CN116659521B - Space debris double-arc angle measurement value integrated primary rail determination and correlation method and device - Google Patents
Space debris double-arc angle measurement value integrated primary rail determination and correlation method and device Download PDFInfo
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Abstract
The invention discloses a space debris double-arc angle measurement value integrated orbit determination and an associated method and device, and belongs to the technical fields of space situation awareness, space target tracking, orbit determination and cataloging. And carrying out association of two independent initial track parameters without track error covariance by utilizing the two independent initial track parameters without prior information so as to judge whether the two initial track parameters are from the same fragment target, then estimating the observation distance of a station and a fragment of the obtained space fragment by correcting the original initial track parameters, carrying out initial track determination again on the basis of the distance information so as to obtain initial track parameters with improved accuracy, carrying out association judgment continuously according to the improved initial track parameters, and judging whether the initial track parameters are from the same target by utilizing the track difference of iteration improvement for a plurality of times as a criterion. The invention can obviously improve the track precision, has higher accuracy and calculation efficiency than the CBTA method, and does not need the track error covariance information.
Description
Technical Field
A space debris double-arc angle measurement value integrated orbit determination and correlation method and device belong to the technical fields of space situation awareness, space target tracking, orbit determination and cataloging.
Background
The space debris target can only be observed passively, and an optical telescope is a common observation means. The method comprises the steps of processing track data of a space debris target flying in an optical telescope field of view, determining an astronomical positioning result (right ascension and declination) corresponding to a space target track by using an astronomical positioning technology based on a sky background image of the space target captured by the telescope in the fly-by field of view, and forming angle observation arc section data of the space debris if a plurality of continuous images can observe the target. Since the target motion speed is fast (about 7 km/s, LEO target), the telescope field of view is limited, so the observation arc length is typically short, such as tens of seconds to minutes, and the observation arc length (observation data duration) appears very short compared to the orbit period of the target, accounting for only a small fraction of its operation period, even less than 0.5%.
The application mainly relates to three technologies, namely, first, single-arc very (extremely) short-arc initial orbit determination, second, association of two very (extremely) short-arc initial orbit parameters, and third, orbit determination of two very (extremely) short-arc angle measurement data. The very (extremely) short arc initial trajectory parameters herein are a set of trajectory parameters obtained by initial trajectory determination with or based on an observation arc segment of very short duration, which may be kepler trajectory parameters or position velocity. The initial orbit determination of angle observation data only refers to the angle observation quantity of a given natural or artificial celestial object at least three moments, which can be (red warp, declination) or (altitude, azimuth), and a set of six independent kepler orbit parameters of the object are solved. The correlation of the very (extremely) short arc initial track parameters is that for two known initial track parameters without prior information (which are usually obtained by tracking single very (extremely) short arc optical (angle) observation data), whether the two parameters belong to the same target is judged by a certain method. The space object may be a space debris or a satellite. The technique is applicable to both space debris and satellites.
From 1957, the human launched the first satellite, and by ESA statistics, by 2022, 12 months and 22 days, the human performed nearly 6340 spacecraft launching activities (including failed tasks), 14710 spacecraft were put into the near-earth orbit, 9780 targets were still in orbit, only 6900 spacecraft were in effective service, the space target inventory maintained by SSN in the united states had 32500 targets, and other space garbage or space debris was changed due to loss of function, and more than 640 events such as on-orbit spacecraft or rocket disintegration/explosion/impact (breaking) occurred, with the total mass of the on-orbit targets being about 10500 tons (from ESA website). Spatial targets include on-orbit working spacecraft and space debris, most of which are space debris. The number of targets greater than 10 cm is about 36500 in terms of target size; the number of fragments of size 1-10 cm is about 100 tens of thousands; the number of fragments greater than 1mm in size was about 1.3 hundred million (from ESA).
The year 2022, month 1 and 28, the news office of China national institutes, 2021, issues white paper of aerospace, wherein the space debris monitoring part clearly indicates that "five years in the future, china will comprehensively advance the construction of a space environment management system. Space traffic management is enhanced, a space debris monitoring facility system, an inventory database and an early warning service system are built and perfected, and the operations of on-orbit maintenance, collision avoidance control, space debris alleviation and the like of the spacecraft are comprehensively prepared, so that the space system is ensured to run safely, stably and orderly.
The space target is observed by the optical telescope to obtain an observation arc section, and the initial track of the space target is determined based on the single arc section, but the initial track parameter precision is not ideal in general, and the space target is not enough to be directly cataloged and put in storage. Therefore, the data association requirement is generated, namely, a plurality of independent primary tracks from the same fragment target are associated in a data association mode, then all data of the associated successful arc segments are utilized to carry out precise track determination, the track precision is improved, and cataloging and warehousing of the space target are realized. Therefore, short arc initial track association is a key technology which is indispensable for expanding the scale of the existing catalogue library, is a research hotspot in the field of space situation awareness in the last ten years, is still in development stage in theory and method at present, and is not mature and widely accepted.
For the problem of space target initial orbit correlation, foreign scholars propose a series of methods, (Lei Xiangxu, 2019) to summarize the existing space target observation data correlation method into four types of algorithms, namely an AR type method (Milani et al., 2004,), an IVP (SIMINSKI ET al., 2014) and a BVP type method (DEMARS AND Jah, 2013), a CBTA type method (Hill et al., 2008), a JPDA and an MTT type method (Bar-Shalm, 1990). The CBTA method is proposed by Hill et al at 2008, the basic idea of which is: given two independent sets of initial track parameters and covariance thereof, selecting a reference moment of one set of track parameters, transmitting the other set of track parameters and covariance thereof to the reference moment, calculating a variable similar to the mahalanobis distance of the two sets of parameters at the reference moment, comparing the variable with a preset threshold value, and determining whether the two sets of track parameters belong to the same fragment. Algorithms of this type have evolved in recent years to extend the algorithm to both flat and instantaneous track numbers (Cazabonne and Cefola, 2021; park and Alfriend, 2022).
In summary, the related algorithms in the prior art are theoretically solid, but there are two prominent problems in practice. First, covariance of the known orbit parameters is required, and second, propagation of covariance is required. The initial orbit determination is carried out by utilizing the very (extremely) short arc angle observation data, the error of the orbit parameter obtained by solving is unstable, and a relatively real error value is difficult to obtain, namely the covariance of the initial orbit parameter is unknown in most cases or is only approximately known. Further, propagation of the orbit parameter covariance is a more difficult problem (Luo and Yang, 2017), which relates to the realism and computational efficiency of the covariance after propagation. The combined impact of the two problems makes the aforementioned methods more uncomfortable to apply to primary track association, which limits the application of CBTA methods. After observing and obtaining a huge number of very (extremely) short arc initial tracks, if the initial track association problem or inefficiency can not be solved, the expansion of the fragment inventory library is severely limited.
Most of the existing algorithms only realize primary track association, but do not realize the track determination of two arc sections, and the rate of nano-pseudo is also required to be reduced. On the basis of the research of the current initial track association algorithm, if the initial track determination and the association algorithm can be integrated, association can be realized, initial track precision is expected to be improved, the defects of the existing initial track determination or association algorithm can be overcome, the method is more suitable for the association scene of massive observation data of a large-scale space target in the future, and the method has larger application potential.
In summary, for angle-only short arc data of space debris, the problems of initial orbit determination of a single arc segment, association of two arc segments and orbit determination remain to be further solved, and no mature and widely accepted algorithm exists for the problems. Meanwhile, a large number of monitoring devices are built in the next few years of China, and then higher requirements are put forward on the initial track setting and association of massive observation data of large-scale space fragments.
Disclosure of Invention
The invention aims to solve the technical problems that: the method and the device solve the problems of low efficiency or low accuracy in the prior art, and can obtain the space debris double-arc angle measurement value integrated initial rail determination of two arc section rail determination results.
The technical scheme adopted for solving the technical problems is as follows: the space debris double-arc angle measurement value integrated primary rail fixing and correlation method is characterized in that: the method comprises the following steps:
s1, respectively carrying out initial track determination on two angle measurement short arc data of any space debris target without prior information to obtain two groups of initial track parameters;
s2, based on the track parameters of two groups of initial moments of different moments of the space debris target, selecting a plurality of decision moments of association judgment;
S3, respectively spreading the two groups of orbit parameters in the step S1 to a plurality of decision moments by using an orbit spreading method, and calculating three-dimensional space distance difference, semi-major axis difference, eccentricity difference and orbit plane difference of the two groups of orbit parameters at the selected decision moments;
S4, judging whether the three-dimensional space distance difference, the semi-major axis difference, the eccentricity difference, the track inclination difference, the included angle of the track surface and the radial difference of two groups of track parameters, the track direction difference and the track surface normal difference are all smaller than corresponding thresholds or not, and executing S5 if yes; otherwise, judging that the two groups of track parameters come from different space debris targets;
S5, propagating the tracks to a plurality of decision moments by utilizing a track propagation method, obtaining two groups of propagated track numbers, and calculating the difference of two groups of propagated track parameters at the same decision moment;
Judging whether the three-dimensional space distance difference, the semi-major axis difference, the eccentricity difference, the track inclination difference, the included angle of the track surface and the radial difference of two groups of track parameters, the track direction difference and the track surface normal difference are smaller than corresponding thresholds or not, and executing the step S6 if yes; if not, judging that the two are from different space debris targets;
S6, the corrected primary track semi-long axis and track inclination angle are utilized to replace the semi-long axis and track inclination angles of two groups of primary track parameters, corrected primary track positions and corrected primary track speed are obtained, observation arc section information corresponding to each primary track is determined, the distance between space fragments and the corresponding moment and between the corresponding stations is estimated according to station measurement information contained in the observation arc sections, and primary track determination is carried out on the two arc sections again by taking the distance as the initial distance of a distance searching method;
S7, if the two arc sections are successful in obtaining initial track parameters, repeating the steps S1 to S6 on the two groups of initial track parameters, and judging whether three-dimensional position differences, track semi-long axis differences, eccentricity differences, inclination angle differences, track surface differences and RTN differences of the two groups of track parameters at a plurality of decision moments are smaller than corresponding thresholds or not, if so, judging that the two groups of track parameters come from the same space debris target; if not, both are considered to be from different fragments;
S8, for two arc sections successfully associated, based on the initial track parameters of the two arc sections, simultaneously carrying out track fixing again by using the two arc sections, wherein a track fixing result is an integrated initial track fixing and association result of the two angle measuring arc sections; if the orbit determination is successful, considering that the two are from the same target and obtaining an orbit determination result of double-arc angle measurement data; otherwise, both are considered to be from different targets.
Preferably, in step S1, the angle measurement value of the space debris target is the angle observation data of the very short arc, the initial orbit parameter is the initial orbit parameter of the angle observation data of the single very short arc, and the integrated initial orbit determination and association result is the combined association orbit determination result of the angle measurement data of the double arcs.
Preferably, the orbit parameters described in step S1 include orbit semi-major axis, orbit eccentricity, orbit inclination angle, ascending intersection point right ascent, near-point angular distance, flat near-point angle, or three-dimensional space position, speed, and observation time corresponding to orbit parameters of the space debris object in the inertial system.
Preferably, the decision time in step S2 is any time between the observation times corresponding to the two sets of track parameters or the observation times corresponding to the two sets of track parameters.
Preferably, the decision time in step S2 is the middle time of the observation time corresponding to the two sets of track parameters and other decision times.
Preferably, in step S3, the two sets of track parameters in step S1 are propagated to the multiple decision moments by using an analytical track propagation method.
Preferably, in step S5, the semi-major axis and the track inclination angle of the two sets of track parameters at the decision time are corrected by using a cyclic method.
Preferably, the method for correcting the semi-major axis and the inclination angle of the track at multiple decision moments for two sets of track parameters in step S5 includes the following steps:
the method for the track semi-major axis and the track inclination angle comprises the following steps:
S5.1, calculating the orbit parameters or the three-dimensional space position and speed of the space debris target at the moment of determination by using an analytic orbit propagation method, and then calculating to obtain the position difference and the speed difference;
s5.2, converting the position difference and the speed difference in the step S5.1 into an initial radial difference, an initial track direction difference and an initial track surface normal difference of the track according to the three-dimensional position and the speed of the space debris target;
calculating the average moving speed and the average center distance of the space debris target at the decision time to obtain the semimajor axis and the track dip angle at the corrected decision time;
S5.3, taking the corrected semi-long axis of the orbit and the orbit inclination angle at the decision time as two groups of orbit parameters, and respectively spreading the two groups of orbit parameters to the semi-long axis and the orbit inclination angle at the decision time;
And S5.4, repeating the steps S5.1-S5.3 for more than two times, and taking the last calculated difference along the track direction, the radial difference and the normal difference of the track surface as the difference along the track direction, the radial difference and the normal difference of the track surface of the two groups of track parameters at the decision moment.
Preferably, in step S6, the estimated distance between the station and the fragment is taken as the initial distance of the distance searching method, and the initial track determining method is performed again for the two arc segments, which comprises the following steps:
S6.1, replacing the semimajor axis and the track inclination angles of the two groups of track parameters by using the corrected semimajor axis and the track inclination angles to obtain new corrected initial track parameters, positions and speeds;
S6.2, original observation data of the two arc segments which are being associated and calculated are determined, station measurement information of corresponding time is extracted, and the distance between the space debris and the station measurement at the corresponding time is estimated according to the station measurement information and the corrected track parameters;
s6.3, based on the distance between the space debris and the measuring station estimated in the step S6.2, using a distance searching method, taking the distance as an initial reference distance, and carrying out initial track determination on the two arc sections again;
And S6.4, if the initial track determination is successful, the step S7 is carried out, otherwise, the two are judged to be from different targets.
Space fragment double-arc angle measurement value integrated primary rail and associated device, characterized in that: comprising a readable and writable memory device which performs the method described above.
Compared with the prior art, the invention has the following beneficial effects:
For two groups of independent space fragment angle measurement arc segments, initial rail determination of a single arc segment is carried out firstly, then association and rail determination of the two arc segments are carried out, rail determination is carried out in the association process, association is carried out after rail determination, iteration is continued, and mutual improvement is carried out; for given two groups of independent space fragment angle measurement arc segments, not only can an initial track association result (whether from the same target) be obtained, but also improved initial track parameters can be obtained in the association judgment iteration improvement process, and the track precision can be remarkably improved; for given two groups of independent space fragment angle measurement arc segments, if the two arc segments are successfully associated, the combined orbit determination of the two arc segments is carried out, so that the initial orbit parameters of double-arc angle measurement data can be obtained, and the orbit precision is obviously improved; for two independent space debris angle measurement arc sections, the accuracy and the calculation efficiency of the method are higher than those of a CBTA method by utilizing the method for associating two groups of initial track parameters; when two independent very (extremely) short arcs are given, only the initial track parameters of the data are observed at angles, the two initial track parameters are associated by using the method, and the association accuracy of different targets is higher than that of a geometric method.
The method only needs to know the initial orbit parameters of the angle observation values of two independent very short arcs, the reference time and the corresponding observation data, and compared with the CBTA method, the method does not need orbit error covariance information.
The method has good autonomous iteration improved initial track determination result and double-arc associated track determination capability, and can automatically run on a computer and give out associated judgment result and double-arc initial track parameters.
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FIG. 1 is a flow chart of a spatial debris dual arc angle measurement integrated primary rail determination and associated method.
Detailed Description
The present application will be further described with reference to specific embodiments, however, it will be appreciated by those skilled in the art that the detailed description herein with reference to the accompanying drawings is for better illustration, and that the application is not necessarily limited to such embodiments, but rather is intended to cover various equivalent alternatives or modifications, as may be readily apparent to those skilled in the art.
FIG. 1 is a preferred embodiment of the present invention, and the present invention is further described with reference to FIG. 1.
The present invention provides two independent sets of very (extremely) short arc angle observations without a priori information, either from the same target or from two targets. The initial trajectory parameters of the individual arc segments may be classical kepler parameters or other forms of parameters (position, velocity or others), typically the initial trajectory parameters contain errors and the errors are large and unknown.
The method comprises the steps of firstly determining initial tracks of single arc segments, carrying out two arc segment association by utilizing initial track determination results, determining whether two independent angle measurement arc segments without prior information come from the same target or fragment or not in an association judgment mode, and carrying out double-arc track determination on two angle measurement arc segments successfully associated.
The associated orbit determination calculation comprises the following steps:
Step 1, two independent very (extremely) short arc angle observation data are given, wherein the two independent very (extremely) short arc angle observation data are from the same target or two targets.
And 2, selecting a plurality of decision moments, wherein the decision moments can be two groups of track parameter reference moments or any moment between the two groups of track parameter reference moments. The average value of the reference moments of the two groups of track parameters is selected as a decision moment.
And 3, respectively transmitting the two groups of track parameters to the decision time. The analysis orbit propagation method is adopted to realize orbit propagation, and the efficiency is higher.
And 4, calculating the three-dimensional space distance, the semi-major axis difference, the eccentricity difference, the track inclination angle and the radial difference, the track direction difference and the track plane normal difference of the two groups of track parameters at the selected decision time.
Step 5, comparing the semi-major axis difference, the track surface included angle, the radial difference of two groups of track parameters, the track direction difference and the track surface normal difference with set thresholds, and making preliminary association judgment, and if one of the semi-major axis difference, the track surface included angle, the radial difference, the track direction difference and the track surface normal difference is larger than the thresholds, considering that the two are from different targets, and ending association; otherwise, both may come from the same shard, continuing the association calculation.
Step 6, adjusting the semimajor axis and the inclination angle of the track, and judging whether the two groups of initial track parameters come from the same fragment according to the difference in the track radial direction, the track direction and the track surface normal direction if the two groups of track parameters have very small track direction deviation after the two groups of parameters are transmitted to the decision moment; if the difference along the track direction, the track radial direction and the track surface normal direction are smaller than the threshold value, performing iterative improvement of the next stage; otherwise, both are considered to be from different targets.
Step 7, replacing the semimajor axis and the inclination angle of the initial track according to the adjusted semimajor axis and the track inclination angle of the track to obtain a group of new track parameters; by using the obtained new track parameters and combining the station position coordinates in the observation arc segment data corresponding to the primary track, the distance between the station and the fragments can be calculated and obtained, and the distance can be regarded as the observation distance.
Step 8, using a distance searching algorithm, taking the distance in the step 7 as an initial value of the distance searching, and carrying out initial track determination on the observation arc section again; if the observation data corresponding to the two primary tracks can be successfully determined again, the next step is carried out, otherwise, the two primary tracks are considered to come from different targets, and the association is finished.
And 9, repeating the steps 2-7 for a plurality of times for the initial track parameters obtained in the step 8, judging according to the track difference obtained in the last calculation, if the difference is smaller than the threshold value, considering the initial track parameters as the same target, otherwise, considering the initial track parameters as different targets, and ending the association.
And 10, for two angle measurement arc sections which are successfully associated, carrying out joint orbit determination of the two arc sections based on initial orbit parameter information of each of the two arc sections.
Through the above related orbit determination calculation, not only can it be judged whether two angle measurement arc segments come from the same target, but also for the arc segments which are successfully related, based on the respective orbit initial results of the two angle measurement arc segments, the orbit parameters with improved accuracy can be obtained by simultaneously determining the orbit by using the two arc segments again, and compared with the initial orbit results of the single arc segment, the orbit initial parameter accuracy is obviously improved.
Specifically, as shown in fig. 1: the space debris double-arc angle measurement value integrated primary rail fixing and correlation method comprises the following steps:
S1, respectively carrying out initial track determination on two angle measurement short arc data of any space debris target without prior information to obtain two groups of initial track parameters.
Specifically, according to the initial orbit parameters of two groups of very (extremely) short arcs of the space debris and the corresponding observation data thereof, the initial orbit parameters comprise reference moments of orbit semi-long axes, orbit eccentricities, orbit inclinations, ascending intersection points, right transparencies, near-site angular distances, even near-site angles and orbit parameters. Setting a decision time of the association judgment, wherein the decision time is selected as the reference time of the two groups of track parameters or any time between the two groups of track parameters. The first-choice decision moment is the middle moment of the reference moments of the two sets of track parameters. The initial track parameter is the initial track parameter.
S2, based on the track parameters of two groups of initial moments of different moments of the space debris target, selecting a plurality of decision moments of association judgment.
Specifically, the two groups of orbit parameters in the step S1 are respectively transmitted to the decision time by using a semi-analytic method of orbit transmission; and calculating the semi-major axis difference and the track surface included angle of the two groups of track parameters at the decision moment.
S3, respectively spreading the two groups of orbit parameters in the step S1 to a plurality of decision moments by using an orbit spreading method, and calculating the three-dimensional space distance difference, the semi-long axis difference, the eccentricity difference and the orbit plane difference of the two groups of orbit parameters at the selected decision moments.
When the semi-major axis difference and the track surface included angle in the step S2 are smaller than the set threshold value, the step S4 is shifted to; otherwise, the two sets of track parameters are considered to come from different spatial fragments, and the association is ended.
S4, judging whether the three-dimensional space distance difference, the semi-major axis difference, the eccentricity difference, the track inclination difference, the included angle of the track surface and the radial difference of two groups of track parameters, the track direction difference and the track surface normal difference are all smaller than corresponding thresholds or not, and executing S5 if yes; otherwise, determining that the two sets of orbit parameters come from different spatial debris targets.
S5, propagating the tracks to a plurality of decision moments by utilizing a track propagation method, obtaining two groups of propagated track numbers, and calculating the difference of two groups of propagated track parameters at the same decision moment.
Judging whether the three-dimensional space distance difference, the semi-major axis difference, the eccentricity difference, the track inclination difference, the included angle of the track surface and the radial difference of two groups of track parameters, the track direction difference and the track surface normal difference are smaller than corresponding thresholds or not, and executing the step S6 if yes; if not, it is determined that the two are from different spatial debris targets.
Specifically, according to the adjusted semimajor axis and track inclination angle of the track, replacing the semimajor axis and inclination angle of the initial track to obtain a set of new track parameters; by using the obtained new track parameters and combining the station position coordinates in the observation arc segment data corresponding to the primary track, the distance between the station and the fragments can be calculated and obtained, and the distance can be regarded as the observation distance.
The method for correcting the semi-long axis and the track inclination angle of the tracks of two groups of track parameters at a plurality of decision moments comprises the following steps:
S5.1, calculating the orbit parameters or the three-dimensional space position and speed of the space debris target at the moment of determination by using an analytic orbit propagation method, and then calculating to obtain the position difference and the speed difference;
s5.2, converting the position difference and the speed difference in the step S5.1 into an initial radial difference, an initial track direction difference and an initial track surface normal difference of the track according to the three-dimensional position and the speed of the space debris target;
calculating the average moving speed and the average center distance of the space debris target at the decision time to obtain the semimajor axis and the track dip angle at the corrected decision time;
S5.3, taking the corrected semi-long axis of the orbit and the orbit inclination angle at the decision time as two groups of orbit parameters, and respectively spreading the two groups of orbit parameters to the semi-long axis and the orbit inclination angle at the decision time;
And S5.4, repeating the steps S5.1-S5.3 for more than two times, and taking the last calculated difference along the track direction, the radial difference and the normal difference of the track surface as the difference along the track direction, the radial difference and the normal difference of the track surface of the two groups of track parameters at the decision moment.
S6, the corrected primary track semi-long axis and track inclination angle are utilized to replace the semi-long axis and track inclination angles of two groups of primary track parameters, corrected primary track positions and corrected primary track speed are obtained, observation arc section information corresponding to each primary track is determined, the distance between space fragments and the corresponding moment and the measuring stations is estimated according to station measuring information contained in the observation arc sections, and primary track determination is carried out on the two arc sections again by taking the distance as the initial distance of a distance searching method.
Specifically, using a distance searching algorithm, taking the distance in the step S5 as an initial value of the distance searching, and performing initial track determination on the observation arc section again; if the observation data corresponding to the two primary tracks can be successfully determined again, the step S6 is entered, otherwise, the two primary tracks are considered to come from different targets, and the association is ended.
Taking the estimated distance between the station and the fragment as the initial distance of a distance searching method, and carrying out an initial track determining method on the two arc sections again, wherein the initial track determining method comprises the following steps of:
S6.1, replacing the semimajor axis and the track inclination angles of the two groups of track parameters by using the corrected semimajor axis and the track inclination angles to obtain new corrected initial track parameters, positions and speeds;
S6.2, original observation data of the two arc segments which are being associated and calculated are determined, station measurement information of corresponding time is extracted, and the distance between the space debris and the station measurement at the corresponding time is estimated according to the station measurement information and the corrected track parameters;
s6.3, based on the distance between the space debris and the measuring station estimated in the step S6.2, using a distance searching method, taking the distance as an initial reference distance, and carrying out initial track determination on the two arc sections again;
And S6.4, if the initial track determination is successful, the step S7 is carried out, otherwise, the two are judged to be from different targets.
S7, if the two arc sections are successful in obtaining initial track parameters, repeating the steps S1-S6 on the two groups of initial track parameters, and judging whether three-dimensional position differences, track semi-long axis differences, eccentricity differences, inclination angle differences, track surface differences and RIC differences of the two groups of track parameters at a plurality of decision moments are smaller than corresponding thresholds or not, if so, judging that the two groups of track parameters come from the same space debris target; if otherwise both are considered to be from different fragments.
Specifically, for the initial track parameters obtained in the step S6, repeating the steps S1 to S6 for a plurality of times, judging according to the track difference obtained in the last calculation, if the difference is smaller than the threshold value, considering the two as the same target, otherwise, considering the two as different targets, and ending the association. If the two are from the same target, the two arc sections are utilized to carry out combined orbit determination, the orbit parameters after the orbit determination is successful are obtained, otherwise, the association fails, and the two are considered to be from different targets. Through the association calculation, not only the initial track successfully associated can be obtained, but also the improved initial track parameter can be obtained, and the initial track parameter precision is obviously improved.
S8, for two arc sections successfully associated, based on the initial track parameters of the two arc sections, simultaneously carrying out track fixing again by using the two arc sections, wherein a track fixing result is an integrated initial track fixing and association result of the two angle measuring arc sections; if the orbit determination is successful, considering that the two are from the same target and obtaining an orbit determination result of double-arc angle measurement data; otherwise, both are considered to be from different targets.
The space debris double-arc angle measurement value integrated primary track and the related device comprise a readable and writable storage device which runs the method.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the invention in any way, and any person skilled in the art may make modifications or alterations to the disclosed technical content to the equivalent embodiments. However, any simple modification, equivalent variation and variation of the above embodiments according to the technical substance of the present invention still fall within the protection scope of the technical solution of the present invention.
Claims (9)
1. The utility model provides a space fragment double-arc angle measurement value integration is decided and is just rail and associated method which characterized in that: the method comprises the following steps:
s1, respectively carrying out initial track determination on two angle measurement short arc data of any space debris target without prior information to obtain two groups of initial track parameters;
s2, based on the track parameters of two groups of initial moments of different moments of the space debris target, selecting a plurality of decision moments of association judgment;
S3, respectively spreading the two groups of orbit parameters in the step S1 to a plurality of decision moments by using an orbit spreading method, and calculating three-dimensional space distance difference, semi-major axis difference, eccentricity difference and orbit plane difference of the two groups of orbit parameters at the selected decision moments;
S4, judging whether the three-dimensional space distance difference, the semi-major axis difference, the eccentricity difference, the track inclination difference, the included angle of the track surface and the radial difference of two groups of track parameters, the track direction difference and the track surface normal difference are all smaller than corresponding thresholds or not, and executing S5 if yes; otherwise, judging that the two groups of track parameters come from different space debris targets;
S5, propagating the tracks to a plurality of decision moments by utilizing a track propagation method, obtaining two groups of propagated track numbers, and calculating the difference of two groups of propagated track parameters at the same decision moment;
Judging whether the three-dimensional space distance difference, the semi-major axis difference, the eccentricity difference, the track inclination difference, the included angle of the track surface and the radial difference of two groups of track parameters, the track direction difference and the track surface normal difference are smaller than corresponding thresholds or not, and executing the step S6 if yes; if not, judging that the two are from different space debris targets;
replacing the semimajor axis and the inclination angle of the initial track according to the corrected semimajor axis and the track inclination angle of the track,
The method for correcting the semi-long axis and the track inclination angle of the tracks of two groups of track parameters at a plurality of decision moments comprises the following steps:
S5.1, calculating the orbit parameters or the three-dimensional space position and speed of the space debris target at the moment of determination by using an analytic orbit propagation method, and then calculating to obtain the position difference and the speed difference;
s5.2, converting the position difference and the speed difference in the step S5.1 into an initial radial difference, an initial track direction difference and an initial track surface normal difference of the track according to the three-dimensional position and the speed of the space debris target;
calculating the average moving speed and the average center distance of the space debris target at the decision time to obtain the semimajor axis and the track dip angle at the corrected decision time;
S5.3, taking the corrected semi-long axis of the orbit and the orbit inclination angle at the decision time as two groups of orbit parameters, and respectively spreading the two groups of orbit parameters to the semi-long axis and the orbit inclination angle at the decision time;
s5.4, repeating the steps S5.1-S5.3 for more than two times, and taking the last calculated difference along the track direction, the radial difference and the normal difference of the track surface as the difference along the track direction, the radial difference and the normal difference of the track surface of the two groups of track parameters at the decision moment;
S6, the corrected primary track semi-long axis and track inclination angle are utilized to replace the semi-long axis and track inclination angles of two groups of primary track parameters, corrected primary track positions and corrected primary track speed are obtained, observation arc section information corresponding to each primary track is determined, the distance between space fragments and the corresponding moment and between the corresponding stations is estimated according to station measurement information contained in the observation arc sections, and primary track determination is carried out on the two arc sections again by taking the distance as the initial distance of a distance searching method;
S7, if the two arc sections are successful in obtaining initial track parameters, repeating the steps S1 to S6 on the two groups of initial track parameters, and judging whether three-dimensional position differences, track semi-long axis differences, eccentricity differences, inclination angle differences, track surface differences and RIC differences of the two groups of track parameters at a plurality of decision moments are smaller than corresponding thresholds or not, if so, judging that the two groups of track parameters come from the same space debris target; if not, both are considered to be from different fragments;
S8, for two arc sections successfully associated, based on the initial track parameters of the two arc sections, simultaneously carrying out track fixing again by using the two arc sections, wherein a track fixing result is an integrated initial track fixing and association result of the two angle measuring arc sections; if the orbit determination is successful, considering that the two are from the same target and obtaining an orbit determination result of double-arc angle measurement data; otherwise, both are considered to be from different targets.
2. The spatial debris double-arc angle measurement value integrated primary rail and correlation method according to claim 1, wherein the method comprises the following steps: in step S1, the angle measurement value of the space debris target is the angle observation data of the very short arc, the initial orbit parameter is the initial orbit parameter of the angle observation data of the single very short arc, and the integrated initial orbit determination and association result is the combined association orbit determination result of the double-arc angle measurement data.
3. The spatial debris double-arc angle measurement value integrated primary rail and correlation method according to claim 1, wherein the method comprises the following steps: the orbit parameters in the step S1 comprise an orbit semi-long axis, an orbit eccentricity, an orbit inclination angle, an ascending intersection point right ascent, a near-place angular distance and a flat-near point angle, or an observation time corresponding to the three-dimensional space position, the speed and the orbit parameters of the space debris target in an inertial system.
4. The spatial debris double-arc angle measurement value integrated primary rail and correlation method according to claim 1, wherein the method comprises the following steps: the decision time in step S2 is the observation time corresponding to two sets of track parameters or any multiple times between the observation times corresponding to two sets of track parameters.
5. The spatial debris double-arc angle measurement value integrated primary rail and correlation method according to claim 1, wherein the method comprises the following steps: the decision time in step S2 is the intermediate time of the observation time corresponding to the two sets of track parameters and other decision times.
6. The spatial debris double-arc angle measurement value integrated primary rail and correlation method according to claim 1, wherein the method comprises the following steps: in step S3, the two sets of track parameters in step S1 are respectively propagated to a plurality of decision moments by using an analytical track propagation method.
7. The spatial debris double-arc angle measurement value integrated primary rail and correlation method according to claim 1, wherein the method comprises the following steps: in step S5, the semi-major axis and the track inclination angle of the two sets of track parameters at the decision time are corrected by using a cyclic method.
8. The spatial debris double-arc angle measurement value integrated primary rail and correlation method according to claim 1, wherein the method comprises the following steps: in step S6, the estimated distance between the station and the fragment is taken as the initial distance of the distance searching method, and the initial track determining method is carried out again for the two arc segments, which comprises the following steps:
S6.1, replacing the semimajor axis and the track inclination angles of the two groups of track parameters by using the corrected semimajor axis and the track inclination angles to obtain new corrected initial track parameters, positions and speeds;
S6.2, original observation data of the two arc segments which are being associated and calculated are determined, station measurement information of corresponding time is extracted, and the distance between the space debris and the station measurement at the corresponding time is estimated according to the station measurement information and the corrected track parameters;
s6.3, based on the distance between the space debris and the measuring station estimated in the step S6.2, using a distance searching method, taking the distance as an initial reference distance, and carrying out initial track determination on the two arc sections again;
And S6.4, if the initial track determination is successful, the step S7 is carried out, otherwise, the two are judged to be from different targets.
9. Space fragment double-arc angle measurement value integrated primary rail and associated device, characterized in that: storage device comprising a read-write capability, which operates the method of any of claims 1 to 8.
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| CN110002014A (en) * | 2019-03-21 | 2019-07-12 | 武汉大学 | A kind of space junk correlating method and medium |
| WO2021239732A1 (en) * | 2020-05-25 | 2021-12-02 | Airbus Defence And Space Sas | Method for estimating collision between at least one piece of space debris and a satellite |
| CN115837992A (en) * | 2022-11-25 | 2023-03-24 | 上海卫星工程研究所 | Space debris-oriented space-based optical observation initial orbit correlation method and system |
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| CN110002014A (en) * | 2019-03-21 | 2019-07-12 | 武汉大学 | A kind of space junk correlating method and medium |
| WO2021239732A1 (en) * | 2020-05-25 | 2021-12-02 | Airbus Defence And Space Sas | Method for estimating collision between at least one piece of space debris and a satellite |
| CN115837992A (en) * | 2022-11-25 | 2023-03-24 | 上海卫星工程研究所 | Space debris-oriented space-based optical observation initial orbit correlation method and system |
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