40 results about "Mars rover" patented technology

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.

A 3D printing rover system for on-site additive manufacturing, consisting of: a mobile chassis that supports the structure of the rover system and facilitates the movement of the rover system through terrain; a robotic arm with a 3D printing extruder configured for layer-by-layer additive manufacturing; a material storage and delivery system configured to store and feed printing materials to the 3D printing extruder; a control system with autonomous operating functions configured to: receive real-time feedback about the environment, Adjust print parameters independently and Navigate and position the rover for optimal printing locations; a sustainable energy system configured to provide continuous energy for the operation of the rover system; and a thermal management system that is operatively linked to the control system and regulates the temperature of key system components to ensure smoother operation.

The invention belongs to the technical field of data processing, and discloses a Mars rover non-contact trafficability estimation method and system based on thermal inertia, and the method comprises the steps: obtaining a ground surface temperature time sequence and environment parameters of a target region; constructing a thermal inertia estimation model, and inputting the earth surface temperature time sequence and the environmental parameters into the thermal inertia estimation model to obtain a thermal inertia estimation value of the fire soil; constructing a thermal inertia and trafficability index relation model, inputting the thermal inertia estimation value of the fire soil into the thermal inertia and trafficability index relation model, and outputting a predicted trafficability index; and determining a trafficability state grade according to the predicted trafficability index, and generating a navigation control suggestion, so that the Mars rover passes through the target area according to the Mars rover navigation control suggestion. According to the method, the trafficability index of the Mars rover is predicted by extracting the thermal inertia estimation value of the fire soil in the target area, the evaluation precision of the Mars rover passing through the target area can be effectively improved, and the driving safety of the Mars rover is ensured.

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.

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 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 invention relates to a high-speed unmanned Mars rover capable of actively switching suspension modes, and belongs to the technical field of deep space exploration, the high-speed unmanned Mars rover comprises a walking frame, a suspension and a switching mechanism, the walking frame comprises a rover frame, a connecting beam, two swing arms and two connecting rods, the suspension comprises an outer fixing plate and a lower shock absorber, and the switching mechanism comprises a rotating shaft, an outer moving plate and an actuator. The two ends of the lower shock absorber are connected to the lower frame and the outer fixing plate correspondingly firstly, then the rotating shaft fixed to the upper frame slides in the curve hole, the linear hole and the expanding hole in a switching mode, when the unmanned Mars rover is parked, the rotating shaft slides in the curve hole to level the rover frame, and when the unmanned Mars rover runs at a low speed, the rotating shaft slides in the curve hole to level the rover frame. The rotating shaft slides in the linear hole, so that the frame swings along with the two swing arms, when the unmanned Mars rover runs at a high speed, the rotating shaft slides in the diameter expanding hole, vibration and shock absorption on the two swing arms are transmitted to the frame, and switching of the suspension among a flexible suspension, a passive suspension and a rigid suspension is achieved.

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.

The application belongs to the technical field of data processing, and discloses a Mars rover non-contact passability prediction method and system based on thermal inertia, which comprises the following steps: obtaining the ground temperature time sequence and environmental parameters of a target area; constructing a thermal inertia estimation model, inputting the ground temperature time sequence and environmental parameters into the thermal inertia estimation model, and obtaining the thermal inertia estimation value of the soil; constructing a thermal inertia and passability index relationship model, inputting the thermal inertia estimation value of the soil into the thermal inertia and passability index relationship model, and outputting a predicted passability index; determining the passability state level according to the predicted passability index, and generating a navigation control suggestion, so that the Mars rover passes the target area according to the navigation control suggestion of the Mars rover. The application can effectively improve the evaluation accuracy of the Mars rover passing the target area by extracting the thermal inertia estimation value of the soil of the target area to predict the passability index of the Mars rover, and ensures the driving safety of the Mars rover.

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 invention provides a Mars rover demand multi-view dynamic analysis and modeling method based on mission-operation. The method comprises the steps of firstly, performing top-layer mission decomposition from a service customer dimension, and determining a customer and a business target corresponding to a mission; mission stages needing to be passed by the completion of the top mission and related execution entities are determined, and capability requirements for completing all the mission stages are determined; by taking the interest system as an analysis view angle, decomposing internal and external execution entities of the interest system involved in each operation stage; and distributing the activity process of each operation stage to a corresponding execution entity, and further identifying the capability demand from the activity of the operation stage. According to the method, multi-level and multi-view anatomy analysis is carried out on the overall demand of stakeholders, the ability demand is drawn by utilizing the modeling analysis process, and the demand source of the system is clarified. The method is used for guiding the design and development of the Mars rover, so that the comprehensiveness of demand source analysis can be ensured, and the availability of the established model is effectively improved.

The present disclosure provides a method, apparatus, and device medium for correcting a Mars rover radar signal. The method comprises: interpolating each channel of raw radar data in the time domain and taking the absolute value of the interpolated signal to obtain multiple channels of high-time-resolution radar data; arbitrarily determining a channel of high-time-resolution radar data from the multiple channels of high-time-resolution radar data as first reference data; performing time-domain cross-correlation analysis on the other channels of high-time-resolution radar data and the first reference data to obtain a time-domain correlation curve corresponding to each channel of high-time-resolution radar data; correcting the time of each channel of high-time-resolution radar data using the time offset corresponding to the peak of the time-domain correlation curve of each channel of high-time-resolution radar data, and performing phase-domain analysis on the time-corrected signal to achieve phase correction. This method solves the problem of discontinuities such as jumps and faults in the downlink radar signal from the Mars rover.

The invention discloses a Mars rover multi-sensor joint calibration system and an optimization method thereof, and belongs to the technical field of Mars detection. Comprising an image and depth data acquisition unit, an environment point cloud acquisition unit, an attitude measurement unit, a data acquisition and synchronization module, a data fusion processing unit and a calibration auxiliary target. The method comprises the following steps: calibrating internal parameters; calibrating external parameters; data acquisition and time sequence correction; and carrying out data fusion and online self-correction. According to the invention, the time dimension alignment error is reduced, the manufacturing cost is reduced, the method is suitable for extreme temperature, high radiation and low pressure environments of Mars, the problem of parameter attenuation caused by environmental factors such as low temperature and vibration of the Mars is effectively solved, manual intervention is reduced, and the calibration efficiency is improved. The method has long-term stable high-precision sensing capability in a Mars surface dynamic environment, and is suitable for task requirements of autonomous navigation, terrain reconstruction, obstacle detection and the like.

A miniature spider-imitating Mars flight detection robot jointly driven by wind and electric fields can carry different types of sensors to land on the Mars along with large devices such as a Mars rover without extra driving energy, and parameter detection is achieved. Relates to the technical field of micro-robots. The detector main body is of a spider bionic foot structure and plays a role in supporting and posture control; the fiber electrification system enables the plurality of fiber filaments to be electrified, so that after the plurality of fiber filaments are electrified, due to the fact that the same charges are mutually repelled and dispersed and act with different charges in the atmosphere of the Mars, the fiber filaments can be erected, the resistance area is increased, and preparation is made for taking off by virtue of a wind field; the attitude control system applies electric quantity to the bionic feet to enable the bionic feet to bend and stretch, the asymmetric bending and stretching of the six bionic feet enable the wind resistance to be changed so as to cause the stress to be changed, and the flight direction is adjusted. The miniature spider-imitating detector is suitable for detecting stars and other stars with thin atmospheric environment and electric field environment.

The embodiment of the invention provides a Mars rover state determination method and system under sparse low-quality observation and a storage medium, and the method comprises the steps: 1, building a factor graph model for a navigation system of a Mars rover, and enabling the navigation system to obtain the state of the Mars rover; 2, according to the sampling frequency and the observation physical quantity type of the sensor, representing an observation data set of same-type state parameters at the same time, and determining the characteristics of observation data; step 3, analyzing the solution performance of the navigation system factor graph model by combining the characteristics of observation data, and judging whether a unique effective optimal solution exists or not; and 4, classifying the sparse observation data sets to form different types of data sets in combination with the characteristics of the observation data, and solving the data sets of different types to obtain a high-precision state estimation result of the Mars rover.

The invention provides a surface topography segmentation method and system based on a double-trunk coding network model, and relates to the technical field of image processing algorithms, and the method comprises the steps: determining a training sample set according to a Mars surface image; a double-trunk coding network model is constructed, the double-trunk coding network model is composed of a convolutional neural network branch and a Swin Transform branch in parallel, the multiple image samples are input into the double-trunk coding network model, and a Mars terrain semantic segmentation prediction map corresponding to each image sample is obtained; and training the double-trunk coding network model, inputting a to-be-detected Mars surface image into the trained double-trunk coding network model, and outputting a pixel-level semantic tag of the to-be-detected Mars surface image. According to the method, the terrain recognition precision and the boundary definition can be remarkably improved, the geological consistency of the segmentation result is enhanced, and technical support is provided for reliable environment perception and safe path planning of the Mars patroller.

This disclosure provides a method for calibrating the amplitude of the high-frequency polarization channel of a Mars rover's subsurface exploration radar, comprising: obtaining the average signals of the HH channel and VV channel respectively through the reflected signals of a metal plate; extracting the effective reflected signals of the HH channel and VV channel respectively based on the average signals; calculating the sum of the amplitude moduli of the effective reflected signals of the HH channel and VV channel respectively; calculating the ratio of the sum of the amplitude moduli of the effective reflected signals of the HH channel to the sum of the amplitude moduli of the effective reflected signals of the VV channel to obtain a correction coefficient; and reading the measured data of the Mars rover radar polarization channel and multiplying the measured data of the HH channel or VV channel by the correction coefficient to complete the polarization channel amplitude calibration.

1. The name of the design product: Mars Rover pants. 2. The use of the design product: for wearing. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: front view. 5. The design product is a thin product, and the top view, bottom view, left view, right view, and perspective view are omitted.

The present application provides a method and related device for designing a Earth-Mars transfer orbit. Based on a preset number of iterations, the method iteratively processes each orbital parameter through a global optimization algorithm to determine a first minimum velocity increment J from the first total velocity increment J1 of the Mars probe after launch obtained in each iteration. 1min . And determine the Earth-Mars transfer orbit according to the first assignment result of each orbital parameter corresponding to J 1min . The orbital parameters in the embodiments of the present application include the orbit insertion time t0 of the Mars probe, the time dt from t0 to the periselene point EL , the time dt from t0 to the deep space maneuver DSM , the time dt from t0 to Mars EM , the lunar gravity assist radius r PL and the lunar gravity assist azimuth angle #imgabs0#. The Earth-Mars transfer orbit determined based on the above orbital parameters can correct the magnitude and direction of the velocity of the probe when it exits the Earth's sphere of influence through lunar gravity assist, thereby reducing the fuel consumption required to control the Mars probe to enter the predetermined Earth-Mars transfer.

This invention discloses a deformable, tumbleweed-inspired Mars exploration robot based on dielectric elastomers, belonging to the field of exoplanet exploration technology, and solving the problems of large size and heavy weight of tumbleweed robots. The invention includes a spherical frame, a flexible solar panel sail, several dielectric elastomer actuators, and a central spherical cabin. The flexible solar panel sail is disposed inside and connected to the spherical frame, with the central cabin located at its center. Several dielectric elastomer actuators are embedded inside the flexible solar panel sail; one end of each actuator is connected to the central cabin, and the other end is connected to the spherical frame. This invention achieves speed control by adjusting its windward area to regulate wind power utilization. Using dielectric elastomers as actuators, it achieves volume change while maintaining a lightweight and compact structure with enhanced terrain adaptability.

The utility model relates to the technical field of simulation exhibition, and particularly discloses a Mars rover-based control simulation device, which comprises a machine base, a movable groove is formed in the machine base, a simulation assembly is arranged in the machine base, and the simulation assembly comprises a sphere movably connected to the interior of the movable groove. The simulation assembly further comprises a first motor fixedly connected to the front end of the interior of the machine base, the left end of an output shaft of the first motor is fixedly connected with a first roller, the right end of the interior of the machine base is fixedly connected with a second motor, and the upper end of an output shaft of the second motor is fixedly connected with a second roller. The inner wall of the movable groove is fixedly connected with a fixed ring, a plurality of grooves are formed in the outer part of the fixed ring, and when a person watches a Mars rover exhibition in a narrow field, a participant can control and simulate the movement of the Mars rover through the device, so that manpower and material resources are greatly saved, and the Mars rover is introduced simply and clearly.

The present invention discloses a locking and releasing device for a rotor-type Mars aircraft on a Mars rover, which includes a Mars rover, a debris shield assembly, a tail locking assembly, a rotor-type Mars aircraft, a middle locking member, and a head locking assembly. The debris shield assembly includes a debris shield, a cylindrical compression spring, an electric push rod I, a debris shield locking member, and a fixed pin I. The present invention belongs to the field of aerospace rotor-type Mars aircraft, and specifically refers to a locking and releasing device for a rotor-type Mars aircraft on a Mars rover, aiming to solve the problems of stability and reliability during the locking and releasing process between the rotor-type Mars aircraft and the Mars rover.

1. Name of the product in this design: Manned Mars Rover. 2. Purpose of this design: To carry various scientific instruments to move on the surface of Mars and complete Mars scientific exploration missions. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1.

The present invention provides an autonomous management method and system for a Mars orbiter without uplink failures in orbit, including: resetting or powering off and restarting the remote control terminal; resetting or powering off and restarting the transponder; switching the cross-backup channels of the transponder and the receiving antenna; performing main-backup switching processing on the crystal oscillator; autonomously switching the TT&C to the low-gain or medium-gain antenna mode, and at the same time, the spacecraft is in the +X sun-pointing mode and rotates 180° around the +X axis; in the +X sun-pointing mode, switching the receiving antenna back to the omnidirectional low-gain receiving mode; in the omnidirectional low-gain receiving mode, the spacecraft slowly rotates around the +X axis facing the sun; after the above-mentioned processing, if the long-term uplink-free autonomous management process still does not jump out on the spacecraft, power on the UHF relay communication machine to the single-carrier transmission mode; use the locked state of other Mars orbiters or Mars rovers to determine the life and death of the orbiter. The present invention can solve the problem that it is impossible to process through the ground when a failure occurs in the uplink channel.

1. Name of this design product: Amusement Ride (Mars Rover). 2. Purpose of this design product: for use as amusement equipment in amusement parks. 3. The key point of the design of this product lies in its shape. 4. The picture or photo that best illustrates the design points: three-dimensional picture.

The invention belongs to the technical field of flight control of aircrafts, and discloses a flight management system and a flight control method for a terrestrial planet vertical take-off and landing aircraft, and the system comprises a navigation module which carries out the state measurement of the aircraft through employing an airborne IMU, and carries out the data fusion with a downward-looking navigation camera and radio ranging; the communication module is used for communicating with a Mars rover; the steering engine module is used for receiving the control signal and driving a rotor wing to work; and the flight control module is used for receiving the data of the navigation module, generating a control instruction according to the navigation data and the target trajectory and sending the control instruction to the steering engine module so as to realize flight control of the vertical take-off and landing aircraft. The problems of survival and control of the deep space exploration aircraft under extreme conditions are solved, and the reliability is effectively improved.

A two-layer counter-based autonomous communication control and fault handling method for Mars rover components uses two layers of counters to implement component communication control and fault handling. One layer of counters records the number of consecutive communication failure cycles. When this count reaches a set threshold, communication fault handling begins. Another layer of counters records the number of fault handling cycles and controls the sequential execution of various fault handling actions. This method decouples communication control and fault handling control functions, resulting in cohesive and clear control logic, making it well-suited to addressing changing requirements. Changing any functional requirement only requires modifying that function, without spreading the impact domain. This ensures the correctness, robustness, and stability of the software system throughout the development process.

This invention discloses a method for enhancing Martian surface images based on convolutional neural networks, comprising: acquiring an image to be processed; performing an image enhancement operation on the image to be processed, the image enhancement operation including: inputting the image into a Martian surface image enhancement neural network model to obtain noise information; and removing the noise information to obtain an enhanced image. By modeling Martian surface images collected by the "Zhurong" Mars rover, the problem of Martian surface image enhancement is transformed into a problem of solving Martian surface image noise. Based on this, a convolutional neural network is designed to solve for the noise in the Martian surface images, and combined with the Martian surface image model, to achieve the enhancement of the Martian surface images. This invention can effectively improve the image acquisition quality of Mars rovers such as "Zhurong," effectively enhance the autonomous perception capabilities of the rovers, and thus contribute to the autonomous navigation and obstacle avoidance capabilities of Mars rovers such as "Zhurong."