16 results about "Star position" patented technology

The application discloses a target initial orbit determination method and device based on spatial filtering velocity measurement, which comprises the following steps: acquiring a star position image; determining an observation target according to the star position image, and establishing a mapping relationship between a measurement coordinate and an angle position of the observation target; modulating the star position image to obtain a distribution signal of target brightness of the observation target changing with time; acquiring a velocity of the observation target according to the distribution signal of the target brightness changing with time; obtaining an angular velocity and an acceleration of the observation target according to the velocity of the observation target through the mapping relationship between the measurement coordinate and the angle position of the observation target; and obtaining a position vector and an initial orbit velocity of the observation target relative to the earth center through an initial orbit determination algorithm. Compared with a traditional initial orbit determination method, the application directly measures the angular velocity of the target, reduces the coupling between the angle position error and the angular motion quantity, improves the initial orbit determination precision of the target under the observation error condition, and realizes the rapid orbit determination of the target.

An inter-satellite pointing target attitude high-precision real-time online prediction method, first, the ground uses the orbit determination program corrected by on-orbit data observation to generate a double-satellite orbit position and velocity value sequence in a predetermined time period, and samples according to the control period, then for each sampling time, the double-satellite orbit position and velocity is used to establish the local orbit coordinate system, and the component of the target star position vector in the local orbit coordinate system is calculated, the pitch and yaw target attitude angle values are calculated according to the target attitude angle definition, the pitch target angle sequence is linearly averaged and estimated, the average orbit period value and the long-term change rate parameter are calculated, and the modified sequence after deducting the long-term change rate is given, for the pitch target angle correction sequence and the yaw target angle sequence, data of a specified average orbit period number is taken from a specified initial time, the fitting coefficient is calculated, finally the generated fitting coefficient is uploaded to the satellite, and the satellite uses the high-precision fitting determination formula to calculate the inter-satellite pointing target attitude angle online every control period.

To reduce the memory access frequency and the calculation time in star position calculation in comparison to a conventional technique.SOLUTION: A star tracker outputs an image by imaging a star with imaging means, searches for a peak pixel having a higher luminance value than a luminance value of an adjacent pixel in the plurality of pixels constituting the image, decides an extraction range for cutting out a partial image including a peak pixel from the image, and calculates a star position based on the luminance value of the plurality of pixels constituting the partial image. Here, the extraction range is decided such that noise included in the partial image is reduced on the basis of at least one of the luminance value of the peak pixel, the position of the peak pixel in the image and a parameter correlated to the temperature of the imaging means.SELECTED DRAWING: Figure 1

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.

The application discloses a star-inertial integrated outfield dynamic calibration method based on a refracting surface constraint mechanism, and relates to the technical field of calibration methods, and specifically discloses the following technical scheme: a relationship model of an observed star position and a zenith direction is established based on a refracting surface constraint mechanism and observation imaging of a star, a first zenith direction measurement model under a star sensor system corresponding to an observation time and an observation position is established based on the relationship model; a second zenith direction measurement model under an inertial navigation system of the zenith direction of a current observation position is established through a filter combination model based on real-time measurement values of angular velocity and angular acceleration of the inertial navigation system; a zenith direction integrated conversion matrix model between the inertial navigation system and the star sensor system is established by simultaneously solving the first zenith direction measurement model under the star sensor coordinate system and the second zenith direction measurement model under the inertial navigation system; and a star-inertial integrated outfield optimization calibration model is established by changing the longitude and latitude of the observation position and the observation direction for multiple times, so that star-inertial integrated outfield calibration is carried out.

The star map recognition method based on radial features and interstellar angular distance relates to the field of star map recognition in astronomical navigation, solves the problems that the existing star map recognition algorithm has less number of stars to be recognized at one time, and the recognition speed and robustness are difficult to be compatible, and the method comprises the following steps: a navigation star table is made, radial recognition feature library and interstellar position relationship library are constructed according to the position distribution features of each navigation star and surrounding near neighbor stars; the interstellar position relationship library is used for storing the star number and radial ring number of the surrounding near neighbor stars of each navigation star; then, initial recognition and accurate recognition are carried out. In the process of matching by using the radial feature library, an angular distance error tolerance is set, and a weight value is set for each ring number, so that the star position noise has strong robustness. After the initial recognition, the accurate recognition is carried out, the surrounding near neighbor stars of the main star are used, and the method has strong robustness to false star noise and missing stars. The method realizes the recognition of multiple stars at one time, and improves the initial attitude solution accuracy.

The embodiment of the invention discloses an all-time star point extraction method, device and equipment considering the influence of atmospheric turbulence. A specific embodiment of the method comprises the following steps: determining a star sensor main shaft initial direction according to a star sensor installation matrix; according to the initial orientation of the star sensor, the view field of the star sensor and the calibration parameters of the star sensor, fixed star position information is determined, and the fixed star position information is the position of the corresponding fixed star in the image plane; according to the fixed star position information, a star map frame sequence containing a preset frame number is collected, and each star map frame in the star map frame sequence corresponds to collection time; selecting each star map frame of a preset candidate frame number from the star map frame sequence as each star point frame to be extracted; and according to the to-be-extracted frame of each star point, determining the centroid position of the fixed star. According to the embodiment, all-day astronomical attitude determination and positioning requirements can be met, and the extraction accuracy of the mass center position of the star point is improved.

This invention relates to a computer-implemented method of generating an article of manufacture. The method comprises the steps of receiving date and location data relating to a user event and thereafter accessing a star catalogue, determining the position of the stars relative to the date and location data, and projecting the star positions onto a two-dimensional (2D) plane. Once the star positions have been projected onto a 2D plane, the method comprises the steps of generating a computer-readable file for the star positions, providing the file to a laser engraving machine, and the laser-engraving machine engraving the article of manufacture according to the computer-readable file. The article of manufacture is preferably an item of jewellery such as a pendant. The method provides an efficient and cost-effective way of manufacturing a bespoke, high value item.

The utility model provides a frame star sundial, which comprises a positioning disc, a time disc, a solar term disc and a time pointer, and is characterized in that the positioning disc, the time disc and the solar term disc are coaxially mounted on a middle shaft and can be fixed mutually; the center shaft is installed on the base stand column and can be fixed to any direction and angle. A gap penetrating through the upper surface and the lower surface is formed in the positioning disc, and an observer observes a star from the lower surface of the positioning disc through the gap; a sharp corner is carved on the positioning disc and is used for aligning to the geographical longitude of an observation place; four layers of scale rings are arranged on the upper surface of the solar term disc, and the outermost layer is December 365 throughout the year; the second outer layer is an identifier of 24 solar terms in a corresponding month in the whole year; the inner layer is corresponding identification of twelve star times; the innermost layer is geographic longitude; the upper surface of the hour disc is provided with three layers of scale rings which are 24 hours, 12 hours and a triangular indicator in sequence. The Beijing time can be directly read through on-site star position observation across the country.

The invention belongs to the technical field of astronomical telescopes, and particularly relates to a quick calibration method and system for a double-horizontal telescope rack. The method comprises the following steps: S1, establishing a coordinate model, and determining observation coordinates and a mark star position; s2, performing azimuth angle deviation calibration according to the observation coordinates obtained in the S1 and the position of the mark star to obtain a calibration state in which the azimuth angle deviation is eliminated; s3, performing pitch angle deviation calibration and corresponding offset calculation according to the calibration state in which the azimuth angle deviation obtained in the step S2 is eliminated; s4, establishing a deviation correction curve through simulation according to the pitch angle deviation data obtained in the S3, and optimizing the pitch angle deviation by using a K value adjustment method to obtain an optimized pitch angle deviation calibration result; and S5, according to a pitch angle deviation optimization result completed in the step S4, performing experimental verification and obtaining a conclusion. The method has the advantages that efficient calibration of the azimuth angle and pitch angle deviation of the rack can be guaranteed, and therefore the pointing precision of the telescope is remarkably improved.

The invention provides a high-altitude aircraft integrated navigation method based on Fourier domain computational imaging, and relates to the technical field of aircraft positioning and navigation.The method comprises the steps that S1, a navigation coordinate system of a high-altitude aircraft is set, and an astronomy and inertia integrated navigation model is established; s2, establishing an image-free target positioning model based on Fourier single-pixel detection, and realizing large-field-of-view celestial navigation star positioning of a high-altitude aircraft; s3, analyzing the celestial navigation star map to realize celestial navigation attitude determination of the high-altitude aircraft; s4, basic parameters in the navigation process are set, and astronomical and inertial integrated navigation based on Fourier domain calculation imaging is achieved. According to the invention, the fluctuation of the light field is modulated at high frequency through the digital micromirror device, the astronomical navigation attitude determination is carried out by utilizing the relevance between the detection light field and the modulation light field on the premise of not reconstructing the total image information, the updating frequency of the large-view-field astronomical navigation information is improved to more than 20Hz, and the integrated navigation positioning precision is improved under the astronomical and inertial navigation framework.

The application discloses a kind of all-weather navigation method and device of cross light field micro-nano composite perception, method includes: based on biological compound eye perception navigation mechanism constructs cross light field composite defocus imaging perception system;System includes imaging coupling depolarization channel and optical defocus subsystem;In night clear scene, based on cross light field composite defocus imaging perception system to star image is obtained to imaging star map based on constant star imaging;Carrying out constant star target extraction and micro-nano polarization imaging error compensation;Star map identification and attitude solution are carried out to the constant star position vector after compensation;In daytime, in the morning, in the evening clear scene, based on cross light field composite defocus imaging perception system to the sun polarized light field carries out depolarization perception and obtains defocus polarization distribution mode, polarization defocus information is compensated and the sun vector is obtained using optimization method;Based on the sun vector obtains heading information, also discloses corresponding system, electronic equipment and computer readable storage medium.

The application provides a multi-level master star selection method and system in a large-scale constellation communication and cooperative coupling scene, and the method comprises the following steps: in the process of cooperative observation task, for the known N-point area master star position, the distance between the area master star position and the target position is solved, and the minimum value of the distance is determined to determine the task master star; based on the determined task master star, any satellite with the minimum communication hop number between the task master star is selected as the area master star in the corresponding task area; based on the selected area master star and the observation resource allocation set related to the task area in the cooperative observation task planning scheme, any satellite with the minimum communication hop number with the area master star in the allocation set is selected as the cooperative observation data fusion master star, and the multi-level master star selection is completed. The application can effectively improve the master star selection efficiency in the normal mode and the task mode of the large-scale constellation for cooperative observation task, and reduce the total communication hop number of the task related satellites.

The application discloses a star map recognition method based on a fuzzy neural network, which comprises the following steps: 1. screening navigation stars, a screening method for voting the navigation stars by using random visual axes is designed, and a navigation star library uniformly distributed in the whole sky is established; 2. the star closest to the center of a field of view is taken as a main star, a navigation star feature subgraph based on a minimum spanning tree mode is constructed by taking the main star as a root node and the angular distance between stars as the weight of an edge, and the navigation star feature subgraph has scale invariance and rotation invariance; 3. random noise is added to a feature vector to generate a training set; 4. a neural network is constructed and trained; 5. star map recognition is performed, and the binary number of the feature subgraph is output. Compared with the traditional star map recognition method, the star map recognition method based on the fuzzy neural network has high recognition accuracy and fast recognition speed, and has good robustness to star position noise, star loss and pseudo stars by using fuzzy rules for network learning and adjustment.

An inter-satellite pointing target attitude high-precision real-time online prediction method comprises the steps that firstly, an orbit determination program obtained after on-orbit data observation and correction is used on the ground to generate a double-satellite orbit position and speed value sequence in a preset time period, sampling is carried out according to a control period, then a satellite orbit coordinate system is established through the double-satellite orbit position and speed at each sampling moment, and the orbit position and speed value sequence is obtained; calculating a component of a target satellite position vector in an orbital coordinate system of the satellite, calculating a pitching and yawing target attitude angle value according to a target attitude angle definition, performing linear average estimation on a pitching target angle sequence, calculating an average orbital period value and a long-term change rate parameter, and giving a correction sequence after deducting a long-term change rate; and for the pitching target angle correction sequence and the yaw target angle sequence, data of a specified average orbital period number is taken from a specified initial moment, a fitting coefficient is calculated, finally, the generated fitting coefficient is uploaded to a satellite, and a high-precision fitting determination formula is used for calculating the inter-satellite pointing target attitude angle on line in each control period of the satellite.

The invention provides a star orbit effect rendering method and device and electronic equipment. The method comprises the following steps: acquiring an initial star position in a UV space of a target model; rendering the target model based on the initial star position to obtain a star effect; in response to a star orbit effect generation instruction, controlling the initial star position to move in the UV space to obtain a moving star position; and rendering the target model based on the initial star body position and the mobile star body position to obtain a star orbit effect. In the mode, the position of the star body effect in the UV space is moved, so that the star orbit effect is obtained through rendering, sampling mapping is not needed, the rendering performance is improved, and then the fluency of a rendered picture is improved.