CN112835116B - Method and system for judging functions of geosynchronous orbit spin-stabilized spatial targets - Google Patents
Method and system for judging functions of geosynchronous orbit spin-stabilized spatial targets Download PDFInfo
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Abstract
The invention discloses a method and a system for judging functions of a spin-stabilized space target of a geosynchronous orbit, wherein the method comprises the following steps: step one: judging whether a foundation luminosity curve of the target has a sinusoidal structure, if not, preliminarily inverting the rotating speed of the target by using a phase dispersion minimization method, and then entering a step three; if the sinusoidal structure exists, the second step is entered; step two: judging whether a foundation luminosity curve of the target is continuous or the sampling rate is constant, and if the foundation luminosity curve is continuous and the sampling rate is constant, preliminarily inverting the target rotating speed by using discrete Fourier transform; if the foundation luminosity curve of the target is discontinuous or the sampling rate is not constant, preliminarily inverting the target rotating speed by using least square spectrum analysis; step three: checking a preliminary inversion result of the target rotating speed by using a phase folding method to obtain the actual rotating speed of the target; step four: and 3, judging the function of the target according to the actual rotation speed of the target in the step three. The invention effectively performs feature recognition on the GEO target.
Description
Technical Field
The invention belongs to the technical field of space target detection and identification, and particularly relates to a method and a system for judging functions of a spin-stabilized space target of a geosynchronous orbit.
Background
The foundation optical observation system is influenced by atmosphere, distance and self resolution, and is difficult to image high-resolution on high-orbit space targets such as geosynchronous orbit (Geostationary Earth Orbit, GEO) targets and the like, and can only present light spots with brightness variation of a few pixels. At present, the foundation optical observation system can only give out the position, speed and brightness information of the target, and no effective means is available for carrying out feature recognition on the GEO target. Therefore, the problem that a large amount of time-efficient data is not effectively utilized and the data is not converted into effective information is caused, although the foundation telescope acquires a large amount of photometric data.
Disclosure of Invention
The invention solves the technical problems that: the method and the system for judging the functions of the geosynchronous orbit spin stable space target are provided to overcome the defects of the prior art, and the GEO target is effectively identified.
The invention aims at realizing the following technical scheme: a method for determining a geosynchronous orbit spin-stabilized spatial target function, the method comprising the steps of: step one: judging whether a foundation luminosity curve of the target has a sinusoidal structure, if not, preliminarily inverting the rotating speed of the target by using a phase dispersion minimization method, and then entering a step three; if the sinusoidal structure exists, the second step is entered; step two: judging whether a foundation luminosity curve of the target is continuous or the sampling rate is constant, if so, preliminarily inverting the target rotating speed by using discrete Fourier transform, and then entering a step III; if the foundation luminosity curve of the target is discontinuous or the sampling rate is not constant, performing preliminary inversion on the target rotating speed by using least square spectrum analysis, and then entering a step III; step three: checking a preliminary inversion result of the target rotating speed by using a phase folding method to obtain the actual rotating speed of the target; step four: and 3, judging the function of the target according to the actual rotation speed of the target in the step three.
In the above-mentioned geosynchronous orbit spin-stabilized spatial target function determination method, in the fourth step, the actual rotation speed of the target is 6 rpm which is a warning satellite, the actual rotation speed of the target is 50 rpm which is a communication satellite, the actual rotation speed of the target is 100 rpm which is a weather satellite, and the other rotation speeds are space debris.
In the above-described geosynchronous orbit spin-stabilized spatial target function determination method, in step two, the discrete fourier transform includes:
presetting x (n) as a finite length sequence, namely:
the discrete fourier transform of x (n) is then:
wherein ,
n is the number of transform points, N is the length of the discrete Fourier transform interval, X (k) is the discrete Fourier transform of the finite length sequence X (N), k represents the kth point of the Fourier transform, W N Is an intermediate variable.
In the above-mentioned geosynchronous orbit spin stabilization spatial target function determination method, in the second step, the least squares spectrum analysis is implemented by calculating a Lomb-Scargle periodic chart, including:
the preset observation time number is M and time t i The corresponding observed value is h i The observed value mean and observed value variance are:
the time delay τ is defined as:
the Lomb-Scargle cycle chart is:
wherein ,
for the mean value of the observed values, i is the number of the observed time, sigma is the variance of the observed value, tau is the time delay, P N (ω) is a Lomb-Scargle periodic chart.
A geosynchronous orbit spin-stabilized spatial target function determination system, comprising: the first module is used for judging whether a foundation luminosity curve of the target has a sinusoidal structure, and if the foundation luminosity curve does not have the sinusoidal structure, preliminarily inverting the rotating speed of the target by using a phase dispersion minimization method; the second module is used for judging whether the foundation luminosity curve of the target is continuous or the sampling rate is constant, and if the foundation luminosity curve is continuous and the sampling rate is constant, the discrete Fourier transformation is used for preliminarily inverting the target rotating speed; if the foundation luminosity curve of the target is discontinuous or the sampling rate is not constant, preliminarily inverting the target rotating speed by using least square spectrum analysis; the third module is used for verifying the preliminary inversion result of the target rotating speed by using a phase folding method to obtain the actual rotating speed of the target; and a fourth module for judging the function of the target according to the actual rotation speed of the target in the third module.
In the above-mentioned geosynchronous orbit spin-stabilized space target function judging system, the actual rotation speed of the target is 6 rpm which is an early warning satellite, the actual rotation speed of the target is 50 rpm which is a communication satellite, the actual rotation speed of the target is 100 rpm which is a meteorological satellite, and the other rotation speeds are space debris.
In the above-described geosynchronous orbit spin-stabilized spatial target function determination system, the discrete fourier transform includes:
presetting x (n) as a finite length sequence, namely:
the discrete fourier transform of x (n) is then:
wherein ,
n is the number of transform points, N is the length of the discrete Fourier transform interval, X (k) is the discrete Fourier transform of the finite length sequence X (N), k represents the kth point of the Fourier transform, W N Is an intermediate variable.
In the above-mentioned geosynchronous orbit spin stabilization spatial target function determination system, the least square spectrum analysis is realized by calculating a Lomb-Scargle periodic chart, comprising:
the preset observation time number is M and time t i The corresponding observed value is h i The observed value mean and observed value variance are:
the time delay τ is defined as:
the Lomb-Scargle cycle chart is:
wherein ,
for the mean value of the observed values, i is the number of the observed time, sigma is the variance of the observed value, tau is the time delay, P N (ω) is a Lomb-Scargle periodic chart.
Compared with the prior art, the invention has the following beneficial effects:
(1) The invention is beneficial to improving the application benefit of foundation luminosity data. Currently, although the ground telescope acquires a huge amount of photometric data, a large amount of data with timeliness is not effectively utilized, and the data is not converted into effective information. The purpose of photometric observation is to identify the target, and the invention can break the gap between the characteristics of the spin-stabilized GEO target and photometric data, and convert the photometric data into knowledge "gold blocks".
(2) The invention is helpful for improving the observation capability of the foundation optical system. Because of the influence of distance and atmosphere, the object recognition difficulty of the foundation optical observation system on the high-orbit space is high, the traditional detection means and method cannot meet the requirements more and more, and the equipment transformation or development is a process with a longer period.
(3) The invention can provide new clues for space application such as space target threat assessment and the like. The invention can judge the function of the GEO spin-stabilized target based on the foundation luminosity data, and has important significance for solving the target threat assessment problem in space situation awareness.
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Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to designate like parts throughout the figures. In the drawings:
FIG. 1 is a flowchart of a method for determining a function of a geosynchronous orbit spin-stabilized spatial target according to an embodiment of the present invention;
FIG. 2 is a schematic illustration of a foundation luminosity curve of a spin-stabilized GEO target provided by an embodiment of the invention;
FIG. 3 is a schematic representation of discrete Fourier transform results of a baseline luminosity curve provided by an embodiment of the present invention;
FIG. 4 is a schematic diagram of the phase folding result of the photometric curve at a 4.17s folding period provided by the present embodiment;
FIG. 5 is a schematic diagram of the phase folding result of the photometric curve at the 8.34s folding period provided by the embodiment of the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
The photometric characteristics of a spatial object generally refer to the change in observed luminance of the object over time, and are commonly measured as constants by photometric curves. The luminosity curve is a time-varying curve of the target brightness observed by an observer, and the target brightness is generally represented by a star or the like. Since the target view, etc., is a function of the characteristics of the target size, orientation, and surface properties, etc., these characteristics can be inverted from the photometric curve.
GEO targets typically exhibit a certain regularity in the time domain in their photometric curve due to geostationary. GEO targets have mainly two stabilization modes, spin stabilization and triaxial stabilization, wherein the photometric curve of the spin stabilization target has a certain periodicity, and the periodicity does not substantially change with time. The period of the spin-stabilized target photometric curve is independent of the shape of the target itself, and is only related to the actual rotation period of the target, which is generally equal to the photometric curve period of the target or 2 times the photometric curve period.
Fig. 1 is a flowchart of a method for determining a geosynchronous orbit spin-stabilized spatial target function according to an embodiment of the present invention. As shown in fig. 1, the method comprises the steps of:
step one: judging whether a foundation luminosity curve of the target has a sinusoidal structure, if not, preliminarily inverting the rotating speed of the target by using a phase dispersion minimization method, and then entering a step three; if the sinusoidal structure exists, the second step is entered;
step two: judging whether a foundation luminosity curve of the target is continuous or the sampling rate is constant, if so, preliminarily inverting the target rotating speed by using discrete Fourier transform, and then entering a step III; if the foundation luminosity curve of the target is discontinuous or the sampling rate is not constant, performing preliminary inversion on the target rotating speed by using least square spectrum analysis, and then entering a step III;
step three: checking a preliminary inversion result of the target rotating speed by using a phase folding method to obtain the actual rotating speed of the target;
step four: and 3, judging the function of the target according to the actual rotation speed of the target in the step three.
In the fourth step, the actual rotation speed of the target is 6 rpm and is an early warning satellite, the actual rotation speed of the target is 50 rpm and is a communication satellite, the actual rotation speed of the target is 100 rpm and is a meteorological satellite, and other rotation speeds are space debris.
Preliminary inversion of spin-stabilized GEO target rotational speed. Inversion is carried out on a photometric curve with continuous sampling and constant sampling rate by using discrete Fourier transform; inversion is performed using least squares spectral analysis for ray curves with non-constant sampling rates or with gaps; for photometric curves with non-sinusoidal structures that cannot be well processed by fourier transforms and least squares spectral analysis, inversion is performed using a phase dispersion minimization technique.
And (5) checking the spin-stabilized GEO target rotating speed. The actual spin period of the target is determined using the phase folding. Unlike the principles of discrete fourier transform, least squares spectral analysis, the frequency components calculated by phase dispersion minimization may not be the higher specific gravity frequency components in the photometric curve. In addition, even if the largest frequency component in the spectrum is determined, the component is not necessarily equal to the actual rotation frequency of the target. In order to determine the actual rotation frequency of the target, it is ensured that the frequency components obtained by discrete fourier transform, least squares spectral analysis and phase dispersion minimization correspond to the photometric curve characteristics, and the photometric curve period is verified by a phase folding method.
Functional determination of spin-stabilized GEO target. Based on the inversion of the target rotating speed, the function of the GEO target is further judged based on the correlation between the target spin period and the target function.
The specific implementation method of the technical links of discrete Fourier transform, least square spectrum analysis, phase dispersion minimization, phase folding, GEO target spin period, function association analysis and the like related by the invention comprises the following steps:
1) Discrete fourier transform
For a continuous sampling and constant sampling rate photometric curve, discrete fourier transform may be used to transform the discrete sampled time domain photometric curve into a power spectrum of each frequency component of the curve, thereby identifying the photometric curve period. Let x (n) be the finite length sequence, namely:
the discrete fourier transform of x (n) is then
wherein ,
2) Least squares spectral analysis
In the case of a light curve with a non-constant sampling rate or gap, a least squares spectral analysis may be used to generate a power spectrum of the photometric curve. The method is similar to Fourier analysis, is a method for estimating the frequency spectrum based on least square fitting of a sinusoidal curve and data samples, and can identify the frequency of a periodic signal hidden in non-equidistant sampling data. The least square spectrum analysis can be realized by calculating a Lomb-Scargle periodic chart, and the number of observation moments is assumed to be M and t i The corresponding observed value is h i The observed value mean and observed value variance are:
the time delay τ is defined as:
the Lomb-Scargle cycle chart is:
3) Phase dispersion minimization
For photometric curves with non-sinusoidal structures that do not process well with fourier transforms and least squares spectra, phase dispersion minimization techniques can be used to determine the curve period. The analysis code with minimized phase dispersion can be obtained in the http:// www.stellingwerf.com/rfs-bin/index. Cgaction=pageview & id=29 website open. The method retrieves all possible periods in the curve. During the retrieval process, the entire photometric curve is divided into several parts according to the test cycle and these parts are stacked on top of each other. Thereafter, the stacked data is further subdivided into a series of data boxes. The variance of all data in these bins is calculated and compared to the total variance of the data set to produce a value between 0 and 1. Where 0 indicates the best match and 1 indicates the least match.
4) Phase folding
The frequency components calculated for minimizing phase dispersion may not be the higher specific gravity frequency components in the photometric curve. In addition, even if the largest frequency component in the spectrum is determined, the component is not necessarily equal to the actual rotation frequency of the target. In order to determine the actual rotation frequency of a target and ensure that frequency components obtained through discrete Fourier transform, least square spectrum analysis and phase dispersion minimization correspond to the characteristics of a photometric curve, the invention uses the idea of phase dispersion minimization to verify the period of the photometric curve through phase folding.
5) GEO target spin cycle and functional association analysis
The analysis is carried out based on open source databases such as UCS satellite database, STK software satellite database and the like, and 554 GEO targets still working in orbit worldwide are totally obtained by 1 month 4 in 2020. Among them, spin stabilization targets were 14 in total, as shown in table 1. The rotating speed of the GEO spin stabilization target and the functions thereof have extremely strong relevance, the rotating speed of the early warning satellite is 6 rpm, the rotating speed of the communication satellite is 50 rpm, and the rotating speed of the meteorological satellite is 100 rpm.
The embodiment of the invention provides an example for judging the function of a GEO spin stabilization target based on foundation luminosity data. In this embodiment, taking the foundation luminosity curve of a certain spin-stabilized GEO target as shown in fig. 2 as an example, the determination process and result of the target function are described according to the method proposed in this patent, and the method specifically includes the following steps:
step one, preliminarily determining the rotating speed of the spin-stabilized GEO target. Firstly, a proper target rotating speed inversion method is selected according to the characteristics of a luminosity curve, and whether the luminosity curve is continuously sampled or not and whether the sampling rate is constant or not can influence the selection of the inversion method. For the photometric curve shown in fig. 1, the sampling is continuous and the sampling rate is constant, so the target rotation speed inversion is performed using the discrete fourier transform, and the result is shown in fig. 3. It can be seen that the peak is maximum at a frequency of 0.24Hz, and there is also a peak at 0.12Hz, with the two frequencies being exactly twice as many. Since the actual rotation period of the target is equal to the target photometric curve period or 2 times the photometric curve period, it can be inferred that the actual rotation period of the target at this time is 4.17 seconds or 8.34 seconds, and the rotation speed is 14.4 rpm or 7.2 rpm.
TABLE 1 Global on-orbit working GEO spin-stabilization target information
And step two, checking the spin-stabilized GEO target rotating speed. Through the first step, the target rotation speed can be determined to be 14.4 rpm or 7.2 rpm, the target rotation frequency is assumed to be 0.24Hz, the corresponding period is 4.17s, the photometric curve is phase folded and normalized based on the period, and the folding result of the photometric curve in a period can be obtained as shown in fig. 4. From the graph, two peak amplitudes of the folded data are about 0.4 and 0.9, respectively, which indicates that 4.17s is half of the target actual period. Assuming a rotation period of 8.34s for the target, the photometric curve is phase-folded based on this period, and the result is shown in fig. 5. As can be seen from the figure, the fold data of each part substantially coincides within one cycle, so 8.34s is closer to the rotation cycle of the target, and the actual rotation speed of the target should be 7.2 rpm.
And thirdly, judging the function of the spin-stabilized GEO target. Through the second step, the rotation speed of the target is 7.2 rpm, and based on the correlation between the spin period of the GEO target and the target function shown in table 1, it is known that the target is not a weather satellite, a communication satellite or an early warning satellite, and thus it can be determined that the target is a space debris.
The embodiment also provides a geosynchronous orbit spin stabilization space target function judging system, which comprises: the first module is used for judging whether a foundation luminosity curve of the target has a sinusoidal structure, and if the foundation luminosity curve does not have the sinusoidal structure, preliminarily inverting the rotating speed of the target by using a phase dispersion minimization method; the second module is used for judging whether the foundation luminosity curve of the target is continuous or the sampling rate is constant, and if the foundation luminosity curve is continuous and the sampling rate is constant, the discrete Fourier transformation is used for preliminarily inverting the target rotating speed; if the foundation luminosity curve of the target is discontinuous or the sampling rate is not constant, preliminarily inverting the target rotating speed by using least square spectrum analysis; the third module is used for verifying the preliminary inversion result of the target rotating speed by using a phase folding method to obtain the actual rotating speed of the target; and a fourth module for judging the function of the target according to the actual rotation speed of the target in the third module.
The invention is beneficial to improving the application benefit of foundation luminosity data. Currently, although the ground telescope acquires a huge amount of photometric data, a large amount of data with timeliness is not effectively utilized, and the data is not converted into effective information. The purpose of photometric observation is to identify the target, and the invention can break the gap between the characteristics of the spin-stabilized GEO target and photometric data, and convert the photometric data into knowledge "gold blocks".
The invention is helpful for improving the observation capability of the foundation optical system. Because of the influence of distance and atmosphere, the object recognition difficulty of the foundation optical observation system on the high-orbit space is high, the traditional detection means and method cannot meet the requirements more and more, and the equipment transformation or development is a process with a longer period.
The invention can provide new clues for space application such as space target threat assessment and the like. The invention can judge the function of the GEO spin-stabilized target based on the foundation luminosity data, and has important significance for solving the target threat assessment problem in space situation awareness.
Although the present invention has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the methods and technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present invention are within the scope of the technical matters of the present invention.
Claims (8)
1. A method for determining a function of a geosynchronous orbit spin-stabilized spatial target, the method comprising the steps of:
step one: judging whether a foundation luminosity curve of the target has a sinusoidal structure, if not, preliminarily inverting the rotating speed of the target by using a phase dispersion minimization method, and then entering a step three; if the sinusoidal structure exists, the second step is entered;
step two: judging whether a foundation luminosity curve of the target is continuous or the sampling rate is constant, if so, preliminarily inverting the target rotating speed by using discrete Fourier transform, and then entering a step III; if the foundation luminosity curve of the target is discontinuous or the sampling rate is not constant, performing preliminary inversion on the target rotating speed by using least square spectrum analysis, and then entering a step III;
step three: checking a preliminary inversion result of the target rotating speed by using a phase folding method to obtain the actual rotating speed of the target;
step four: and 3, judging the function of the target according to the actual rotation speed of the target in the step three.
2. The geosynchronous orbit spin-stabilized spatial target function determination method according to claim 1, wherein: in the fourth step, the actual rotation speed of the target is 6 rpm and is an early warning satellite, the actual rotation speed of the target is 50 rpm and is a communication satellite, the actual rotation speed of the target is 100 rpm and is a meteorological satellite, and other rotation speeds are space debris.
3. The geosynchronous orbit spin-stabilized spatial target function determination method according to claim 1, wherein: in step two, the discrete fourier transform includes:
presetting x (n) as a finite length sequence, namely:
the discrete fourier transform of x (n) is then:
wherein ,
n is the number of transform points, N is the length of the discrete Fourier transform interval, X (k) is the discrete Fourier transform of the finite length sequence X (N), k represents the kth point of the Fourier transform, W N Is an intermediate variable.
4. The geosynchronous orbit spin-stabilized spatial target function determination method according to claim 1, wherein: in the second step, the least square spectrum analysis is realized by solving a Lomb-Scargle periodic chart, which comprises the following steps:
the preset observation time number is M and time t i The corresponding observed value is h i The observed value mean and observed value variance are:
the time delay τ is defined as:
the Lomb-Scargle cycle chart is:
wherein ,
for the mean value of the observed values, i is the number of the observed time, sigma is the variance of the observed value, tau is the time delay, P N (ω) is a Lomb-Scargle periodic chart.
5. A geosynchronous orbit spin-stabilized spatial target function determination system, comprising:
the first module is used for judging whether a foundation luminosity curve of the target has a sinusoidal structure, and if the foundation luminosity curve does not have the sinusoidal structure, preliminarily inverting the rotating speed of the target by using a phase dispersion minimization method;
the second module is used for judging whether the foundation luminosity curve of the target is continuous or the sampling rate is constant, and if the foundation luminosity curve is continuous and the sampling rate is constant, the discrete Fourier transformation is used for preliminarily inverting the target rotating speed; if the foundation luminosity curve of the target is discontinuous or the sampling rate is not constant, preliminarily inverting the target rotating speed by using least square spectrum analysis;
the third module is used for verifying the preliminary inversion result of the target rotating speed by using a phase folding method to obtain the actual rotating speed of the target;
and a fourth module for judging the function of the target according to the actual rotation speed of the target in the third module.
6. The geosynchronous orbit spin-stabilized spatial target function determination system according to claim 5, wherein: the actual rotation speed of the target is 6 rpm which is an early warning satellite, the actual rotation speed of the target is 50 rpm which is a communication satellite, the actual rotation speed of the target is 100 rpm which is a meteorological satellite, and the other rotation speeds are space debris.
7. The geosynchronous orbit spin-stabilized spatial target function determination system according to claim 5, wherein: the discrete fourier transform includes:
presetting x (n) as a finite length sequence, namely:
the discrete fourier transform of x (n) is then:
wherein ,
n is the number of transform points, N is the length of the discrete Fourier transform interval, X (k) is the discrete Fourier transform of the finite length sequence X (N), k represents the kth point of the Fourier transform, W N Is an intermediate variable.
8. The geosynchronous orbit spin-stabilized spatial target function determination system according to claim 5, wherein: the least square spectrum analysis is realized by solving a Lomb-Scargle periodic chart, and comprises the following steps:
the preset observation time number is M and time t i The corresponding observed value is h i The observed value mean and observed value variance are:
the time delay τ is defined as:
the Lomb-Scargle cycle chart is:
wherein ,
for the mean value of the observed values, i is the number of the observed time, sigma is the variance of the observed value, tau is the time delay, P N (ω) is a Lomb-Scargle periodic chart. />
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| US8767210B1 (en) * | 2012-05-08 | 2014-07-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method for ground-to-space laser calibration system |
| CN108627667A (en) * | 2018-05-15 | 2018-10-09 | 中国人民解放军战略支援部队航天工程大学 | Based on luminosity sequence while estimation space unstability target precession and spin rate method |
| CN108876846A (en) * | 2018-06-05 | 2018-11-23 | 中国科学院国家天文台 | A kind of satellite body size computing method based on light curve |
| CN111428365A (en) * | 2020-03-24 | 2020-07-17 | 中国人民解放军32035部队 | Method for distinguishing GEO target by using astronomical measurement data |
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| US8240611B2 (en) * | 2009-08-26 | 2012-08-14 | Raytheon Company | Retro-geo spinning satellite utilizing time delay integration (TDI) for geosynchronous surveillance |
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| CN108627667A (en) * | 2018-05-15 | 2018-10-09 | 中国人民解放军战略支援部队航天工程大学 | Based on luminosity sequence while estimation space unstability target precession and spin rate method |
| CN108876846A (en) * | 2018-06-05 | 2018-11-23 | 中国科学院国家天文台 | A kind of satellite body size computing method based on light curve |
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