355 results about "Celestial body" patented technology

A system includes a plurality of satellites orbiting around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to input the image data for each image into a pre-processing software pipeline to generate for each image a contrast-enhanced image data replica of each image, and an enhanced image data replica of each image, to receive from an output of a known-unknown RSO split data processing pipeline, a determination that a candidate RSO is a known RSO stored in an RSO catalog, or an unknown RSO, and to assign to the candidate RSO based on the determination, an RSO ID of the known RSO listed in the RSO catalog, or a new RSO ID.

The invention provides a star catalogue file generation method and device, a celestial body data query method and device, computer equipment and a storage medium. The star catalogue file generation method comprises the steps of obtaining star catalogue data; dividing the celestial sphere surface area corresponding to the plurality of celestial bodies into a plurality of local areas, and determining an identifier of each local area; determining an identifier matched with each celestial body data according to the right ascension and declination included in the celestial body data and the identifier of each local area in the celestial sphere surface area; sorting the celestial body data of the plurality of celestial bodies based on the identifiers corresponding to the celestial body data; and writing the sequenced celestial body data of the plurality of celestial bodies into an initial column storage file matched with the identifier to obtain a target file stored with the celestial body data, and generating file index information corresponding to the target file. The celestial body data is stored by utilizing the column type storage file, so that the problems of high maintenance cost and high use threshold caused by utilizing a database to store data are relieved while the data query efficiency is guaranteed.

A system includes a plurality of satellites orbiting around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to input the image data for each image into a pre-processing software pipeline to generate for each image a contrast-enhanced image data replica of each image, and an enhanced image data replica of each image, to receive from an output of a known-unknown RSO split data processing pipeline, a determination that a candidate RSO is a known RSO stored in an RSO catalog, or an unknown RSO, and to assign to the candidate RSO based on the determination, an RSO ID of the known RSO listed in the RSO catalog, or a new RSO ID.

The invention provides a lunar polar region sun synchronization # imgabs0 # path planning method, which can be applied to the technical field of celestial body image processing and path planning. The method comprises the following steps: independently training a plurality of enhanced U-Net models by using training data with time sequence slices and fusion types and a mixed loss function; dividing and extracting the reasoning data with a time sequence slice type and a time sequence fusion type by using a plurality of trained enhanced U-Net models to obtain a lunar polar region friendly illumination region, and preprocessing the reasoning data with the lunar polar region friendly illumination region and gradient data corresponding to the lunar polar region friendly illumination region; and based on the reasoning data after time alignment and the gradient data after space alignment, constructing a heuristic function by using mixed cost, and performing heuristic path planning by using an improved # imgabs1 # path planning algorithm with a time one-dimensional function and an in-situ waiting function to obtain a sun synchronization planning path of the lunar polar region.

The invention discloses an astronomical cross identification method based on spherical trapezoidal division, and the method comprises the steps: S1, taking a unit spherical surface as a celestial sphere, dividing the celestial sphere into a plurality of strips parallel to an equatorial line, and determining the right ascension span of each strip for the transverse segmentation of the strip; s2, dividing each strip into a same spherical isosceles trapezoid with two waists perpendicular to the equator, and taking the same spherical isosceles trapezoid as a sky area; s3, determining an index of each sky area; s4, dividing a star catalogue A and a star catalogue B, and creating a zipper type hash table based on the row number of the star catalogue B; s5, mapping each celestial body in the star catalogue B into a linked list in a hash table in a multi-thread parallel mode, and inserting celestial body data into the linked list by means of a two-stage insertion strategy; s6, mapping each celestial body in the star catalogue A into a linked list in a group of hash tables in a multi-thread parallel mode, and traversing to obtain celestial body IDs of which the spherical distance is smaller than the error radius; the method not only can completely avoid the problem of result omission, but also can greatly improve the astronomical cross identification calculation performance.

Method and device for celestial timekeeping that synchronizes independent object-relative cyclic time and displays each unique temporal interval on a single user display system. Multi-celestial cyclic time is displayed based on a user's frame of reference by aligning with recurrent and unique cyclic start / stop signals and the local reference frame timekeeping system. For example, using the Coordinated Universal time (UTC) for a user on Earth to equate the duration of independent cyclic time of Lunar18, Mars24, and so on. The method uses dimensional analysis and equates a single cyclic, non-cyclic (zero-time; start / stop non-dimensional instant of a cycle), and linear continuous time [T] from an observer frame of reference for displaying one or more temporal cycles on the user's device. Each independent cycle is consistent with temporal counts of a whole cycle (equated to SI units) displayed as either a discrete geometric shape (spatiotemporal units) and / or algebraic numbers on the device.

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.

Methods and systems are provided for determining navigational information for an entity such as a vehicle using celestial measurements. One method involves determining a Kalman gain based at least in part on inertial measurement data at or before a current point in time associated with the celestial measurement data, determining a celestial measurement error based at least in part on a relationship between the celestial measurement data and a prior estimate for the celestial measurement data, determining a current estimated error associated with the location of the entity based at least in part on a prior estimated error associated with the location, the Kalman gain and the celestial measurement error, and determining an updated estimate of the location of the entity based at least in part on the current estimated error and a prior estimate of the location of the entity.

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.

1. Name of the Design Product: Smart Astronomical Telescope. 2. Use of the Design Product: For celestial observation. 3. Design Key Points of the Design Product: Lies in the shape. 4. Picture or Photograph that Best Illustrates the Design Key Points: Perspective View 1.

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 image processing, particularly relates to a celestial body faint target feature extraction method based on deep learning, and aims to solve the problem that in the prior art, a faint celestial body target is difficult to effectively detect when the celestial body target is detected, so that the detection accuracy is influenced. The method provided by the invention comprises the following steps: acquiring a foundation optical image to be detected; inputting the ground-based optical image into a pre-constructed target neural network to obtain a target feature map output by the target neural network, the target feature map being used for indicating detail information and semantic information of a celestial body faint target in the ground-based optical image; the target neural network comprises a backbone network, a feature extraction module and a feature fusion module. Based on the method provided by the invention, a feature extraction module (Res-MBDA) and a feature fusion module (CAFFM) are adopted to enhance the attention on the information of the faint celestial body target, and the detection rate of the faint celestial body target is effectively improved.

To assist a user in making various decisions and performing operations for highly accurate introduction and tracking of a celestial body, in an astronomical telescope having a rotation drive mechanism for a telescope barrel for automatically capturing a target celestial body within the field of view of the telescope and a control device for controlling the drive mechanism, without connecting a special device to the telescope control device. [Solution] A digital camera 1 that moves in unison with the movement of the telescope T is attached to the telescope, and the telescope is driven by instructions to steer its field of view towards the target coordinates. The camera also captures an image in the direction the telescope is pointed and the image is analysed to identify the pointing coordinates that will actually be introduced into the field of view of the telescope. The error between the target coordinates and the pointing coordinates is calculated, and if the desired pointing accuracy is not achieved, a re-introduction operation to the target coordinates is performed, and the telescope is pointed precisely towards the target coordinates.

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.

Embodiments relate to a high-efficiency, refractive metalens capable of observing celestial bodies such as the moon. The metalens comprises a plurality of nanocylinders spatially arranged on a substrate, wherein the plurality of nanocylinders provide the metalens with an aperture having a diameter of 80 mm. The metalens is fabricated with deep-ultraviolet (DUV) projection stepper lithography, which is commonly used in the semiconductor industry. Embodiments further relate to a multi-level-compensated metalens (MLCM) that can achieve achromatic focusing and imaging across the entire visible light spectrum (e.g., 400 nm to 700 nm). The MLCM includes nanocylinders made of high-refractive-index silicon nitride and a plurality of stairs made of low-dispersion silicon nitride, separated by a spacer layer.

The invention provides a star catalogue data matching method and device, computer equipment and a storage medium. The method comprises the steps of obtaining a plurality of star catalogue files; aiming at each star catalogue file, generating a target table corresponding to the star catalogue file, and storing serial number information of the celestial body data under multiple levels in the target table; constructing a storage calculation table according to the structure information of the target table and a set storage division strategy, and storing the table content of the target table into the storage calculation table; for any two to-be-matched star catalogue files, taking a column where a target hierarchy indicated by the storage division strategy is located as a connection key, carrying out connection operation on storage calculation tables corresponding to the two to-be-matched star catalogue files, and determining a matching result between multiple pieces of celestial body data with the same serial number information of the target hierarchy in the two storage calculation tables; and when the matching result is that matching succeeds, outputting at least part of data in the multiple pieces of celestial body data. According to the method, cross matching of celestial body data in different star catalogue files is realized, and the matching efficiency is improved.

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 invention relates to a lunar soil trace water accurate detection test method under equivalent vacuum and ultralow temperature coupling, and belongs to the technical field of extraterrestrial celestial body sampling detection. Aiming at the technical bottleneck that the existing lunar soil trace water detection technology in the earth environment is interfered by water vapor, the method comprises the following steps: placing lunar soil in a sample cabin in a nuclear magnetic probe; the temperature of the sample cabin is adjusted through liquid nitrogen refrigeration, and the ultralow-temperature lunar environment is simulated; the humidity condition of the sample cabin is adjusted, and lunar soil nuclear magnetic semaphores under different humidity are collected; establishing a relation curve of different humidity and nuclear magnetic signal increments; when the semaphore is different, deducting signal increment caused by environment humidity by taking a nuclear magnetic signal of unit humidity under a steady-state condition as a reference to obtain nuclear magnetic signal data under an equivalent vacuum environment; and inverting the semaphore under the equivalent vacuum to obtain the lunar soil water content. Compared with the prior art, the method has the advantages that the key technical problem in extraterrestrial sample earth environment detection is solved, and an important means is provided for moon water resource detection and sampling return sample analysis.

The invention belongs to the technical field of astronomy, and provides a multi-channel synchronous polarization imager system which is used for a night astronomy observation scene. According to the system, through cooperative work of key components such as a relay optical system, a polarization calibration unit rotating wheel, a broadband optical filter, a zero polarization splitting prism, a super achromatic half-wave plate and a polarization splitting prism, celestial body polarization state synchronous measurement in a full view field is completed through one-time exposure. Wherein the relay optical system is responsible for collimation and imaging functions; the polarization calibration unit rotating wheel is used for polarization calibration; the zero-polarization splitting prism divides an incident light beam into a transmission light beam and a reflection light beam; the super achromatic half-wave plate and the polarization splitting prism are used for polarization modulation. The system solves the problem of dispersion effect during broadband measurement, improves the detection capability of a dark and weak target, and is suitable for high-precision synchronous polarization measurement of a large field of view.

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 provides a target celestial body searching method and device, and relates to the field of celestial body shooting. The target celestial body searching method comprises the following steps: determining equipment control coordinates according to a theoretical position of a target celestial body and an equipment rotation plane position of shooting equipment; wherein the theoretical position comprises a theoretical elevation angle and a theoretical azimuth angle; and based on the equipment control coordinate, controlling the shooting equipment to search the target celestial body. According to the target celestial body searching method provided by the embodiment of the invention, the horizontal zero position and the orientation of the shooting equipment can be calibrated based on the absolute position of the sun, so that the target celestial body can be efficiently and accurately shot. The target celestial body searching device based on the target celestial body shooting method can realize automatic calibration of shooting equipment based on the absolute position of the sun so as to realize high-quality celestial body shooting work.

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.