117 results about "Star chart" patented technology

The invention discloses a star map registration method based on a remote optical image, relates to the technical field of image processing, and solves the problems that the existing method is multi-oriented to a single telescope, most of the single telescope is aligned at a star point level, and the robustness is insufficient when parallax, distortion, optical difference and background pollution exist in remote multi-station imaging. The method comprises the following steps: acquiring a remote star map and extracting a star point centroid; angular distance calculation and triangle construction; registering the centroids of the star points in the whole image; performing similarity transformation and homography estimation; and carrying out sub-pixel refinement and full image registration. According to the invention, dual registration of star point centroids and pixel coordinates can be realized for star maps shot by a plurality of telescopes in different places, and meanwhile, a high-quality registration reference can be provided for subsequent three-dimensional information acquisition of a space target and identification and positioning of the space target.

The invention relates to a thermal power plant fault early warning and diagnosis method based on a nebula system, and the method comprises the steps: collecting the multi-dimensional operation time sequence data of a thermal power plant, carrying out the feature extraction and lexical element processing of the multi-dimensional operation time sequence data through an encoder, and obtaining a unified equipment state lexical element sequence; based on the equipment state lexical element sequence, constructing a dynamic star map representing the operation state of the whole power plant; inputting the dynamic star map into a space-time fusion backbone network; the space-time fusion backbone network performs iterative processing on the dynamic star map and generates a health degree attenuation trajectory; when the slope of the health degree attenuation trajectory exceeds a preset threshold value, dynamic early warning and system diagnosis are triggered, and a natural language diagnosis report containing a causal reasoning chain is generated; new multi-dimensional operation time sequence data are collected in real time, and an incremental learning algorithm is used to update the encoder and the space-time fusion backbone network online; compared with the prior art, the system can continuously adapt to working condition changes and has high self-optimization capacity.

The invention relates to a star map stray light processing method based on multidirectional gradient, belongs to the technical field of space situation awareness, and solves the technical problems of low processing speed and inaccurate target edge information processing when the existing method is used for processing stray light under a complex illumination condition. Comprising the following steps: performing multidirectional gradient calculation on each pixel point of an original star map image containing stray light to obtain a multidirectional gradient value of each pixel point, and performing normalization processing to obtain a normalized gradient image; carrying out adaptive threshold segmentation on the normalized gradient image to obtain a binary image; performing morphological closed operation on the binarized image to obtain a contour image after the closed operation; and carrying out contour filling on the contour image after the closed operation, and carrying out mask processing to obtain a pure star map image with a reserved target area. The influence of strong stray light on target detection is effectively eliminated, and the precision and robustness of star map image target positioning are improved.

The invention discloses a star point coordinate extraction and star sensor attitude optimization method based on deep learning. The whole process of pseudo star map generation, star point coordinate extraction and attitude calculation is optimized. Multi-factor interference such as spacecraft jitter and optical distortion is simulated through dynamic star point modeling, and a high-fidelity pseudo star map is generated; a noise adaptive detection network is designed to fuse denoising and key point detection, and star point positioning precision in a low signal-to-noise ratio environment is improved; and optimizing attitude solution, constructing a loss function based on star point coordinates, and performing back propagation to optimize attitude parameters to realize an algorithm closed loop. According to the method, real data can be expanded to realize effective training of the model, and the positioning precision is improved; the star point coordinate positioning precision is improved to a sub-pixel level (RMSElt; 0.3 pixel); an end-to-end optimization framework reduces error accumulation in a traditional assembly line, and the robustness of the system is improved by 40%.

The embodiment of the invention discloses an all-day and all-world time measurement method and device. A specific embodiment of the method comprises the following steps: constructing a short-wave infrared astronomical survey star catalogue; constructing a short-wave infrared astronomical geodetic survey star database according to the short-wave infrared astronomical survey star catalogue; optimizing the short-wave infrared astronomical geodetic survey star library to obtain an optimized short-wave infrared astronomical geodetic survey star library, and correcting atmospheric refraction errors in the optimized short-wave infrared astronomical geodetic survey star library; carrying out all-day fixed star point coordinate extraction on the shot multi-frame daytime star map to obtain fixed star point coordinates; and according to the star point coordinates of the fixed star, carrying out all-day astronomical observation world time calculation on the observation fixed star to obtain all-day world time. According to the embodiment, unified comparison of multi-period monitoring data is realized, and the engineering practicability of a monitoring result is improved.

The invention discloses a star sensor rapid tracking method based on dynamic window blind restoration, and belongs to the field of star sensor algorithms. The method comprises the following steps: estimating a coordinate estimation value of each star in an overlapped view field on a star map at the next moment through a historical star map, and extracting a local window image of a star point corresponding to each star in the overlapped view field; gaussian filtering, top-hat transformation and connected domain processing are carried out on the local window image, star point trailing information is extracted based on a Zernike moment sub-pixel edge extraction method, and a star point area is restored by using a Richardson-Lucy algorithm; then, star point centroids are extracted from the restored image, star points which are tracked successfully are screened out in combination with motion consistency, and initial attitude parameters are calculated through a QUEST method; and finally fusing the star point information newly entering the field of view to obtain attitude parameters of the star sensor under the reference coordinate system. According to the method, the image traversal range is greatly reduced, and the method has important engineering significance.

The invention provides an inertial navigation aided navigation positioning method and system, and the method comprises the steps: calculating the coordinate of each navigation satellite in an ECEF coordinate system according to the satellite ephemeris of a satellite navigation system; according to the navigation satellite coordinate and the inertial navigation system positioning result, the azimuth angle and the pitch angle of the navigation satellite relative to the optical detection equipment under the ENU coordinate system are solved, and the navigation satellite is tracked; acquiring star maps collected by the optical detection equipment, matching the star maps through a star map recognition algorithm, resolving a coordinate transformation matrix between two continuous frames of star maps, and recognizing fixed stars and satellites in the star maps based on the transformation matrix; converting the identified fixed star in the field of view into an ECEF coordinate system, calculating an observation angular distance between the fixed star and the satellite, and calculating a satellite observation vector in the ECEF coordinate system according to the observation angular distance; and performing error correction on the positioning result of the inertial navigation system based on the satellite observation vector. Through the scheme, the positioning precision of the inertial navigation system can be improved, and the influence of interference deception signals is reduced.

The invention discloses a star sensor fixed star detection capability analysis method based on a polarization degree image, and belongs to the technical field of star sensor detection. In order to solve the problems of few detection means and low utilization rate of sky light radiation information during star observation of a near-earth space all-time star sensor, the method comprises the following steps: constructing a star sensor integrated with a focal plane micro-polarizer array, and acquiring four gray star maps through short exposure by using the star sensor integrated with the focal plane micro-polarizer array; a star sky Stokes vector diagram is calculated; calculating star sky polarization degree distribution to obtain a polarization degree star map; constructing a fixed star polarization signal-to-noise ratio calculation formula in the polarization degree star map by utilizing a physical process of converting radiation energy into polarization degree; the calculation formula calculates the polarization signal-to-noise ratio of the fixed star in the field of view; and comparing the polarization signal-to-noise ratio of the fixed star with a signal-to-noise ratio threshold value detected by the near-earth space all-time star sensor, and judging the detectable capability of the fixed star in the polarization degree star map. According to the method, the robustness of the near-earth space all-day star-sensitive technology to a complex environment is improved.

The invention relates to the technical field of camera on-orbit calibration, in particular to a fisheye camera on-orbit calibration method based on a starlight vector, which comprises the following steps of: S1, acquiring a plurality of star maps observed by a fisheye camera on orbit, and extracting and denoising star points to form a star point set; s2, according to fisheye imaging distortion distribution, a star point located in an imaging center area is selected from a star point set, and a starlight vector is constructed based on image point coordinates of the star point in combination with star catalogue data subjected to space-time deviation and propagation path deviation correction; and S3, performing local geometrical relationship star point matching on the starlight vector in the step S2. According to the method, the multiple star maps observed by the fisheye camera in orbit are obtained and processed to form the star point set, so that the problems of poor in-orbit calibration applicability and low precision caused by the fact that most traditional fisheye camera calibration methods adopt a ground pre-calibration or space reference object arrangement mode are solved.

The invention discloses a star point motion parameter estimation method for a high-dynamic star sensor. The method specifically comprises the following steps: (1) acquiring a star map under a dynamic condition through a fixed star sensor; (2) carrying out filtering preprocessing on the fixed star sensor image obtained in the step (1); (3) carrying out threshold segmentation on the image processed in the step (2) and carrying out connected domain extraction to obtain rough star points; (4) selecting the brightest star point in the star points obtained in the step (3); (5) obtaining a sub-pixel star point track by using the brightest star point adjacent area obtained in the step (4) and adopting a Zernike moment sub-pixel edge extraction method; and (6) utilizing the sub-pixel star point trajectory obtained in the step (5), and adopting least square fitting to obtain star point motion parameters. The method has the beneficial effects that the precision of star point trailing length and angle estimation is improved, so that the extraction precision of star points in a dynamic environment is improved, and the precision of a fixed star sensor is improved.

The invention discloses a fixed star detection capability improving method fusing energy and polarization information, and belongs to the technical field of star sensor detection. In order to solve the problem that a near-earth space all-day star sensor is insufficient in fixed star detection capability in a strong atmospheric background stray light interference environment, the method comprises the following steps: exposing the sky once by using a star sensor integrated with a focal plane micro-polarizer array to obtain four gray star maps; calculating a polarization degree calculation value to obtain a polarization degree star map, and determining the sky background polarization degree; setting a polarization degree segmentation threshold value; performing threshold segmentation on the polarization degree star map to obtain a polarization degree star map segmentation result; determining a weight coefficient according to the radiation energy ratio of the fixed star to the sky background; and comparing the sky background polarization degrees, and performing weighting processing on the gray star map or the accumulated star map with the highest signal-to-noise ratio based on different conditions to obtain a final processed high-signal-to-noise-ratio star map. According to the invention, the fixed star detection capability is effectively improved.

A space-based optical space target detection method fusing track information comprises the following steps: acquiring an image spot position of a point target in a star map of a current position by using a space-based optical camera, and determining a candidate target set according to different motion characteristics of a fixed star and a space target; determining the center-of-mass coordinate and pixel range of the candidate target under the image plane coordinate system according to the orientation of the optical camera, converting the center-of-mass coordinate and pixel range into the sight angle and range under the satellite body coordinate system, carrying out inter-frame trajectory association on the obtained star map sequence, updating the space target library according to trajectory information, and outputting a space target detection result. And repeating the steps to traverse all star maps.

The invention relates to the technical field of space target detection, and discloses a target detection method and device, computer equipment and a readable storage medium. The method comprises the following steps: acquiring a plurality of frames of star maps to be detected, and extracting star images in each frame of star map to obtain pixel information of the plurality of star images; obtaining a plurality of star map sequences and motion parameters of stars corresponding to the star images; determining a projection frame serial number value by using the pixel information and the motion parameters of the plurality of star images; performing projection processing on the multi-segment star map sequence by using the projection frame serial number value to obtain multiple projection frames; according to the method, the multiple projection frames are subjected to centroid neighborhood matching, the target star image is obtained, the target star image is accurately detected in the process, the GEO target detection rate is increased, and the error detection rate is reduced.

The application provides a spacecraft autonomous navigation method and electronic equipment. The spacecraft autonomous navigation method comprises the following steps: determining technical indexes of an optical sensor according to navigation requirements, and determining a configuration of the optical sensor according to orbit information of the spacecraft; collecting a star map by using the optical sensor with the determined technical indexes and configuration, processing the star map, identifying a refraction star and extracting a refraction angle; and using a Kalman filtering algorithm to perform information fusion on information output by an inertial navigation system and a refraction apparent height calculated based on the refraction angle, so as to correct navigation errors and obtain corrected navigation information. The application corrects drift errors of the inertial navigation by astronomical navigation, maintains continuous navigation information by using the inertial navigation when the astronomical system is unavailable, and achieves the purpose of improving navigation accuracy.

The invention discloses an indoor positioning and attitude determination method based on pseudo star map recognition. The method comprises the following steps: designing a pseudo star array meeting a cross ratio constraint condition based on a three-dimensional topological layout; accurately calibrating the position of each pseudo star, calculating the cross-ratio of collinear adjacent four-point pseudo stars, and generating a global pseudo star cross-ratio feature library; collecting a scene image containing a pseudo star in real time, and extracting a sub-pixel-level light spot center coordinate to form a feature point set of each view field; a collinear point group is screened out from the feature point set, and then specific collinear point chains are extracted to form a collinear point chain set; calculating a cross-ratio invariant for the longest collinear point chain based on a cross-ratio invariance principle, and constructing a local pseudo-star cross-ratio sub-library through matching with a global pseudo-star cross-ratio feature library; carrying out cross-ratio calculation on other collinear point chains and matching local pseudo-star cross-ratio sub-libraries to establish a corresponding relation; and resolving an initial pose value, constructing a joint optimization model fusing a re-projection error and a cross-ratio constraint, and iteratively optimizing and outputting a high-precision six-degree-of-freedom pose result. The invention further discloses a corresponding system, electronic equipment and a computer readable storage medium.

The invention discloses an embedded star catalogue data storage and query method oriented to a bare computer environment, relates to the technical field of embedded data query processing, solves the problem of mismatch between a DSP system structure and a star map query task in the prior art, and comprises the steps of star block storage, star block query, primary selection of star blocks in star block query and determination of navigation stars. In the star block storage, the GeoHash coding technology is adopted to take the star block as a primary key value, and a B + tree is adopted to store the star block in an easy-to-search form; a star map shot by an astronomical camera is preliminarily decomposed into primarily-selected star blocks in a partition mode, then corresponding storage star blocks in a bare computer environment are inquired respectively, and high flexibility and adaptability are achieved. The method is compatible with the GeoHash coding technology, parallel computing of a multi-core bare computer is facilitated, and the query speed can be doubled.

The application discloses a wireless multi-astronomical telescope control system based on an ASCOM communication protocol and belongs to the field of system control. The overall application is divided into three parts, namely, an ASCOM (astronomy common object model) standardization module, a server and a client. An ordinary user selects corresponding stars to control a telescope through the client, and a manager uses a server control software running on a PC to configure the telescope numbers controllable by the client and continuously receives control commands sent by the client, and sends control commands to star map software to move a corresponding group of telescopes to the selected stars.

The present application relates to a kind of astronomical image background extraction method and system, mainly for the processing of starry sky background in space small target detection process;Extraction method includes the following steps: S1, according to the gray characteristic of the astronomical image to be processed, the size of the largest star in astronomical image is detected, to set the window length of one-dimensional median filtering;S2, the background of astronomical image is extracted using the method of bidirectional one-dimensional median filtering, to obtain the image after background correction;S3, the background of the image after background correction is extracted using adaptive interframe difference method.The part outside target area is regarded as the background of astronomical image in the present application, and the effect of suppressing complex background interference in star map and filtering background star can be achieved by extracting and subtracting the background of astronomical image, which creates favorable conditions for subsequent detection of space small target.

The invention provides a spacecraft autonomous navigation method and electronic equipment. The autonomous navigation method for the spacecraft comprises the following steps: determining a technical index of an optical sensor according to a navigation requirement, and determining a configuration of the optical sensor according to orbit information of the spacecraft; acquiring a star map by using an optical sensor with determined technical indexes and configuration, processing the star map, identifying a refraction star and extracting a refraction angle; and carrying out information fusion on the information output by the inertial navigation system and the refraction apparent height calculated based on the refraction angle by using a Kalman filtering algorithm so as to correct the navigation error and obtain the corrected navigation information. The drifting error of the inertial navigation is corrected through the astronomical navigation, and the navigation information is kept continuous through the inertial navigation when the astronomical system is unavailable, so that the purpose of improving the navigation precision is achieved.

The invention belongs to the technical field of astronomical image data processing, particularly relates to an astronomical image data set labeling method, and aims to solve the problem that existing single threshold segmentation-based labeling and star map projection-based labeling are difficult to meet the requirement of a depth model for a high-quality data set. According to the method, on the basis of threshold segmentation labeling and star map projection labeling, a first labeling result and a difference set are adopted as a labeling result A for an observation image large-probability detectable target, a second labeling result is adopted as a labeling result B for an observation image small-probability detectable target, and the labeling result A and the labeling result B are integrated to obtain a labeling result A and a labeling result B; and obtaining a final labeling result. According to the method, the integrity of target labeling can be improved, the probability of missing labeling and wrong labeling can be reduced, the actual fitting degree of the labeling result and the image can be met, unification of integrity and accuracy is achieved, and the depth model performance can be improved through the manufactured data set.

A celestial exploration support program is disclosed. The program can execute, on a computing device, a hopping-path providing function that generates and provides to a user a hopping-path image in which hopping information including a hopping direction and an angular distance from a guiding star to a specific celestial object is reflected on a basic star chart image.

1. The name of the design product: console (star map). 2. The use of the design product: the design product is used for the console of the control center operator's office and the operation of the control equipment. 3. The design points of the design product: the combination of shape and pattern. 4. The picture or photo that best indicates the design points: design 1 perspective view. 5. The bottom of the design product is not easy to see or not visible during use, omitting design 1, design 2, design 3, design 4, design 4. 6. Design 1 is designated as the basic design.

The invention discloses an autonomous pose estimation system of a spacecraft by utilizing earth-moon-star recognition, and relates to the technical field of optical autonomous navigation.The method comprises the steps that an earth-moon image is obtained through an optical navigation camera, image quality is improved by utilizing SwinIR super-resolution reconstruction, star point information is extracted by combining star map matching and an SIFT algorithm, and the attitude of the spacecraft is estimated. And estimating the attitude of the spacecraft relative to the ECI system by adopting a QUEST method. And further extracting earth-moon centroid coordinates and vectors, calculating an azimuth angle and a pitch angle in combination with attitude information, and determining the position of the spacecraft. And finally, fusing angle measurement information and position data based on extended Kalman filtering to realize high-precision pose estimation of the spacecraft. According to the method, more reliable pose information is provided for navigation control of the spacecraft, and the autonomous navigation capability and task execution precision of the spacecraft can be improved.

The invention discloses a grid star map identification method and system based on weighted voting and geometric verification, and the method specifically comprises the steps: firstly, constructing a feature mode database containing all-day navigation stars, and storing the rasterized geometric mode of an adjacent star sky region of each navigation star and the inverse document frequency (IDF) weight of each grid unit in the database; secondly, extracting a plurality of brightest observation stars as main stars from an observation star map obtained by a star map sensor, and generating an observation geometric mode for each main star; inquiring an offline database by utilizing an observation mode, generating a candidate navigation star list, dynamically filtering low-credibility candidate stars through an adaptive threshold strategy, and sorting the candidate stars by adopting a mixed scoring function; and finally, carrying out pose consistency check on the plurality of candidate stars with the highest scores through a geometric verification method, and identifying the most reliable matching result. On the premise of ensuring the real-time performance, the grid star map recognition robustness and accuracy under various noises and interferences are improved.

The present application relates to the technical field of altazimuth telescope, in particular to a pointing model calibration method of altazimuth telescope, the error function of the telescope is obtained by two-dimensional surface fitting, the star image is shot every 10 degrees or so in the azimuth and elevation directions, the right ascension and declination of the image center are obtained by comparing with the standard star map, the right ascension and declination are converted into the real azimuth and real elevation in the geodetic horizontal coordinate according to the shooting time, the geographical longitude and latitude of the telescope, the altitude, the air temperature and air pressure; the real azimuth and real elevation are subtracted by the azimuth and elevation read by the angle sensor of the telescope respectively, the azimuth error matrix and the elevation error matrix are obtained respectively; the error matrix is fitted to obtain the azimuth error function, the real azimuth and real elevation of any target are subtracted by the azimuth pointing error and the elevation pointing error respectively, and the accurate pointing of the telescope can be obtained.

The application discloses a method for improving star detection capability by fusing energy and polarization information, and belongs to the technical field of star sensor detection. In order to solve the problem of insufficient star detection capability of a near-earth space all-time star sensor in a strong atmospheric background light interference environment, the star sensor integrated with a micro-polarization plate array is used to obtain four gray star images through one-time exposure of the sky; a polarization degree calculation value is calculated to obtain a polarization degree star image and determine a sky background polarization degree; a polarization degree segmentation threshold is set; the polarization degree star image is subjected to threshold segmentation to obtain a polarization degree star image segmentation result; a weight coefficient is determined according to the ratio of the radiant energy of the star and the sky background; the sky background polarization degree is compared, and the gray star image or the accumulated star image with the highest signal-to-noise ratio is subjected to weighted processing based on different conditions to obtain a final high signal-to-noise ratio star image after processing. The star detection capability is effectively improved.

The invention relates to a real-time global backlight detection simulation device for a moving target in a space star map, relates to the technical field of spaceflight detection simulation, and solves the technical problem that a detection system with strong backlight interference resistance needs to be researched and developed urgently in the prior art. The device comprises an inertial space detection multi-degree-of-freedom simulation rotary table, a star point light three-in-one multi-degree-of-freedom simulation rotary table, a multi-angle mapping projection fusion optical system, a tunable strong light projector, a global real-time multi-stage star map generator, a high-speed multi-scale moving target generation unit and a control unit. And a global imaging system is arranged on the inertial space detection multi-degree-of-freedom simulation turntable. According to the real-time global backlight detection simulation device for the moving target in the space star map, the detection scene of the moving target in the space star map in a backlight environment can be truly simulated through cooperative work of all the components.

The invention relates to the technical field of integrated navigation, in particular to a positioning method and system based on optical angle measurement and astronomical-inertial integrated navigation. According to the method, firstly, a star image and a navigational satellite image are obtained at the same time by shooting a star map, after recognition and processing, the attitude of a camera relative to a geocentric inertial coordinate system is calculated by utilizing the star, and then the coordinate of the navigational satellite in the coordinate system is determined. And obtaining angle information of the navigation satellite relative to the observer under the earth coordinate system through coordinate transformation. Optical angle measurement information is fused with attitude, speed and position information output by an inertial navigation system, a Kalman filtering state equation and an observation equation are constructed, and finally real-time high-precision calculation and updating of the position of the observer are achieved. According to the method, the accuracy of optical angle measurement, the limited distance reference of celestial navigation and the autonomous continuity of inertial navigation are fused, and the navigation positioning accuracy and reliability under the complex environment and the satellite denial condition are effectively improved.

The star map compression method based on target detection belongs to the field of image processing, and solves the problems of low target detection accuracy, and the difficulty in balancing the image compression efficiency and the local detail preservation of the existing star map coding method. The method comprises the following steps: dividing the star map into a plurality of sub-images with the same pixel size as a primary coding unit; using the maximum inter-class variance method to perform adaptive threshold target detection on the plurality of primary coding units; simultaneously counting the number of pixel points in the eight neighborhoods around the detection points which are divided into target regions and background regions; refining the coding unit according to the adaptive threshold target detection result; and using the adaptive quantization parameter method to perform compression coding on the refined coding unit. Through the adaptive threshold target detection, the detection accuracy is improved; under the same compression rate, the local detail preservation effect of the image coded and decoded by the method is better, and the peak signal-to-noise ratio is higher.

This invention discloses a star map matching method based on the statistical features of star pairs, comprising the following steps: constructing star pairs; searching for similar stars from an image star pair list and a star catalog star pair list; determining the rotation angles of the image and the star catalog; initially determining matching parameters; and precisely determining the matching parameters. This invention's method can achieve a relatively high correct matching rate even with star position errors, false star images, missing star images, and high-density star fields.