Identification method for triangular star atlas based on characteristic of inertia ratio

The invention discloses a method for identifying a triangular star map, and belongs to the field of navigation, guidance and control of spacecraft The method comprises the following steps of: 1, establishing a navigation database, namely constructing characteristic triangles, calculating a plane unit normal vector, solving an optimal projection principal axis and projection point values, and normalizing magnitude; 2, forming an observation triangle; and 3, searching a characteristic triangle which is most matched with the observation triangle from the navigation database, sequentially retrieving a projection point value block index stable, a characteristic triangle table and a magnitude normalizing table in a hierarchical retrieval mode, and finishing the matching of the observation triangle The method for identifying the triangular star map solves the problems of low noise robustness, more redundant matching and low identification rate of the conventional method for identifying the triangular star map, obviously improves the search speed of the navigation database, reduces redundant matching, improves the identification rate, and has higher noise robustness

Method for identifying triangular star map

The invention provides a rapid, high-robustness and autonomous fixed star identification method, which comprises the following steps: firstly, finding a navigation star pair with a highest matching frequency from all observed star pairs to generate a matching matrix; secondly, confirming the matching relation between every two matching pairs in the matching matrix to generate a matching confirmation matrix; finally, calculating a maximum matching group according to the matching confirmation matrix to obtain an identification result. The method of the invention has the advantages of high identification speed, good robustness, high identification probability, low mis-identification rate, low algorithm realization cost, and high identification error tolerance rate.

Rapid, high-robustness and autonomous fixed star identification method

Method for identifying long-distance space motion target based on stellar map matching

The invention relates to a combined defining method for the carrier attitude of a double-star sensor, and belongs to the field of celestial navigation. The method comprises the following steps: firstly, in an astronomical refraction correction method based on the star reference vectors for a star sensor, realizing the correction of astronomical refraction by amending the star reference vectors; secondly, in a ship body attitude determination method based on the star observation vectors of a combined double-star sensor, combining the observation vectors of each recognizable star of the double-star sensor in two fields into an observation vector matrix, and finally completing ship body attitude resolving with a corresponding star reference vector matrix. On the basis of simplifying the astronomical refraction correcting algorithm of the star sensor, the capability of obtaining the ship body attitude of the double-star sensor is improved at the same time. The main contents refer to the two aspects of the astronomical refraction correction method based on the star reference vectors and the ship body attitude determination method based on the star observation vectors of the combined double-star sensor.

Combined defining method for carrier attitude of double-star sensor

The invention relates to a fast triangle star atlas identification method in astronomy navigation technology field, which includes steps: 1. using star angular distance as a main identification characteristic, using relative magnitude difference of two stars as a auxiliary identification characteristic to determine star atlas identification characteristic quantity, using the star angular distance between two stars, the relative magnitude difference and star number of the two stars composing the star pair as storage basic element, hypothesizing star sensor view field diagonal distance to be d, storing all basic elements with diagonal distance less than or equal to d, constructing a navigation star database and storing the same; 2. extracting observed stars in a observation star atlas, ordering the star from light to dark according to brightness, constructing a observation triangle to be identified; 3. performing triangle identification by utilizing the method; and 4. verifying. The method realizes fast identification of star triangle in the observation star atlas, has advantages of small amount of calculation, stronger fault tolerance capability, faster identification time and navigation database with smaller capacity, and reduces storage pressure of redundant data to hardware system.

Rapid triangle star map recognition method

The invention relates to a multifunctional intelligent image conversion system, which relates to the field of the video image processing. A first conversion chip in the system is used for decoding the data of a camera link video image and inputting the converted data to a FPGA (field programmable gate array) chip, an SDI (serial digital interface) decoding chip is used for decoding the data of an SDI standard-definition image and inputting the converted data to the FPGA chip, after the time sequence is reintegrated by the FPGA chip, the data can be directly converted to a video image conforming to protocols of VGA (video graphics array), PAL (programmable array logic), SDI and camera link interface, the data also can be inputted to a DSP (digital signal processor) ship so as to solve the maximal value and the minimal value of the image gray scale and the resolution rate of the image, and after being under the pseudo-color enhanced processing and the image gray-scale stretching processing according to the image information calculated by the DSP chip, the image is outputted and displayed. Due to the adoption of the multifunctional intelligent image conversion system, conversion among multiple interfaces such as camera link, SDI, VGA and PAL can be realized, and the quality of the outputted image is high.

Multifunctional intelligent image conversion system

The invention discloses a method for measuring antenna deformation of ship-borne radio measuring equipment, and relates to the field of spacecraft attitude control ground application. The method solves the problem that in the prior art, self-deformation of the ship-borne radio measuring equipment cannot be measured. The method comprises the steps that 1 a star sensor SS1 and a star sensor SS2 are installed at the position of a base of the ship-borne radio equipment and at the position of the center of the three axes respectively, 2 when a ship docks and displaces, radio antenna directing angles satisfy the equations that A=0 degree and E=90 degrees and are locked, and installation matrixes of the two star sensors are marked, 3 when the ship sails, the antenna directing angles which satisfy the equations that A=0 degree and E=90 degrees are locked, the two star sensors conduct star measuring simultaneously and ship body attitude angles at the position of the base and at the position of the center of the three axes are resolved respectively, and 4 an antenna deformation matrix is resolved and an antenna equivalent deformation angle is solved. According to the method for measuring antenna deformation of the ship-borne radio measuring equipment, astronomical refraction correction is conducted on star sensor attitude angles under the inertial navigation horizontal system, and the calculating precision of the deformation angle is improved.

Method for measuring antenna deformation of ship-borne radio measuring equipment

The invention discloses a quick and autonomous orientation method of a photoelectric theodolite and belongs to the technical field of celestial navigation. The method comprises the following steps of: shooting a star map through the photoelectric theodolite, and identifying at least three fixed stars in a view field by using a star map identification algorithm; adjusting the photoelectric theodolite to ensure that the image of one identified fixed star is formed on a visual axis of the photoelectric theodolite, and computing the view position of the fixed star at this time; computing a theoretical azimuth angle and a theoretical angular altitude of the fixed star relative to the true north by combining an astronomical coordinate of the photoelectric theodolite; selecting other fixed stars to obtain a coder average value of the true north; and introducing the photoelectric theodolite to the measured true north direction, and clearing a direction encoder to finish quick and autonomous orientation of the photoelectric theodolite. The method is high in precision and high in speed, and the advantages of the photoelectric theodolite are realized. By the means of star map identification, the photoelectric theodolite can orient autonomously without initial direction, so that the limit of only observing the Polaris in the conventional astronomical orientation method is broken through, and the photoelectric theodolite can orient in any directions by virtue of any fixed stars.

Quick and autonomous orientation method of photoelectric theodolite

The invention provides a data processing system of a star sensor and relates to the technical field of celestial navigation. The invention aims to solve the problems that when the star sensor autonomously navigates a highly motorized carrier, the posture loss easily occurs, the acceptance rate and the updating rate of data of the star sensor are reduced, and the like. An initial angular velocity measurement module is additionally arranged in the data processing system, so that an initial posture measurement module and a tracking module can be effectively jointed when the carrier is in a highly-motorized state. The tracking measurement module is improved to be a forecast tracking measurement module, so as to forecast a posture angle of the star sensor and a coordinate of a navigation star in a view field of a next sampling period according to the posture angle and a posture angle speed provided by the initial angular velocity measurement module. Therefore, the window tracking and the posture measurement can be completed. The posture angle and the posture angle speed can be updated by using a posture measurement result of the module, and a forecast tracking function is executed. In the forecast tracking measurement module, a conditional number of distribution of a star map is brought in to help judge the posture measurement precision; when the conditional number of the distribution of the star map is relatively large, the forecast tracking measurement module is triggered to identify a relatively large quantity of navigation stars.

Zhang Lei

Papers

Rapid triangle star map recognition method

Multifunctional intelligent image conversion system

Method for measuring antenna deformation of ship-borne radio measuring equipment

Quick and autonomous orientation method of photoelectric theodolite

Data processing system of star sensor