36 results about "Martian surface" patented technology

The invention provides an obstacle avoidance method for soft landing of an object outside the earth under a multi-obstacle constraint environment, and belongs to the technical field of navigation, guidance and control. The invention provides an improved optimum soft landing guidance method based on convex optimization for the problem of optimum guidance under the multi-obstacle constraint environment on the basis of the previous achievements. The method is characterized by, to begin with, establishing an optimal second-order cone programming model without obstacle constraint, and standardizing the model; then, carrying out analysis modeling on bulge obstacles on the surface of the Mars, and carrying out linear conversion to enable nonconvex constraints to be converted into convex constraints; fusing an obtained bulge obstacle mathematical model into second-order cone programming problems, and establishing a complete optimal second-order cone programming model with the obstacle constraints being taken into consideration; and finally, verifying the correctness of the algorithm through simulation analysis of three different types of obstacle constraints. The method can be applied to the study of lunar soft landing; the simulation result shows that the new algorithm realizes effective avoidance of three-dimensional space obstacles; available space for flying above and surrounding the obstacles is utilized reasonably; and fuel minimization is met simultaneously.

The invention provides a method for detecting a Mars underground ice layer by use of a double-frequency radar. According to the method, through analyzing characteristics including radar echo signal intensity and time-delay and the like, information such as the thickness of the cover layer on the surface of the Mars, whether the ice layer exists underground on the Mars, the thickness of the ice layer and the like can be obtained. Compared to a neutron measuring technology in the prior art, the accuracy and reliability are higher.

The invention discloses a comprehensive environment heat balance test system for a Mars detector single-machine product. The system comprises a Mars environment simulation chamber, a solar irradiationsimulation system, a Mars atmosphere simulation system, a Mars surface wind simulation system, a temperature control system and a test piece support system, wherein the Mars environment simulation chamber is a horizontal and capsule-shaped cabin body, container gates which can be opened are arranged at the two ends of the cabin body, and the Mars environment simulation chamber is mainly used forforming a closed space without obvious leakage and maintaining a special atmospheric environment in the cabin. The system can provide comprehensive stress environment tests of five parameters including gas atmosphere, wind speed, pressure, solar irradiation and environment temperature on the surface of Mars, and is easy to operate and good in generalizability.

The invention discloses a wheel suitable for the terrain environment of the Mars. The wheel comprises a wheel body, a wheel driving joint, spokes, a driving mechanism, a hub, and pawls, wherein the wheel driving joint enables the wheel body and the driving mechanism to be connected, and connection joints connecting the spokes and connecting the driving mechanism are respectively designed; the wheel driving joint is connected with the spokes through screws and nuts; the spokes are rigid spokes and are mounted on one side of the wheel; the driving mechanism is arranged at the inner part of the hub; the spokes are connected with the hub through screws and nuts; the pawls are connected with the hub through screws and nuts. The wheel is beautiful in structural appearance, easy in machining, compact in structure, high in passability on the surface of the Mars and high in strength, can bear the weight of a Mars patrolling device, and can bear certain torque.

The invention relates to a spark surface gas component simulation device and method. In order to solve technical problems that an existing ground simulation scheme has large simulation errors and cannot truly and accurately simulate the pressure environment of the surface of Mars, the invention provides a device and a method for simulating gas components on the surface of Mars. The gas componentson the surface of the Mars are considered to the maximum extent, an atmospheric state of the Mars can be simulated close to the actual atmospheric state, and technical support is provided for a real and accurate environment simulation test of a Mars detector on the ground.

The invention discloses a separable wireless networking imaging system and an imaging method suitable for extraterrestrial celestial body detection. The imaging system comprises a wireless control unit and a plurality of wireless cameras, the wireless control unit and the wireless cameras adopt a wireless connection communication mode, and the wireless cameras are divided into a fixed type and a separated type, so that the problem of third-view-angle imaging of extraterrestrial celestial body detection is solved, independent imaging on the extraterrestrial celestial body is realized, and the imaging efficiency is improved. Image and video data with more unique visual angles are obtained, the visuality and the display degree of key link engineering state monitoring are better achieved, and the effect that human beings obtain process images of a Mars rover moving on the surface of Mars for the first time is achieved.

The invention relates to a distance and speed measurement sensor beam pointing determination method for Mars landing, which comprehensively considers the configuration layout of a detector, and considers the measurement precision requirements of long and short distance sections and heterogeneous backup of two types of distance and speed measurement sensors. The pointing directions of four fixed pointing beams of the microwave distance and speed measuring sensor and nine fixed beam pointing directions of the phased array sensor are determined. In actual use, the phased array sensor calculates and appoints four wave beams through a spaceborne computer in each measurement period to provide distance measurement and speed measurement information. Multi-beam information fusion processing is carried out on relative distance and speed information obtained in eight beam directions of the microwave distance and speed measuring sensor and the phased array sensor, so that the relative distance, speed and other information of the detector relative to the surface of the Mars can be solved.

The invention discloses a multi-case weak supervision Mars surface morphology detection method based on online learning, and belongs to the field of machine vision object detection. The method aims at solving the problems that an existing weak supervision object detection method is low in detection precision and converges to a local optimal solution. Comprising the steps of generating a plurality of candidate boxes for a Mars long-range image by adopting a selective search algorithm; a VGG16 network model is adopted to carry out image feature extraction on the Mars long-range image; obtaining a full connection feature of each candidate box; in the weak supervision detection network, full connection features of candidate boxes are input, the category of each candidate box is judged through classification and detection branches, position information of the candidate boxes is scored, and finally scores of the candidate boxes are obtained by multiplying scores of the two branches and serve as case-level labels; and the K-level refined network layer takes the score of each candidate box of the multi-case learning network or the previous-level branch as supervision information, trains other optimized branches of the network, and carries out backward propagation calculation. The method is used for detecting the surface topography and the target of the Mars.

The invention discloses a flying method on Mars, and a Mars flying device. According to the method, a medium on the surface of Mars and a medium acceleration unit are adopted; under the action of electric power, the medium acceleration unit works, the medium is conveyed to the medium acceleration unit, and is separated from the medium acceleration unit after being accelerated by the medium acceleration unit, and reactive force is generated due to momentum conservation and overcomes Mars attraction to drive a load to take off. The method is novel and unique, is suitable for the Mars environmentwhich does not have atmosphere and cannot fly by means of atmospheric buoyancy, breaks through the obstacle of Mars morphology to scientific investigation, and can expand the detection, investigationand development capacity of human beings to Mars.

The invention discloses an active compensation method for a somatosensory micro-low gravity simulation device, and the somatosensory micro-low gravity simulation device comprises a gravity balance assembly, and a buffer assembly which provides buffer potential energy for the gravity balance assembly to at least partially balance the gravity of a human body. The active compensation method comprises the following steps: S1, acquiring an additional torque generated by a micro-low gravity simulation device; and S2, outputting compensation torque in the opposite direction to the somatosensory micro-low gravity device according to the additional torque. The reverse compensation torque is output according to the obtained additional torque, so that the walking effect of the astronaut in the training system is consistent with or close to the actual walking effect on the moon surface and the Mars surface, the active compensation efficiency is improved, and the simulation precision of the device is improved.

The invention discloses a simulated Mars soil preparation method which comprises the following steps: sequentially drying, removing impurities and crushing volcanic ash to obtain volcanic ash particle aggregates with different particle size ranges, and obtaining corresponding simulated Mars soil standard gradation according to a preset soil mechanical property target value range. The simulated Mars soil can be produced in batches according to the standard grading; the invention further discloses a construction method of the simulated Mars soil test bed, the simulated Mars soil laying area is arranged in the foundation pit, layered filling of the simulated Mars soil is carried out to obtain the test bed, and after filling of each layer is completed, the physical and mechanical parameters of the test bed are controlled according to the physical and mechanical property requirements; a severe landing environment is built on the surface of the test bed. The Mars surface fire soil landform and physical and mechanical properties can be truly reproduced, it is ensured that the Mars lander can recognize the severe environment of the Mars surface with high precision in the Mars surface soft landing process, and meanwhile accidents such as foot pad subsidence are avoided.

The invention relates to a porous injection device, in particular to a porous injection device for generating multi-type spark rotational flow. The invention aims to solve the problems that the authenticity of a high-speed dust storm environment effect on the surface of the Mars simulated by an existing Mars environment simulation device is poor, only a single rotational flow type can be generated, and people cannot conveniently research the real Mars dust storm environment. The device comprises a base, four pose adjusting mechanisms and four ejectors. The four pose adjusting mechanisms are evenly distributed and installed on the upper surface of the base, and each pose adjusting mechanism is provided with one ejector. The invention belongs to the field of aerospace.

The invention discloses a kinematics closed-loop test system and method based on virtual reality and DEM information interaction, and belongs to the technical field of deep space probe ground system experimental testing. The method comprises the following steps: firstly, establishing a Mars surface three-dimensional topographic map by using a virtual reality system, loading a Mars rover real three-dimensional model into the three-dimensional topographic map, performing interaction of a DEM, an attitude position and time information by the virtual reality system and a kinematics module, and completing real-time transmission of camera images with a spaceborne computer at the same time. The test system effectively simulates the working environment of a Mars rover on the surface of the Mars.

The invention provides a locating method for non-cooperative targets in images of the Martian surface. The locating method comprises the following steps that step 1, a Mars exploration mission groundapplication system is responsible for proposing the acquisition task, aiming to the targets on the Martian surface, of location locating information of the images on the Martian surface; step 2, the factors of device-ground time delay and device-ground timing system are considered, a ground observation and control system, a VLBI orbit measurement system and a detector autonomous navigation systemuse the images of the targets on the Martian surface in the step 1 as input to complete the extrapolation data acquisition of the orbit information of a detector and carry out the correlation analysisof positioning errors. The locating method further improves the locating information accuracy.

The invention discloses an environment simulation device, system and method for a low air pressure discharge test on Mars surface. The method comprises the following steps of: connecting the pressurecontrol unit with the vacuum flange through the pressure relief interface and the re-pressing interface; acquiring the vacuum degree data information in the vacuum tank, and comparing the received vacuum degree data information with the vacuum degree numerical range set by the actual test; when the vacuum degree data is larger than the upper limit value of the vacuum degree numerical range set bythe actual test, carrying out the pressure relief treatment on the vacuum tank; when the vacuum degree data of the pressure acquisition module is smaller than the lower limit value of the vacuum degree numerical range set by the actual test, carrying out the re-pressing treatment on the vacuum tank; and when the vacuum degree data of the pressure acquisition module is in the vacuum degree value range set by the actual test, carrying out the pressure maintenance treatment on the vacuum tank. According to the environment simulation device, system and method, the interference of a vacuum controlsystem is avoided, the function of pressure automatic control is provided, the pressure relief rate is controllable, the acquired data can be stored and analyzed, the power supply system is safe and reliable, and the stable operation time is long.