integrated heat exchange cryogenic subsystem based on heat conduction and convection is compact in structure, liquid nitrogen and liquid helium do not need to be used, and energy conservation and environmental protection are achieved.

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 provides an energy supply system based on Mars in-situ resources, which is suitable for supplying energy to a Mars base and comprises an energy conversion unit and a Mars atmosphere trapping unit. The energy conversion unit comprises a carrier gas device suitable for containing the Mars atmosphere and being heated by an external heat source; and the heat energy conversion device is connected with the gas carrying device and is suitable for converting at least part of heat energy of the Mars atmosphere into mechanical energy and / or electric energy and outputting the Mars atmosphere at the first temperature. And the Mars atmosphere trapping unit is communicated with the energy conversion unit and is suitable for trapping the Mars atmosphere on the Mars in situ and supplementing the Mars atmosphere to the energy conversion unit.

The invention relates to the technical field of deep space exploration visual three-dimensional terrain reconstruction error analysis, in particular to a visual three-dimensional terrain reconstruction error modeling method and system for a Mars patroller. In view of the limitation of the Mars surface environment and the existing error analysis method, the purpose of improving the three-dimensional reconstruction precision is achieved. Technically, the method comprises the following steps: sparsely reconstructing a covariance propagation model based on bundle adjustment, processing a camera imaging equation, carrying out re-projection error calculation and optimization, carrying out nonlinear least square algorithm iterative solution and the like to obtain a camera attitude, a three-dimensional point position parameter and a covariance matrix of the three-dimensional point position parameter; densely reconstructing a covariance propagation model based on linear triangularization, and calculating a three-dimensional point coordinate covariance matrix through equation conversion, least square solution and covariance propagation formula derivation. The experiment simulates the Mars environment to obtain simulation data for dense reconstruction error analysis, and the result shows that the method can effectively analyze errors, significantly improve the three-dimensional terrain reconstruction precision, and powerfully guarantee Mars detection and navigation tasks.

The invention belongs to the related technical field of large models, and discloses a construction method and application of a Mars geology large model based on multi-source data fusion, and the method comprises the steps: (1) carrying out the time alignment of various types of Mars geology heterogeneous data through employing a sliding window and an interpolation method, meanwhile, performing spatial alignment on various types of Mars geological heterogeneous data by adopting GIS spatial registration and feature point matching; performing vectorization conversion on the aligned data in time and space; (2) identifying the data entities subjected to quantitative conversion, extracting a relationship between the data entities to generate a triple, storing the triple in a database, and then constructing a Mars geological knowledge map based on the database; and (3) taking the Mars geological knowledge map as structured background information, and constructing a large-scale machine learning model based on vectorized conversion data. According to the invention, the alignment accuracy and efficiency are improved.

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 invention discloses a vehicle detection path planning and interaction method and system based on the universe and application of the vehicle detection path planning and interaction method and system in Mars rover detection. The method comprises the following steps: constructing collaborative interaction: realizing voice, video and data transmission based on a WebRTC protocol, classifying gesture actions of a user by adopting a support vector machine algorithm, and mapping a classification result into a vehicle movement, data acquisition or path modification operation instruction in a meta-universe environment; a machine learning method is used for extracting geological data features, a terrain detection target is combined, a vehicle terrain detection path plan is generated and projected to the meta-universe environment in real time, and a user shares and visualizes data in the meta-universe environment through a collaborative interaction module and checks and modifies the path plan; and after the user confirms that the path planning is correct, the final optimized path planning and related operation instructions are fed back to the vehicle to guide the vehicle to execute the terrain detection task, so that the efficiency and scientificity of terrain detection 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 present invention discloses a low-pressure temperature control experimental cabin for Mars environment simulation test and an experimental method, which relates to the technical field of ground simulation equipment for Mars environment and solves the problem of insufficient comprehensive simulation ability of ground simulation equipment for Mars environment, especially in terms of temperature. The experimental cabin of the present invention has an inner and outer double-layer cavity. The upper cover of the experimental cabin is provided with a refrigeration expander and a vacuum baffle valve connected to the inner cavity; the vacuum baffle valve connected to the inner cavity is communicated with the inner cavity body, and the refrigeration expander is connected to the inner cavity body; an outer cavity connection vacuum baffle valve and an outer cavity air intake channel provided on the outer cavity are communicated with the outer cavity, and an inner cavity air intake channel on the outer cavity is communicated with the inner cavity body; a condenser and a heater are provided on the inner cavity body, and a copper cold screen is arranged inside. The refrigeration expander, the condenser and the copper cold screen are connected in sequence. The present invention can fully simulate the surface temperature, gas environment and pressure environment of Mars, make up for the deficiencies of ground simulation experimental devices for Mars environment, and provide equipment support for fields such as aerospace and Mars exploration.

The present invention relates to a method and device for identifying Martian mineral spectra based on deep learning. The Martian mineral spectra identification method based on deep learning uses four-dimensional constraints, namely, standard deviation, spectrum length, absorption depth, and overall reflectivity, to adaptively identify background spectra in images, and calculate ratio spectra based on dynamic background spectra, effectively eliminating interference from non-target factors such as atmospheric scattering and instrument noise. By directly extracting endmember spectra from hyperspectral images and combining the second ratio spectrum with a preset standard spectrum library, a mixed spectrum library containing Martian-specific minerals is constructed, thereby making up for the lack of data in the preset standard spectrum library and avoiding the problem of poor regional adaptability of directly using the preset standard spectrum library, that is, directly using the Earth spectrum library may not accurately reflect the surface characteristics of Mars, thereby improving the adaptability of the model to the Martian surface and ensuring that the model has higher recognition accuracy in the specific environment of Mars.

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 invention discloses a Mars surface flight-oriented ornithopter attitude estimation method, which comprises the following steps: sensor data acquisition: acquiring original data of a Mars ornithopter through a sensor; sensor data filtering processing: carrying out data filtering processing on the original data acquired by the sensor; preprocessing sensor data, performing complementary filtering processing on the filtered data, and taking an obtained attitude quaternion as an estimation reference of an attitude estimation algorithm; attitude estimation: fusing the preprocessed sensor data by adopting an improved self-adaptive gradient descent algorithm to obtain a final attitude estimation result; and attitude description and updating: updating the attitude of the Mars flapping-wing aircraft by adopting a quaternion method, and converting the attitude into attitude angle information as attitude description. Through data preprocessing and an improved gradient descent algorithm, rapid and accurate convergence of attitude estimation is ensured, and the real-time performance of the system is ensured.

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.

A multifunctional integrated Mars reentry detector relates to the technical field of Mars detection and mainly comprises a detector body, a rotor wing, a nose cone cover, a rotating device, a heat shield and the like. During launching, the rotor wings are in a compressed and folded state, and the detector body, the nose cone cover and the heat-proof cover serve as a whole device fairing. In the initial stage of reentry, the heat shield is used for protecting the rotor blade from pneumatic heating, can be further unfolded to a certain angle after descending at a certain speed, and serves as a speed brake for further speed reduction. And when the speed is reduced to subsonic speed, the rotor blades are unlocked and released, the blades are unfolded through an internal telescopic mechanism, the blades are driven to rotate by utilizing relative incoming flow, and rotation kinetic energy is converted into electric energy to be stored while lift force is provided for deceleration. In the landing stage, the rotor wings are switched to an active working mode, stored electric energy is used for providing rotating power for the rotating device, and autonomous hovering and obstacle avoidance are achieved; and the heat shield is completely unfolded to provide stable support and buffer for the detector body.

The utility model discloses a spark sand jet simulation vacuumizing tank which comprises a tank body, the tank body is installed on a base, and dry ice can be contained at the bottom end in the tank body. When the device simulates a spark environment, dry ice is put into the tank body, the vacuum pump is started to vacuumize the tank body, the dry ice volatilizes to form carbon dioxide, then the irradiation lamp is started, solar irradiation is simulated, the temperature is reduced through the temperature adjusting assembly, and then the temperature sensor and the barometer are started to perform integrated monitoring. A fan is installed inside or an air inlet pipe is installed on the side wall to introduce airflow according to requirements, a certain amount of fine sand is sprayed into the tank body through the sand spraying device, and finally various data including pressure, temperature, wind speed, sand and dust concentration and the like in the experiment process are recorded through the data detector, so that experiment detection is completed. And the performance and durability of the Mars rover can be effectively and accurately evaluated.

This invention is embodied in a system and device for transporting assets (small satellites, commodities, or other payloads) in space. The preferred system comprises a scaffold of relay stations strategically orbiting one or more celestial bodies. The orbits are complimentary to each other so that the relay stations can transfer mass from one station to another. In this way, the system can support different logistical networks connecting the space between orbits such as Low Earth orbit (LEO), geostationary orbit (GEO), and Low Lunar orbit (LLO), and even between Earth and Mars.

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 invention discloses a Mars in-situ carbon dioxide cooling supply nuclear energy power generation system, belongs to the technical field of nuclear energy power generation systems, and particularly relates to an extraterrestrial celestial body in-situ resource utilization (ISRU) nuclear energy power generation technology. The problems that an existing Mars closed Brayton cycle nuclear power generation subsystem is difficult in heat dissipation and difficult in working medium supply are solved. The system comprises a carbon dioxide liquefaction subsystem and a closed Brayton cycle nuclear power generation subsystem. The Mars in-situ carbon dioxide cooling replenishment nuclear energy power generation system is suitable for deep space exploration and extraterrestrial energy utilization.