A method for processing and identifying space-based optical measurement data

Abstract

The invention discloses a data processing and identification method based on space-based optical measurement, comprising the following steps: S1, reading space-based optical data; S2, judging whether the data is reasonable, eliminating the unreasonable data, and entering step S3 if it is reasonable; S3, performing data conversion on the reasonable data; S4, determining the initial orbit; S5, if the initial orbit is successfully determined, using the orbit determination result to compare and identify with the TLE in the target set, judging the threshold conditions according to the semi-major axis, eccentricity, and ascending node right ascension, and obtaining suspected targets that meet the threshold conditions; if the initial orbit is determined unsuccessfully, extrapolating and inverting the TLE in the target set, comparing the pointing data with the measured data, giving the right ascension and declination judgment threshold conditions, and selecting suspected targets that meet the threshold conditions; S6, further eliminating the suspected targets through identification rules, finding the closest target, giving a confidence evaluation, and outputting the identification results. The invention solves the problem of large amount of space-based observation data and difficulty in identification.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft data processing, and in particular to a method for processing and identifying space-based optical measurement data. Background Art

[0002] With the development of the aerospace industry, there are more and more space targets, most of which are space debris. The threat of space debris to spacecraft is also increasing. It is necessary to catalog as much space debris as possible. Due to the current problems of large amount of space-based observation data and difficulty in identification, it is difficult to meet the requirements of cataloging more targets by relying solely on external measurement data collected by ground detection equipment. In order to better catalog and manage space targets, detection methods are also increasing. At present, space-based optical observation equipment is also increasingly valued by various countries due to its unique observation advantages. At present, space-based observation data has become an indispensable data type for orbit determination, so space-based optical data processing and target identification have become necessary. Summary of the invention

[0003] In order to solve the existing problems, the present invention provides a method for processing and identifying space-based optical measurement data, which specifically includes the following steps:

[0004] A method for processing and identifying space-based optical measurement data comprises the following steps:

[0005] S1, reads space-based optical data;

[0006] S2, judging whether the data read in S1 is reasonable, if not, discarding it, if reasonable, proceeding to step S3;

[0007] S3, data conversion is performed on the reasonably screened data;

[0008] S4, determining the initial orbit according to the result of step S3;

[0009] S5, if the initial orbit determination is successful, the orbit determination result is compared with the TLE in the target set for identification, and the threshold conditions are determined according to the semi-major axis, eccentricity, and right ascension of the ascending node to obtain suspected targets that meet the threshold conditions; if the initial orbit determination fails, the TLE in the target set is extrapolated and inverted, and the pointing data is compared with the measured data to give the threshold conditions for right ascension and declination, and the suspected targets that meet the threshold conditions are selected;

[0010] S6, further eliminate suspected targets through recognition rules, find the closest target, give a confidence assessment, and output the recognition result.

[0011] Preferably, the reasonable value range of the optical right ascension in the space-based optical data in step S1 is [0º, 360º], and the reasonable value range of the optical declination is [-90º, 90º].

[0012] Preferably, step S3 specifically includes the following steps:

[0013] S31, calculating the position vector of the space target relative to the horizon coordinate system of the observation satellite;

[0014] S32, calculating the relationship between the position vector of the space target, the observation vector of the space target, and the measured right ascension α and declination δ in the equatorial Cartesian coordinate system of the observation star according to the result obtained in step S31 and the transformation matrix from the observation star's horizontal coordinates to the geocentric equatorial coordinates;

[0015] S33, comparing the calculation results of step S32 to obtain the relationship between the right ascension α and the declination δ and the azimuth angle A and the pitch angle E.

[0016] Preferably, if the longitude of the observation star at a certain moment is σ, the latitude is φ, the local sidereal time is θ, the distance of the observation star to a certain space target is ρ, the azimuth is A, and the pitch angle is E, then the position vector of the observation star horizontal coordinate system in step S31 is

[0017] , where is the observed star vector;

[0018] The transformation matrix from the observation star horizontal coordinates to the geocentric equatorial coordinates in step S32 is:

[0019] ,

[0020] Then the position vector of the control target in the Cartesian coordinate system of the observation star equator is

[0021] ;

[0022] Observation vector and measured right ascension of target in Cartesian coordinate system of the observation satellite equator and declination The relationship is

[0023] ;

[0024] Thus, the right ascension is obtained in step S33 and declination The relationship between the azimuth angle A and the elevation angle E is:

[0025] .

[0026] Preferably, the determination of the initial trajectory in step S4 specifically includes the following steps: , , the total number of points is n, No processing is performed, t0 is the initial point, ti is the corresponding sampling time, t i Always observe the longitude, latitude and altitude of the satellite in the fixed system on the ground. is the position component of the observed satellite in the earth fixed system; calculate t i Greenwich Mean Time Sg i , get the observed star t i Time Local Sidereal Time ;

[0027] Using the least squares method of more than three points to determine the orbit, the transformation matrix from the observation satellite's horizontal coordinate system to the observation satellite's equatorial coordinate system is calculated as follows:

[0028] Y direction:

[0029] Z direction:

[0030] The transformation matrix is:

[0031]

[0032] data , The rectangular component converted to the observation satellite's horizontal coordinate system is

[0033]

[0034] The sampling points are converted into the observation star equatorial coordinate system ;

[0035] Set the convergence threshold and the maximum number of iterations to obtain the position component of this set of data , velocity component If the maximum number of iterations does not reach the convergence threshold, the initial orbit determination is considered to have failed.

[0036] The present invention also discloses a computer-readable storage medium, on which a computer program is stored. After the computer program is run, any of the above methods is executed.

[0037] The present invention also discloses a computer system, including a processor and a storage medium, wherein a computer program is stored on the storage medium, and the processor reads and runs the computer program from the storage medium to execute any of the methods described above.

[0038] The beneficial effects of the present invention are:

[0039] The present invention provides a method for processing and identifying space-based optical measurement data, which solves the problem of large amount of space-based observation data and difficulty in identification. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0041] Figure 1 This is a principle block diagram of the present invention. DETAILED DESCRIPTION

[0042] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0043] like Figure 1 A method for processing and identifying space-based optical measurement data, characterized in that it includes the following steps:

[0044] S1, read space-based optical data.

[0045] S2, judging whether the data read in S1 is reasonable, if not, discarding it, if reasonable, proceeding to step S3; wherein, the reasonable value range of the optical right ascension in the space-based optical data is [0º, 360º], and the reasonable value range of the optical declination is [-90º, 90º].

[0046] S3, perform data conversion on the reasonably screened data.

[0047] The specific steps include:

[0048] S31, calculating the position vector of the space target relative to the horizon coordinate system of the observation satellite;

[0049] S32, based on the result obtained in step S31 and the transformation matrix from the observation star's horizontal coordinates to the geocentric equatorial coordinates, calculate the position vector of the space target in the observation star's equatorial Cartesian coordinate system, the observation vector of the space target and the measured right ascension and declination relationship;

[0050] S33, compare the calculation results of step S32 to obtain the right ascension and declination With azimuth and pitch angle relationship.

[0051] Specifically, if the longitude of the observation star at a certain moment is σ, the latitude is φ, the local sidereal time is θ, the distance of the observation star to a certain space target is ρ, the azimuth is A, and the pitch angle is E, then the position vector of the observation star horizontal coordinate system in step S31 is

[0052] , where is the observed star vector;

[0053] The transformation matrix from the observation star's horizontal coordinates to the observation star's equatorial coordinates in step S32 is:

[0054] ,

[0055] Then the position vector of the control target in the Cartesian coordinate system of the observation star equator is

[0056] ;

[0057] Observation vector and measured right ascension of target in Cartesian coordinate system of the observation satellite equator and declination The relationship is

[0058] ;

[0059] Thus, the right ascension is obtained in step S33 and declination The relationship between the azimuth angle A and the elevation angle E is:

[0060] .

[0061] S4, determining the initial orbit according to the result of step S3.

[0062] The determination of the initial trajectory requires the determination of the initial position and velocity of the target, which specifically includes the following steps: , the total number of points is n, No processing is performed, t0 is the initial point, t i is the corresponding sampling time, t i Always observe the longitude, latitude and altitude of the satellite in the fixed system on the ground. is the position component of the observed satellite in the earth fixed system; calculate t i Greenwich Mean Time Sg i , get the observed star t i Time Local Sidereal Time ;

[0063] Using the least squares method of more than three points to determine the orbit, the transformation matrix from the observation satellite's horizontal coordinate system to the observation satellite's equatorial coordinate system is calculated as follows:

[0064] Y direction:

[0065] Z direction:

[0066] The transformation matrix is:

[0067]

[0068] data , The rectangular component converted to the observation satellite's horizontal coordinate system is

[0069] The sampling points are converted into the observation star equatorial coordinate system ;

[0070] Set the convergence threshold and the maximum number of iterations to obtain the position component of this set of data , velocity component If the maximum number of iterations does not reach the convergence threshold, the initial orbit determination is considered to have failed.

[0071] S5, if the initial orbit determination is successful, the orbit determination result is compared with the two rows of orbit elements tle in the target set for identification, and the threshold conditions are determined according to the semi-major axis, eccentricity, and right ascension of the ascending node to obtain suspected targets that meet the threshold conditions; if the initial orbit determination fails, the tle in the target set is extrapolated and inverted, and the pointing data is compared with the measured data to give the threshold conditions for right ascension and declination, and the suspected targets that meet the threshold conditions are selected;

[0072] S6, further eliminate suspected targets through recognition rules, find the closest target, give a confidence assessment, and output the recognition result.

[0073] The present invention provides a method for processing and identifying space-based optical measurement data, which solves the problem of large amount of space-based observation data and difficulty in identification.

[0074] The present invention also discloses a computer-readable storage medium, on which a computer program is stored. After the computer program is run, any of the above methods is executed.

[0075] The present invention also discloses a computer system, including a processor and a storage medium, wherein a computer program is stored on the storage medium, and the processor reads and runs the computer program from the storage medium to execute any of the methods described above.

[0076] Those skilled in the art will further appreciate that the various illustrative logic blocks, modules, circuits, and algorithm steps described in conjunction with the embodiments disclosed herein may be implemented as electronic hardware, computer software, or a combination of the two. To clearly illustrate this interchangeability of hardware and software, various illustrative components, blocks, modules, circuits, and steps are generally described above in terms of their functionality. Whether such functionality is implemented as hardware or software depends on the specific application and the design constraints imposed on the overall system. The technician may implement the described functionality in different ways for each specific application, but such implementation decisions should not be interpreted as resulting in a departure from the scope of the present invention.

[0077] The various illustrative logic blocks, modules, and circuits described in conjunction with the embodiments disclosed herein may be implemented or performed with a general purpose processor, a digital signal processor (DSP), an application specific integrated circuit (ASIC), a field programmable gate array (FPGA) or other programmable logic device, discrete gate or transistor logic, discrete hardware components, or any combination thereof designed to perform the functions described herein. A general purpose processor may be a microprocessor, but in the alternative, the processor may be any conventional processor, controller, microcontroller, or state machine. The processor may also be implemented as a combination of computing devices, such as a combination of a DSP and a microprocessor, a plurality of microprocessors, one or more microprocessors in cooperation with a DSP core, or any other such configuration.

[0078] The steps of the method or algorithm described in conjunction with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of the two. The software module may reside in a RAM memory, a flash memory, a ROM memory, an EPROM memory, an EEPROM memory, a register, a hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to a processor so that the processor can read and write information from / to the storage medium. In an alternative, a storage medium may be integrated into a processor. The processor and the storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In an alternative, the processor and the storage medium may reside in a user terminal as discrete components.

[0079] In one or more exemplary embodiments, the functions described may be implemented in hardware, software, firmware, or any combination thereof. If implemented as a computer program product in software, each function may be stored on or transmitted by a computer-readable medium as one or more instructions or codes. Computer-readable media include both computer storage media and communication media, including any medium that facilitates the transfer of a computer program from one place to another. Storage media may be any available medium that can be accessed by a computer. As an example and not limitation, such a computer-readable medium may include RAM, ROM, EEPROM, CD-ROM or other optical disk storage, disk storage or other magnetic storage device, or any other medium that can be used to carry or store the desired program code in the form of an instruction or data structure and can be accessed by a computer. Any connection is also properly referred to as a computer-readable medium. For example, if the software is transmitted from a website, server, or other remote source using a coaxial cable, fiber optic cable, twisted pair, digital subscriber line (DSL), or wireless technologies such as infrared, radio, and microwaves, the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwaves are included in the definition of the medium. Disk and disc as used herein include compact disc (CD), laser disc, optical disc, digital versatile disc (DVD), floppy disk and Blu-ray disc, wherein disk often reproduces data magnetically, while disc reproduces data optically with lasers. Combinations of the above should also be included within the scope of computer-readable media.

[0080] The previous description of the disclosure is provided to enable any person skilled in the art to make or use the disclosure. Various modifications to the disclosure will be apparent to those skilled in the art, and the general principles defined herein may be applied to other variations without departing from the spirit or scope of the disclosure. Thus, the disclosure is not intended to be limited to the examples and designs described herein, but should be granted the widest scope consistent with the principles and novel features disclosed herein.

[0081] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent substitutions for some of the technical features therein; and these modifications or substitutions do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for processing and identifying space-based optical measurement data. It is characterized in that The following steps are involved: S1, reads space-based optical data; S2, judging whether the data read in S1 is reasonable, if not, discarding it, if reasonable, proceeding to step S3; S3, data conversion is performed on the reasonably screened data; The specific steps include: S31, calculating the position vector of the space target relative to the horizon coordinate system of the observation satellite; S32, calculating the relationship between the position vector of the space target, the observation vector of the space target, and the measured right ascension α and declination δ in the equatorial Cartesian coordinate system of the observation star according to the result obtained in step S31 and the transformation matrix from the observation star's horizontal coordinates to the geocentric equatorial coordinates; S33, comparing the calculation results of step S32 to obtain the relationship between the right ascension α and the declination δ and the azimuth angle A and the pitch angle E; If the longitude of the observation star at a certain moment is σ, the latitude is φ, the local sidereal time is θ, the distance of the observation star to a certain space target is ρ, the azimuth is A, and the pitch angle is E, then the position vector of the observation star's horizontal coordinate system in step S31 is: , where is the observed star vector; The transformation matrix from the observation star's horizontal coordinates to the observation star's equatorial coordinates in step S32 is: ， Then the position vector of the control target in the Cartesian coordinate system of the observation star equator is: ； The relationship between the target observation vector and the measured right ascension α and declination δ in the Cartesian coordinate system of the observation satellite equator is: ； Therefore, the relationship between the right ascension α and the declination δ and the azimuth angle A and the pitch angle E obtained in step S33 is: ； S4, determining the initial orbit according to the result of step S3; The determination of the initial trajectory requires determining the initial position and velocity of the target, which includes the following steps: A set of data after transformation (t i , A i , E i ), i=0, 1, 2, ..., n; the total number of points is n, and no processing is performed when n ≤ 3, t 0 is the initial point, t i is the corresponding sampling time; STA (i,j) , i=0,1,2,…,n; j=1,2,3; is t i Always observe the longitude, latitude and altitude of the satellite in the Earth's fixed system; STA1 (i,j) , i=0,1,2,...,n; j=1,2,3; is the position component of the observed star in the earth fixed system; calculate the Greenwich sidereal time Sgi at time ti, and get the local sidereal time of the observed star at time ti ; Using the least squares method of more than three points to determine the orbit, the transformation matrix from the observation satellite's horizontal coordinate system to the observation satellite's equatorial coordinate system is calculated as follows: Y-direction: ; Z direction: ; The transformation matrix is: ; Data (t i , A i , E i ), i=0, 1, 2, ..., n; the rectangular component converted to the observation star's horizontal coordinate system is ; The sampling points are converted into the observation star equatorial coordinate system ; Set the convergence threshold and the maximum number of iterations to obtain the position component of this set of data , velocity component ,If the maximum number of iterations does not reach the convergence threshold, it is considered that the initial orbit determination has failed; S5, if the initial orbit determination is successful, the orbit determination result is compared with the two rows of orbit elements tle in the target set for identification, and the threshold conditions are determined according to the semi-major axis, eccentricity, and right ascension of the ascending node to obtain suspected targets that meet the threshold conditions; if the initial orbit determination fails, the tle in the target set is extrapolated and inverted, and the pointing data is compared with the measured data to give the threshold conditions for right ascension and declination, and the suspected targets that meet the threshold conditions are selected; S6, further eliminate suspected targets through recognition rules, find the closest target, give a confidence assessment, and output the recognition result.

2. The method according to claim 1, It is characterized in that The method according to claim 1 is characterized in that: the reasonable value range of the optical right ascension in the space-based optical data in step S1 is [0º, 360º], and the reasonable value range of the optical declination is [-90º, 90º].

3. A computer-readable storage medium, Features: A computer program is stored on the medium, and after the computer program is run, the method according to any one of claims 1 to 2 is executed.

4. A computer system, Features: The method comprises a processor and a storage medium, wherein a computer program is stored in the storage medium, and the processor reads and runs the computer program from the storage medium to execute the method as claimed in any one of claims 1 to 2.

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