252 results about "Celestial body" patented technology

Implementations of the disclosed subject matter provides a system having an artificial light source disposed at a distance from earth or other celestial body, where the artificial light source is configured to project one or more beams of light onto the earth or other celestial body. The system may include a photovoltaic array disposed in an area on the earth or other celestial body that is 200 m-20 km or more in any one dimension that is configured to receive the projected one or more beams of light and is configured to convert the received one or more beams of light into electricity.

The invention discloses a celestial body data retrieval method and device, a storage medium and electronic equipment, and the method comprises the steps: matching the coordinate information of each celestial body image in a celestial body image header file with the coordinate information contained in each celestial body star catalogue record in a star catalogue database of each different data source according to the coordinate similarity; and determining each celestial body data pair formed by the celestial body image and the celestial body star catalogue record which have a matching relationship, and for each celestial body data pair, carrying out feature coding on the celestial body image and the celestial body star catalogue record in the celestial body data pair to obtain the multi-modal features of the celestial body data pair. A multi-modal feature is constructed by associating a celestial body image in a celestial body image header file with celestial body star catalog records in a star catalog database. And when celestial body data retrieval needs to be carried out, obtaining a retrieval result according to the multi-modal features. According to the method, the similarity of data features in the celestial body image and the celestial body star catalogue record is considered at the same time, and more accurate retrieval precision can be achieved.

The invention discloses a distributed ground-based radar atmospheric refraction error calculation method for celestial body observation. According to the method, a local numerical weather forecast model is corrected by using real-time surface meteorological parameters, atmospheric refractive index profile data containing elevation meteorological information is obtained, a geometric elevation angle of a celestial body target is taken as a standard, and a neutral atmospheric refractive index error is searched in combination with a corrected data source and a ray tracing method, so that the atmospheric refractive index is obtained. And finally, neutral atmospheric refraction error calculation and correction are realized. The effectiveness of the algorithm is verified through simulation.

The invention discloses a lunar balance dynamic parameter high-precision resolving method and system combining LRR and LLR technologies, and belongs to the field of deep space exploration and celestial body dynamics, and the method comprises the steps: constructing an LRR and LLR combined observation data set, and carrying out the preprocessing; constructing an LRR and LLR combined moon measurement model, and deducing a partial derivative of the model for a moon rotation parameter and a tidal LOVE number to obtain a combined partial derivative matrix; iterative solution is carried out through nonlinear least square to obtain dynamic parameters of the moon balance; and evaluating a resolving result and optimizing a resolving strategy, and optimizing a resolving scheme by dynamically adjusting the weight, improving a tide model and eliminating abnormal values. According to the method, the parameter calculation error is reduced, the technical advantages of two types of data are effectively integrated, the problem of insufficient observation continuity or precision of a single data source is solved, and reliable parameter support is provided for moon rotation and internal structure research.

A tiered spacecraft docking station is adapted to facilitate docking of spacecraft within outer space. A first tier includes a first frame enclosing a first area. A first net-like mesh is coupled to the first frame and fills the first area enclosed by the first frame. A second tier includes a second frame enclosing a second area. A second net-like mesh is coupled to the second frame and fills the second area enclosed by the second frame. A plurality of support beams attach the first frame to the second frame. A lander is used to slow and stop a spacecraft on a celestial body. The lander includes a first and a second webbed structure and a decelerator coupled to the first webbed structure and / or the second webbed structure. The decelerator maintains a tension in the first and / or second webbed structure below a predetermined threshold.

Described herein is a method for wireless transmission of energy in space, wherein a constellation of transmitting satellites orbiting around a celestial body, such as the planet (P) Earth or the Moon (L), are equipped with a laser apparatus for sending a beam of coherent electromagnetic waves to an orbiting satellite or another receiving target, such as a mobile vehicle or a fixed base on said generic celestial body, in order to transmit energy thereto. The total power transmitted is divided among the orbiting satellites in the constellation, resulting in less contraindications than in the case of a single transmitting system with equivalent total power. The advantage of such division among a constellation of satellites mainly consists of shorter periods of solar eclipse, since sunlight is necessary for the operation of the transmission system. The receiving target or satellite converts the beam of electromagnetic waves into electric energy.

The invention provides a wide-area tomography calculation astronomical imaging system and device, and the system comprises a snapshot spectral imaging module which is used for capturing full-view three-dimensional hyperspectral data of an observation view field; the red shift resolving module is used for processing the three-dimensional hyperspectral data through a hybrid algorithm based on the three-dimensional hyperspectral data, and inverting a target red shift value, three-dimensional space coordinates and physical parameters of the target celestial body; the chromatography data visualization module is used for generating a three-dimensional chromatography map through pseudo-color labeling and a three-dimensional modeling method based on the target red shift value, the three-dimensional space coordinates and the physical parameters; and the control module is used for configuring the snapshot spectral imaging module based on the observation target parameters. According to the method, high-precision cosmic chromatography of a wide-area sky area is realized, three-dimensional hyperspectral data is converted into a visual and reliable three-dimensional space distribution model and a physical parameter map, and reliable technical support is provided for frontier research of cosmic large-scale structures, galaxy evolution and dark matter distribution.

The invention belongs to the technical field of inverse synthetic aperture radars, and particularly relates to a tidal deformation dynamic modeling and parameter inversion method based on hybrid GRFT. The specific process is as follows: dynamic slope distance and echo modeling: aiming at each scattering point of a target celestial body, combining a radar position and introducing three-dimensional rotation correction caused by rotation to calculate a dynamic slope distance, and simulating a radar echo signal based on the dynamic slope distance; echo processing based on mixed GRFT: performing pulse compression on echo signals, compensating phase errors caused by rotation and deformation in sub-apertures by using the mixed GRFT, and performing non-coherent superposition on GRFT output of each sub-aperture; searching parameters: setting a search range of initial height and dynamic viscosity of each scattering point, setting a fitness function as non-coherent superposition energy synthesis of each scattering point, and searching in the search range until a termination condition is met; and tide deformation quantity calculation: calculating the tide deformation quantity according to the estimated values of the initial height and the dynamic viscosity of the searched scattering points.

The invention relates to the technical field of extraterrestrial celestial body landing obstacle avoidance, in particular to a landing obstacle avoidance trajectory planning method, system and equipment based on an error-considered voxel model and a medium. The method comprises the following steps: constructing a terrestrial body pixel model by using point cloud data acquired by a laser radar, establishing an obstacle body pixel error model containing three probability error regions through point error propagation, and quantifying the risk degree and uncertainty of each pixel block; in combination with a Gaussian distribution probability density function of land device position uncertainty and a constructed obstacle object pixel error model, calculating a collision probability; and integrating the calculated collision probability as a core component of the repulsive force potential into an artificial potential field method framework, deriving a control instruction based on the Lyapunov stability theory, and planning a safe landing trajectory.

The application provides a variable configuration spacecraft system and method for non-cooperative target capture, and belongs to the field of deep space exploration. The method comprises the following steps: 1) a rigid combination flies to the vicinity of the target; 2) the combination is spun to be expanded into a ring belt; 3) the ring belt envelopes the target; and 4) the ring belt encloses the target. Large space debris and small celestial bodies both belong to non-cooperative targets, and cannot provide special interfaces for assisting capture. It is extremely difficult to develop general control mechanisms and methods to realize reliable capture and stable connection of various targets. In order to solve the problem, the application utilizes the inter-satellite connection to expand a plurality of controllable satellites into a ring-shaped multi-body tether satellite formation system, and carries out ring belt enveloping and then enclosing the tether to realize capture of a non-cooperative target with large scale, complex geometric shape, great uncertainty of motion state and inertia information according to a predetermined trajectory. The application has the advantages of high applicability, flexibility, high intelligence, reusability and small size.

This disclosure provides a method for segmenting a star catalog. The method includes: acquiring a target star catalog file corresponding to a target celestial sphere, the target star catalog file including observation data of M celestial bodies in the target celestial sphere; dividing the target celestial sphere into N sub-regions and N region numbers corresponding to the N sub-regions based on a predetermined maximum segmentation level K; determining the number of celestial bodies in each region represented by each of the N region numbers based on the observation data of the M celestial bodies in the target star catalog file, obtaining a result determining the number of N celestial bodies; and segmenting the target star catalog file according to the matching result between the result determining the number of N celestial bodies and a predetermined segmentation threshold T, determining multiple star catalog subset files corresponding to the target star catalog file. This disclosure also provides an apparatus, device, and storage medium for segmenting star catalogs.

The application discloses a small-sized separated penetrator for in-situ detection of celestial bodies, and relates to the technical field of penetrator equipment, comprising an aluminum honeycomb buffer module, which comprises an external protective shell and an aluminum honeycomb, and has the beneficial effects that the application is provided with in-situ detection of high-speed penetration of celestial bodies, and discloses a small-sized separated penetrator, which comprises a planet soil penetration module and a star table detection module, and realizes autonomous separation in the impact penetration process, the star table module can realize star table detection and communication with an orbiter, the penetration module is internally provided with an energy storage device and an impact hammer, and can continue to penetrate and dive relying on the energy storage device after impact; the star table module is connected with the penetration module through flexible wires, and can supply power and signal transmission to the latter, the technology enables the penetrator with the modular characteristic to have the in-situ detection capability of planet soil profile, aims to expand the application mode of the penetrator for celestial body detection, and provides a scientific basis for the research of star table structures.

This invention relates to a multi-constraint trajectory planning method for bouncing movement on the surface of complex small celestial bodies, belonging to the field of deep space exploration. The implementation method is as follows: Establishing a closed-form relationship between bouncing movement distance, velocity, takeoff angle, and energy consumption, and a two-layer expansion radius obstacle representation model; establishing escape velocity constraints, no-fall constraints, fly-through feasibility constraints, and convex obstacle fly-through constraints; using the two-layer expansion radius obstacle representation model and multiple constraints, establishing a fly-through feasibility determination mechanism for obstacles; using Poisson-disk sampling to establish the bouncing reachability domain and an analytical solution for the energy-optimal trajectory satisfying multiple constraints; establishing a reachability domain filtering method based on the bouncing reachability domain and the analytical solution for the energy-optimal trajectory; using energy consumption as the weight, employing the A* algorithm to search for a global energy-optimal bouncing path point sequence and the corresponding velocity and takeoff angle of each path point, generating a global energy-optimal trajectory, thus realizing multi-constraint trajectory planning for bouncing movement on the surface of complex small celestial bodies.

The invention discloses a space science data collaborative computing method and system based on a no-service computing architecture. According to the method, the technical problems that in traditional space science data processing, resource elasticity is insufficient, multidisciplinary cross-domain heterogeneous computing environment collaboration is difficult and data islands are serious are solved by constructing a whole-process and service-free computing framework of data access-function encapsulation-collaborative scheduling-result aggregation. Specifically, tasks such as preprocessing, analysis and modeling of space science data are packaged into a lightweight and non-service calculation function, data calculation collaborative calling in the interdisciplinary field is achieved in combination with a multi-calculation-node permission management mechanism, and calculation resources are distributed according to needs through a dynamic resource scheduling algorithm. The multi-disciplinary cross-domain TB / PB-level spatial data processing method has the advantages of being high in resource utilization rate, low in operation and maintenance cost and high in expansibility, and can be widely applied to space science research scenes such as sun-earth space physics, deep space exploration and high-energy celestial body outbreak.

The application discloses a kind of small celestial body weak gravity condition under detection robot movement control method and device, the method of the present application includes first to detection robot is carried out steady gait planning, at the end time of the foot end trajectory obtained, add the active attachment bias Δr for ensuring that detection robot is attached to the clamping of small celestial body star table;Then the foot end trajectory is as leg desired position, inverse kinematics is solved to obtain the desired joint angle of each joint, obtains the current joint angle of each joint of detection robot, and calculates the deviation between the current joint angle and the desired joint angle of each joint, and the deviation is input into the movement controller to obtain the joint output control torque, the corresponding joint is controlled by joint output control torque, until the deviation is less than set value.The present application can realize the stable attachment and movement of detection robot on the surface of small celestial body under the condition of weak gravity of small celestial body, create prerequisite for the smooth development of detection task.

The application provides a celestial body orientation parameter solving method and system based on inverse VLBI interferometry and a medium. The method comprises the following steps: firstly, a rotation orientation physical model of a celestial body and an inverse VLBI differential measurement model are established, a lander coordinate and a celestial body orientation parameter are introduced into the model by combining the conversion between a non-inertial system and an inertial system coordinate. High-precision differential measurement tracking data of inverse VLBI are obtained, and based on the principle of the least square method, a lander position and a celestial body orientation model parameter are determined, so that the residual square sum between the calculated theoretical observation value of inverse VLBI and the ground observation value is minimum, and high-precision extraterrestrial celestial body orientation parameters are obtained. The application can realize precise positioning of a lander and solving of celestial body orientation parameters, the obtained data are high in precision, high-precision inverse VLBI differential measurement data can significantly improve the solving precision of the celestial body orientation model parameters, and then information about the internal structure and surface mass distribution change of the celestial body is provided, and additional constraints for the improvement of the celestial body physical model are provided.

This disclosure provides a method, apparatus, and storage medium for on-orbit optical axis calibration of a spectrometer, relating to the field of astrophysical detector calibration technology. The method includes: performing a helical scan of the celestial body under test; during the scan, continuously acquiring the imaging position of the centroid of the celestial body on the imaging target surface of the imaging device, and acquiring the thermal radiation energy of its pointing position at a first angle based on a preset acquisition frequency using the spectrometer; inverting the continuously acquired imaging positions onto the first target surface, and mapping the acquired thermal radiation energy to the corresponding position on the first target surface according to the acquisition time, generating first thermal radiation data; and using the position of the point with the highest thermal radiation energy in the first thermal radiation data on the first target surface as the optical axis pointing position of the spectrometer at the first angle. This disclosure achieves joint observation by synchronously controlling the imaging device and spectrometer of the astrophysical detector, and determines the true pointing position of the spectrometer's optical axis through the observation results, which is simple to operate and has high accuracy.

The application provides an extraterrestrial celestial body soil detection probe, which comprises a shell, a soil collecting structure and a soil testing structure; the soil collecting structure is arranged on the shell; the soil collecting structure comprises a collecting hole and a boss; the boss is arranged on the shell, the top of the boss is higher than the outer surface of the shell, and the collecting hole is connected between the inside and outside of the shell; and the soil testing structure is arranged in the collecting hole. The extraterrestrial celestial body soil detection probe further comprises a heating sheet, a pipe and a volatile component detector; the volatile component detector is arranged in the shell, the heating sheet is attached to the outer wall of the collecting hole, and the collecting hole is connected with the volatile component detector through the pipe. The four soil collecting structures arranged in the circumferential direction of the shell are used to collect soil, and soil physical property analysis is carried out through the soil testing structure, so that the demand for extraterrestrial celestial body soil detection is met, and important data support is provided for planetary science and the like.

The invention relates to a mechanism for displaying lunar eclipse and solar eclipse for a mechanical or electromechanical timepiece movement configured to be able to operate said mechanism, the eclipse display mechanism (1) comprising a first mobile indicator (2) corresponding to a first celestial body, such as the sun, and a second mobile indicator (3) corresponding to a second celestial body, such as the sun, the food display mechanism (1) comprises a first movement indicator (2) corresponding to a first celestial body, such as the moon, and a second movement indicator (3) corresponding to a second celestial body, such as the moon, the food display mechanism (1) comprising a first zone (6) in which the first indicator (2) and the second indicator (3) are visible, and a second zone (7) which allows the one or more indicators (2, 3, 4, 5) to be masked behind the cover plate (8), the food display mechanism (1) comprising a third movement indicator (4), and a third movement indicator (4) corresponding to a second celestial body, the configuration of which is different from the configuration of the second indicator (3), the third movement indicator (4) having at least one visible characteristic different from that of the second movement indicator (3), characterized in that the third indicator (4) is visible in the first zone (6) in place of the second indicator (3).

Disclosed are a method and an astrophotographic apparatus for acquiring images of targets in a sky area. The method includes: step 1, an image acquisition device is driven through a controlled rotatable component to point to the position near a target in a sky area, and images of the sky area are acquired through the image acquisition device; step 2, the images of the sky area are analyzed to obtain the right ascension coordinates and the declination coordinates of the center point of images for synchronizing the coordinates to the controlled rotatable component; step 3, the image acquisition device is driven by the controlled rotatable component to point to a target position of the target right ascension coordinates and the target declination coordinates corresponding to the target celestial body to acquire the images; and step 4, an image processing is performed on the images to obtain the processed images.

The application discloses a kind of structure optimization method, device, terminal equipment and storage medium of basin type insulator, by selecting the same number of coordinate points as target coordinate points from the basin body concave surface and basin body convex surface of the parameterized finite element model of basin type insulator, then according to the overall maximum field intensity of basin type insulator, concave surface maximum field intensity, convex surface maximum field intensity, first difference and second difference, construct objective function, according to the ordinate of target coordinate point, iteratively update operation is carried out to initial celestial body according to objective function and initial celestial body using Kepler algorithm, when the iteration number of iteration update operation reaches the preset iteration number threshold, obtain target celestial body, finally according to target celestial body, generate the target structure parameter of basin type insulator. Therefore, the present application overcomes the defect that the current structure optimization method is easy to fall into local optimum, and ensures the practicability of the structure optimization scheme of basin type insulator.

An object of a system according to an embodiment is to make starry sky observation easier and more enjoyable and to promote information sharing and exchange between users.SOLUTION: A system includes an imaging unit, an identification unit, an explanation providing unit, an interaction unit, an information sharing unit, and a community unit. The photographing unit photographs a starry sky. The identification unit analyzes the image captured by the imaging unit to identify celestial objects and constellations. The explanation providing section provides an explanation about the celestial body or the constellation identified by the identifying section. The interaction unit performs interaction with a user. The information sharing unit performs information sharing between users. The community component facilitates interaction between users.SELECTED DRAWING: Figure 1

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 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.

The invention belongs to the technical field of industrial automation, and particularly relates to a Healpix-based star catalogue homogenization segmentation and evaluation method. The method comprises the following steps: S1, acquiring original star catalogue data, and determining Healpix grid level parameters based on an expected subdivision degree of a user; s2, calculating a Healpix pixel index number of each celestial body by adopting a Healpix algorithm based on celestial sphere coordinates of each celestial body in a celestial sphere equator coordinate system contained in the original star catalogue data; s3, constructing a blank star catalogue, and constructing a homogenized star catalogue based on the celestial body set extracted by the sampling strategy and the Healpix pixel index number corresponding to each celestial body contained in the celestial body set; and S4, constructing a Uscore evaluation model, performing Uscore scoring on the homogenized star catalogue by using the Uscore evaluation model, and evaluating the uniformity of each celestial body in the homogenized star catalogue based on the Uscore score. According to the invention, an objective and quantifiable comparison reference is provided for the effects of different homogenization methods.

The application discloses a small celestial body penetration anchoring test platform and a test method thereof. The test platform comprises a main structure, a simulated asteroid container, a launching unit, a speed meter, a camera, a force steel wire, a tension meter, a rocker arm, and a rocker arm support. The launching unit comprises a mounting plate, a base, a launching cylinder, a piston, a cartridge, a ejector pin, a recovery spring, an electromagnet, an anchor body, a buffer pad, a flange, an ejector pin support, and a pose adjustment groove. The cartridge is internally provided with air holes, so that the penetration depth, the penetration trajectory, and the anchoring force of the anchor body in different speeds, different penetration angles, and layered asteroid soil can be tested. The anchor body penetration power is provided by a blank cartridge, and the blank cartridge is triggered by the electromagnet hitting the ejector pin. The application has the characteristics of high test efficiency, full test coverage elements, low cost, safe and simple operation, and the like.

The invention relates to a satellite system (100) for monitoring and detecting space objects (102) in near-celestial space, in particular for monitoring and detecting space debris, preferably for determining at least one property of the space objects (102), comprising satellites (108, 110, 112, 114, 160) arranged on at least one first principal orbit (104), a torus-shaped monitoring area (116) extending around the celestial body, wherein each of the satellites (108, 110, 112, 114, 160) has an observation device (164) arranged and configured to generate images of space objects (102) within an observation field (108b, 110b, 112b, 114b) and to image space objects (102) within the torus-shaped monitoring area (116), at least one Control device (166) which is arranged and designed to align the observation fields (108b, 110b, 112b, 114b) in such a manner,that images of the space objects (102) located in the torus-shaped monitoring area (116) are generated.

The application discloses an extraterrestrial celestial body task area search path planning method based on an elevation map and belongs to the technical field of space robots. The method is as follows: the slope data in a task area is solved through the point set data of the elevation map, and the alternative passing position points of the rover are determined; the planning grid size is determined, and whether the grid is passable is determined according to the proportion of the number of passable points in the grid to the total number as a judgment standard; the exploration value of each grid is determined, and a weight value is assigned to the grid. The current grid is taken as a center point, the detectable nodes in a predetermined range around the current grid are marked as detected nodes, and the weight values of the detected nodes are reduced; the value of each grid in the passable range around the current grid is judged with the current grid as a center point, if there is a grid with a value not less than an end threshold, the grid with the maximum value is selected as a next path node, the above steps are repeated, and the extraterrestrial celestial body task area search path planning based on the elevation map is realized.

The invention discloses an intelligent staged compression method and system for radio astronomical data based on deep learning. The method comprises the following steps: 1) constructing a celestial body signal frequency domain template library according to observation data in the radio astronomy field; 2) mapping current observation data to be processed to a frequency domain to generate a frequency point matrix; 3) extracting a frequency domain feature of each frequency point from the frequency point matrix, performing similarity calculation on the frequency domain feature and a feature corresponding to each template, if the similarity is greater than a set threshold value, determining that the corresponding frequency point is an effective frequency point, otherwise, determining that the corresponding frequency point is an invalid frequency point; (3) the effective frequency points are analyzed and processed according to channel dimensions, and if the difference between the adjacent channel data is smaller than or equal to a difference threshold value, the difference value between the adjacent channel data is recorded in a difference coding mode; 4) performing secondary compression on the output data in the step 3); and 5) generating a standard Fits format file from the secondary compressed coding data and adding metadata parameters. According to the method, the bottleneck problem of mass data storage and transmission caused by multi-beam observation is effectively solved.