9 results about "Star position" patented technology

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 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 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 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 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.