CN102496029B - Space debris identifying method - Google Patents
Space debris identifying method Download PDFInfo
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- CN102496029B CN102496029B CN 201110367652 CN201110367652A CN102496029B CN 102496029 B CN102496029 B CN 102496029B CN 201110367652 CN201110367652 CN 201110367652 CN 201110367652 A CN201110367652 A CN 201110367652A CN 102496029 B CN102496029 B CN 102496029B
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Abstract
A space debris identifying method is characterized by including step one, making a space debris feature base; step two, determining features of space debris to be identified; and step three, identifying the space debris according to comparison of data obtained from the step one and step two. The space debris identifying method is completed in observing software systems of astronomical telescopes using CCD (charge-coupled device) camera equipment or other air telescopes using the CCD camera equipment. Using the space debris identifying method can rapidly identify the observed space debris. The method is already applied to equipment development, and the actual measurement results show that the method is quick in identifying speed and high in identifying success rate and is widely applicable to development of space debris monitoring equipment.
Description
Technical field
The present invention is a kind of space junk personal identification method, and it can identify the identity of the space junk of observing fast, is the fast and high space junk personal identification method of recognition success rate of a kind of recognition speed.
Background technology
In many fields such as scientific research, military affairs, all need space junk is monitored, thereby position and the variation thereof of each moment that provides space junk on high, determine the orbit of space junk, thereby obtain the accurate information of space junk, thereby the relevant information that provides at the rail spacecraft is provided.
The invention of CCD has substituted traditional camera observation, becomes one of effective means of space junk supervision.Because the increase of human solar-system operation causes the space junk in the space more and more, greater than 1 centimetre space junk even reached several ten thousand, threatened the safety of operation on orbit spacecraft.In order to obtain the information of these space junks, must observe it.Traditional telescope generally can only be observed single space junk under the guiding of forecast, this observed pattern can not the application space fragment requirement of cataloguing.In order to observe carrying out a plurality of space junks simultaneously, on the basis of analysis space fragment feature, select comparatively reasonably to observe strategy to carry out space junk observation, this can bring a problem to be simultaneously: there are a plurality of space junks to appear at the observation visual field, and must be to the identity validation of these space junks.So this method just is based under this background and puts forward, it can identify the identity of the space junk of observing fast, and has recognition speed and reach soon the high advantage of recognition success rate.
Summary of the invention
A kind of space junk personal identification method of the present invention, it can identify the identity of the space junk of observing fast, is the fast and high space junk personal identification method of recognition success rate of a kind of recognition speed.
Finish the technical scheme of foregoing invention task, a kind of space junk personal identification method is characterized in that, may further comprise the steps:
⑴. make the space junk feature database;
⑵. determine the feature of space junk to be identified;
⑶. the contrast of integrating step ⑴, step ⑵ the data obtained, carry out the identification of space junk.
Thereby above-mentioned three subsystems closely cooperate and finish the quick identification of space junk identity.More optimize with more specifically above each step of description is as follows:
⑴. make the space junk feature database;
The space junk feature generates subsystem existing space junk, according to its orbit information, according to given space junk feature generation strategy span fragment feature database, for space junk feature identification subsystem.
The feature generation strategy: generate the scope plan kinematic parameter of observation period by the orbit parameter of known spatial fragment by orbit prediction, comprise orbit parameter, the time of passing by, movement velocity, heading, with reference to the apparent magnitude.These characteristics are used for the aspect ratio pair of the measured data obtained after surveillance program is implemented to finish.
⑵. space junk feature to be identified is determined:
Space junk feature to be identified is determined subsystem, according to given space junk observational data to be identified, determines strategy according to given space junk feature, generates its characteristic information, for space junk feature identification subsystem.
Feature is determined strategy: determine that by initial orbit technology obtains the preliminary orbit feature of observation fragment by the location measurement information of measured data, orbit prediction parameter by the known spatial fragment, pass by the time, the measurement data of heading and actual observation fragment is carried out primary election, definite known set of patches that conforms to the actual observation fragment, and each fragment and observation data generated corresponding time error sequence and orbital plane error sequence, and by finding the solution system of linear equations, obtain observing the feature of fragment and known fragment to determine parameter, i.e. the time error, the time error variability, the orbital plane error, orbital plane error variability.
⑶. the space junk identification:
Space junk feature identification subsystem is determined the characteristic information of the space junk to be identified that subsystem generates according to space junk feature generation subsystem span fragment feature database and space junk feature to be identified, space junk identification strategy according to given carries out the identification of space junk.
Given space junk identification strategy: the feature by comparison observation fragment and known fragment is determined parameter, i.e. time error, time error variability, orbital plane error, orbital plane error variability are determined the identity of observation fragment.Comparison thresholding Provisioning Policy is time error less than 60 seconds, time error variability less than 1 second per minute, and the orbital plane error is less than 0.5 degree, and orbital plane error variability is less than 1 degree per minute.
The present invention be the astronomical telescope that adopts the CCD camera installation or adopt the CCD camera installation other sky is finished in the telescopical observation software systems.Related " the space junk feature generates subsystem " reaches the computing machine observation software systems that " space junk feature to be identified is determined subsystem " can adopt astronomical telescope of the prior art, gets final product and increase step operation part of the present invention in the system of prior art.
A kind of space junk recognition methods of the present invention, it can according to the observational data of space junk, identify the identity of the space junk of observing fast.This method has been applied in the equipment development, and measured result shows that the method is the fast and high space junk personal identification method of recognition success rate of a kind of recognition speed, can be widely applied in the development of space junk monitoring equipment.
Description of drawings
Fig. 1 is combined into the synoptic diagram of system of the present invention for each device.
Embodiment
Embodiment 1, and the space junk personal identification method is with reference to Fig. 1: finish the quick identification of space junk identity thereby three subsystems closely cooperate.More optimize with more specifically above each step of description is as follows:
⑴. make the space junk feature database;
The space junk feature generates subsystem existing space junk, and according to its orbit information, according to given space junk feature generation strategy, span fragment feature database is for space junk feature identification subsystem.
The feature generation strategy: generate the scope plan kinematic parameter of observation period by the orbit parameter of known spatial fragment by orbit prediction, comprise orbit parameter, the time of passing by, movement velocity, heading, with reference to the apparent magnitude.These characteristics are used for the aspect ratio pair of the measured data obtained after surveillance program is implemented to finish.
⑵. space junk feature to be identified is determined:
Space junk feature to be identified is determined subsystem, according to given space junk observational data to be identified, determines strategy according to given space junk feature, generates its characteristic information, for space junk feature identification subsystem.
Feature is determined strategy: determine that by initial orbit technology obtains the preliminary orbit feature of observation fragment by the location measurement information of measured data, orbit prediction parameter by the known spatial fragment, pass by the time, the measurement data of heading and actual observation fragment is carried out primary election, definite known set of patches that conforms to the actual observation fragment, and each fragment and observation data generated corresponding time error sequence and orbital plane error sequence, and by finding the solution system of linear equations, obtain observing the feature of fragment and known fragment to determine parameter, i.e. the time error, the time error variability, the orbital plane error, orbital plane error variability.
⑶. the space junk identification:
Space junk feature identification subsystem is determined the characteristic information of the space junk to be identified that subsystem generates according to space junk feature generation subsystem span fragment feature database and space junk feature to be identified, space junk identification strategy according to given carries out the identification of space junk.
Given space junk identification strategy: the feature by comparison observation fragment and known fragment is determined parameter, i.e. time error, time error variability, orbital plane error, orbital plane error variability are determined the identity of observation fragment.Comparison thresholding Provisioning Policy is time error less than 60 seconds, time error variability less than 1 second per minute, and the orbital plane error is less than 0.5 degree, and orbital plane error variability is less than 1 degree per minute.
Claims (1)
1. a space junk personal identification method is characterized in that, the space junk feature generates subsystem, space junk feature to be identified determines that subsystem and space junk feature identification subsystem closely cooperate, and operate according to following steps:
⑴. make the space junk feature database;
The space junk feature generates subsystem existing space junk, and according to its orbit information, according to given space junk feature generation strategy, span fragment feature database is for space junk feature identification subsystem;
The feature generation strategy: generate the scope plan kinematic parameter of observation period by the orbit parameter of known spatial fragment by orbit prediction, comprise orbit parameter, the time of passing by, movement velocity, heading, with reference to the apparent magnitude; These characteristics are used for the aspect ratio pair of the measured data obtained after surveillance program is implemented to finish;
⑵. space junk feature to be identified is determined:
Space junk feature to be identified is determined subsystem, according to given space junk observational data to be identified, determines strategy according to given space junk feature, generates its characteristic information, for space junk feature identification subsystem;
Feature is determined strategy: determine that by initial orbit technology obtains the preliminary orbit feature of observation fragment by the location measurement information of measured data, orbit prediction parameter by the known spatial fragment, pass by the time, the measurement data of heading and actual observation fragment is carried out primary election, definite known set of patches that conforms to the actual observation fragment, and each fragment and observation data generated corresponding time error sequence and orbital plane error sequence, and by finding the solution system of linear equations, obtain observing the feature of fragment and known fragment to determine parameter, i.e. the time error, the time error variability, the orbital plane error, orbital plane error variability;
⑶. the space junk identification:
Space junk feature identification subsystem is determined the characteristic information of the space junk to be identified that subsystem generates according to space junk feature generation subsystem span fragment feature database and space junk feature to be identified, space junk identification strategy according to given carries out the identification of space junk;
Given space junk identification strategy: the feature by comparison observation fragment and known fragment is determined parameter, i.e. time error, time error variability, orbital plane error, orbital plane error variability are determined the identity of observation fragment; Comparison thresholding Provisioning Policy is time error less than 60 seconds, time error variability less than 1 second per minute, and the orbital plane error is less than 0.5 degree, and orbital plane error variability is less than 1 degree per minute.
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| CN102496029B true CN102496029B (en) | 2013-02-06 |
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| CN104267406B (en) * | 2014-09-03 | 2016-08-24 | 中国科学院云南天文台 | A kind of diffuse-reflectance laser ranging and the photo-electric telescope system of high resolution imaging synchro measure |
| CN104750999B (en) * | 2015-04-10 | 2017-10-31 | 中国科学院国家天文台 | Ground based detection equipment based on orbital plane, which is passed by, calculates target and period screening technique |
| CN106850051B (en) * | 2017-04-12 | 2020-04-03 | 上海航天控制技术研究所 | Space debris cleaning system and method based on microsatellite |
| CN110002014A (en) * | 2019-03-21 | 2019-07-12 | 武汉大学 | A kind of space junk correlating method and medium |
| CN113627303A (en) * | 2021-08-03 | 2021-11-09 | 南京航空航天大学 | Space debris identification method and system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101458766A (en) * | 2008-12-16 | 2009-06-17 | 南京大学 | Method for processing astronomical observation gray level image information by computer for target tracing |
| CN101465033A (en) * | 2008-05-28 | 2009-06-24 | 丁国锋 | Automatic tracking recognition system and method |
| CN101846511A (en) * | 2010-04-29 | 2010-09-29 | 中国科学院紫金山天文台 | Detection system of space debris |
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| WO2010039553A1 (en) * | 2008-10-03 | 2010-04-08 | Illumina, Inc. | Method and system for determining the accuracy of dna base identifications |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101465033A (en) * | 2008-05-28 | 2009-06-24 | 丁国锋 | Automatic tracking recognition system and method |
| CN101458766A (en) * | 2008-12-16 | 2009-06-17 | 南京大学 | Method for processing astronomical observation gray level image information by computer for target tracing |
| CN101846511A (en) * | 2010-04-29 | 2010-09-29 | 中国科学院紫金山天文台 | Detection system of space debris |
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