CN112800169B - Data matching method, device and equipment for synchronous belt satellite and storage medium - Google Patents
Data matching method, device and equipment for synchronous belt satellite and storage medium Download PDFInfo
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Abstract
The embodiment of the application provides a data matching method, a data matching device, data matching equipment and a data matching storage medium for a synchronous belt satellite, and relates to the technical field of synchronous satellites. The method comprises the following steps: acquiring optical observation data of a synchronous belt satellite; generating a synchronous belt virtual satellite orbit according to the optical observation data, and acquiring a rising point right ascension of the synchronous belt virtual satellite orbit; carrying out iterative processing on the synchronous belt virtual satellite orbit and the ascension point right ascension to obtain the fixed point longitude of the optical observation data; obtaining the right ascension variation of the earth rotation according to the fixed point longitude and the preset fixed time; drawing a scatter diagram of a two-dimensional coordinate system according to the fixed point longitude and the right ascension variation; and performing linear fitting on the scatter diagram to obtain a fitting curve, wherein coordinate points on the fitting curve are a result set matched by the synchronous belt satellite. The method can achieve the technical effect of improving the success rate of synchronous belt satellite matching correlation.
Description
Technical Field
The present disclosure relates to the field of synchronous satellite technologies, and in particular, to a data matching method, apparatus, device, and storage medium for a synchronous satellite.
Background
At present, the geostationary satellite has a very close relationship with the production and life of human beings; the geostationary satellite is a satellite having an operation cycle identical to a planetary rotation cycle or an orbital plane rotation angular velocity substantially equal to a planetary revolution angular velocity. Geostationary satellites are generally divided into geostationary satellites and sun-synchronized satellites, and the geostationary satellites with the same satellite revolution period and earth rotation period are called geostationary satellites and also called 24-hour geostationary satellites; the rotation angular velocity of the satellite orbital plane is almost equal to the angular velocity of the earth revolving around the sun, and is called a sun synchronous satellite. The synchronous belt is a satellite belt formed by 3 ten thousand (6) kilometers above the equator of the earth and encircling the earth, and geostationary satellites encircle the earth at intervals of 2-3 degrees on the synchronous belt.
In the prior art, a common method for space-based optical matching identification of synchronous belt satellites at present is to acquire the number of orbits by 'initial orbit determination', and then perform matching association between each two orbits by the number of orbits. The 'initial orbit determination' is a key for synchronous belt satellite matching association, but in practical application, after the data of the short arc section is calculated through the initial orbit determination, the obtained error ratio is large, even the number of the tracks can not be obtained, so that the success rate of pairwise matching association is low, and the effect in practical application is not obvious.
Disclosure of Invention
The embodiment of the application aims to provide a data matching method, a data matching device, data matching equipment and a data matching storage medium for synchronous belt satellites, which can reduce calculation errors, accurately acquire the number of orbits and achieve the technical effect of improving the success rate of synchronous belt satellite matching correlation.
In a first aspect, an embodiment of the present application provides a data matching method for a synchronous belt satellite, including:
acquiring optical observation data of a synchronous belt satellite;
generating a synchronous belt virtual satellite orbit according to the optical observation data, and acquiring a rising point right ascension of the synchronous belt virtual satellite orbit;
carrying out iterative processing on the synchronous belt virtual satellite orbit and the ascension point right ascension to obtain the fixed point longitude of the optical observation data;
obtaining the right ascension variation of the earth rotation according to the fixed point longitude and the preset fixed time;
drawing a scatter diagram of a two-dimensional coordinate system according to the fixed point longitude and the right ascension variation;
and performing linear fitting on the scatter diagram to obtain a fitting curve, wherein coordinate points on the fitting curve are a result set matched by the synchronous belt satellite.
In the implementation process, the data matching method of the synchronous belt satellite avoids the fundamental problems of difficult orbit determination and large deviation of short arc section data, generates a synchronous belt virtual satellite orbit through optical observation data of the synchronous belt satellite, calculates the virtual position according to the synchronous belt virtual satellite orbit, namely calculates the ascent point right ascension, the fixed point longitude, the ascent point variable quantity and the like, so as to obtain the three-point sub-satellite point position, corrects the standard orbit through the fixed point longitude of the sub-satellite point, obtains a new sub-satellite point longitude, converts the complex initial orbit determination calculation into simple geometric relation mapping, calculates the sub-satellite point position of the current data arc section, and greatly improves the calculation efficiency; and finally fitting according to a scatter diagram drawn by the fixed point longitude and the right ascension variation to further obtain a synchronous belt satellite matching result. Therefore, the method can reduce the calculation error and accurately acquire the number of the orbits, and achieves the technical effect of improving the success rate of the synchronous belt satellite matching association.
Further, after the step of acquiring the optical observation data of the synchronous belt satellite, the method further includes:
and denoising the optical observation data based on a 3 sigma criterion of normal distribution.
In the implementation process, the optical observation data is denoised according to the 3 sigma criterion, so that data of a noise point and a noise point in the optical observation data are removed, the quality of the optical observation data can be effectively improved, and the accuracy of a data matching result is improved.
Further, before the step of generating a synchronous belt virtual satellite orbit according to the optical observation data, the method further includes:
calculating the position of the measuring station in a J2000 inertial coordinate system to obtain the position information of the measuring station;
and respectively calculating the fixed point longitudes of the starting time, the middle time and the ending time of the optical observation data according to the position information of the observation station and the preset space-based platform measuring distance to obtain a fixed point longitude average value and a fixed point longitude interval.
In the implementation process, the maximum value and the minimum value of the measuring distance of the space-based platform are respectively the semimajor axis of the synchronous track belt and the semimajor axis of the space-based platform, and the semimajor axis of the synchronous track belt and the semimajor axis of the space-based platform; then, the fixed point longitudes of the start time, the middle time and the end time of the optical observation data are respectively calculated, and the average value of the fixed point longitudes and the fixed point longitude interval are obtained.
Further, the step of generating a synchronous belt virtual satellite orbit according to the optical observation data and acquiring a rising point right ascension of the synchronous belt virtual satellite orbit includes:
setting the initial epoch time of the synchronous belt virtual satellite orbit according to the observation optical data;
calculating the fixed point longitude of the initial epoch moment;
and calculating the fixed point longitude average value and the fixed point longitude at the initial epoch moment to obtain the ascent point right ascension of the synchronous belt virtual satellite orbit.
In the implementation process, a synchronous belt virtual satellite orbit is generated according to the optical observation data, wherein the semi-major axis of the synchronous belt virtual satellite orbit is 42165200 meters, the initial epoch is the starting time of the space-based observation optical data, and the eccentricity, the inclination angle, the ascension point, the ascension angle of the ascending intersection point, the amplitude angle of the near place and the average near point angle are all 0; calculating the fixed point longitude of the initial epoch moment; and subtracting the fixed point longitude obtained at the initial epoch time from the average value of the fixed point longitude, and performing modulo operation to obtain the ascent point right ascension of the new track.
Further, the step of obtaining the right ascension variation of the earth rotation according to the fixed point longitude and a preset fixed time includes:
calculating a difference value between the preset fixed time and the starting moment of the optical observation data to obtain a relative time difference;
and calculating the relative time difference, the degree of the earth rotation and the fixed point longitude to obtain the right ascension variation of the earth rotation.
In the implementation process, setting fixed time, and calculating the relative time difference between the starting time point of the optical observation data and the starting time point of the optical observation data; the relative time difference is multiplied by 360.9865 (degrees of earth rotation per day), then the fixed point longitude is added, and the change of the right ascension channel of the earth rotation in the elimination time is obtained by taking the modulus.
In a second aspect, an embodiment of the present application provides a data matching apparatus for a synchronous belt satellite, including:
the acquisition module is used for acquiring optical observation data of the synchronous belt satellite;
the generating module is used for generating a synchronous belt virtual satellite orbit according to the optical observation data and acquiring the ascent point right ascension of the synchronous belt virtual satellite orbit;
the iteration module is used for performing iteration processing on the synchronous belt virtual satellite orbit and the ascension point right ascension to obtain the fixed point longitude of the optical observation data;
the right ascension computing module is used for obtaining the right ascension variable quantity of the earth rotation according to the fixed-point longitude and the preset fixed time;
the drawing module is used for drawing a scatter diagram of a two-dimensional coordinate system according to the fixed point longitude and the right ascension variation;
and the fitting module is used for performing linear fitting according to the scatter diagram to obtain a fitting curve, and coordinate points on the fitting curve are a result set matched by the synchronous belt satellite.
Further, the apparatus further comprises: and the preprocessing module is used for preprocessing the optical observation data based on a 3 sigma criterion of normal distribution so as to remove noise and noise in the optical observation data.
Further, the apparatus further comprises:
the position calculation module is used for calculating the position of the measuring station in a J2000 inertial coordinate system to obtain the position information of the measuring station;
and the fixed point longitude calculation module is used for respectively calculating the fixed point longitudes of the starting time, the middle time and the ending time of the optical observation data according to the position information of the observation station and the preset space-based platform measuring distance to obtain a fixed point longitude average value and a fixed point longitude interval.
Further, the generating module includes:
the setting unit is used for setting the initial epoch time of the synchronous belt virtual satellite orbit according to the observation optical data;
the first calculation unit is used for calculating the fixed point longitude of the initial epoch time;
and the second calculation unit is used for calculating the fixed point longitude average value and the fixed point longitude at the initial epoch moment to obtain the ascent point right ascension of the synchronous belt virtual satellite orbit.
Further, the right ascension calculation module includes:
the third calculating unit is used for calculating the difference value between the preset fixed time and the starting moment of the optical observation data to obtain a relative time difference;
and the fourth calculating unit is used for calculating the relative time difference, the degree of the earth rotation and the fixed point longitude to obtain the right ascension variation of the earth rotation.
In a third aspect, an apparatus provided in an embodiment of the present application includes: memory, a processor and a computer program stored in the memory and executable on the processor, the processor implementing the steps of the method according to any of the first aspect when executing the computer program.
In a fourth aspect, a storage medium is provided in an embodiment of the present application, where the storage medium has instructions stored thereon, and when the instructions are executed on a computer, the instructions cause the computer to perform the method according to any one of the first aspect.
In a fifth aspect, embodiments of the present application provide a computer program product, which when run on a computer, causes the computer to perform the method according to any one of the first aspect.
Additional features and advantages of the disclosure will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by the practice of the above-described techniques.
In order to make the aforementioned objects, features and advantages of the present application more comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments of the present application will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and that those skilled in the art can also obtain other related drawings based on the drawings without inventive efforts.
Fig. 1 is a schematic flowchart of a data matching method for a synchronous belt satellite according to an embodiment of the present disclosure;
fig. 2 is a schematic flowchart of another data matching method for a synchronous belt satellite according to an embodiment of the present disclosure;
fig. 3 is a schematic structural diagram of a data matching device for a synchronous belt satellite according to an embodiment of the present disclosure;
fig. 4 is a schematic structural diagram of another data matching device for a synchronous belt satellite according to an embodiment of the present application;
fig. 5 is a schematic structural diagram of a generating module provided in the embodiment of the present application;
fig. 6 is a schematic structural diagram of a right ascension calculation module according to an embodiment of the present application;
fig. 7 is a block diagram of a device according to an embodiment of the present disclosure.
Detailed Description
The technical solutions in the embodiments of the present application will be described below with reference to the drawings in the embodiments of the present application.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures. Meanwhile, in the description of the present application, the terms "first", "second", and the like are used only for distinguishing the description, and are not to be construed as indicating or implying relative importance.
The embodiment of the application provides a data matching method, a data matching device, data matching equipment and a data matching storage medium for synchronous belt satellites, and the data matching method, the data matching device, the data matching equipment and the data matching storage medium can be applied to matching correlation of the synchronous belt satellites; the data matching method of the synchronous belt satellite avoids the fundamental problems of difficult short arc section data orbit determination and large deviation, generates a synchronous belt virtual satellite orbit through optical observation data of the synchronous belt satellite, calculates a virtual position according to the synchronous belt virtual satellite orbit, namely calculates rising point right ascension, fixed point longitude, right ascension variation and the like, thereby obtaining a three-point sub-satellite point position, corrects a standard orbit through the fixed point longitude of the sub-satellite point, obtains new sub-satellite point longitude, converts complex initial orbit determination calculation into simple geometric relation mapping, calculates the sub-satellite point position of the current data arc section, and greatly improves the calculation efficiency; and finally fitting according to a scatter diagram drawn by the fixed point longitude and the right ascension variation to further obtain a synchronous belt satellite matching result. Therefore, the method can reduce the calculation error and accurately acquire the number of the orbits, and achieves the technical effect of improving the success rate of the synchronous belt satellite matching association.
Referring to fig. 1, fig. 1 is a schematic flow chart of a data matching method for a synchronous belt satellite according to an embodiment of the present application, where the data matching method for the synchronous belt satellite includes the following steps:
s100: and acquiring optical observation data of the synchronous belt satellite.
Exemplarily, the synchronous belt satellite can be used as a space-based observation platform to acquire optical observation data; analyzing the optical observation data can respectively obtain the time information, and the right ascension data and the declination data corresponding to the time information.
In some embodiments, the station related information may be obtained from a station address file of the station.
S200: and generating a synchronous belt virtual satellite orbit according to the optical observation data, and acquiring the ascent point right ascension of the synchronous belt virtual satellite orbit.
Exemplarily, the ascension point right ascension is an angular distance between the ascension point and the spring equinox of the satellite orbit; wherein the intersection point is the intersection point with the earth equatorial plane when the satellite runs from south to north; on the contrary, the other intersection point of the orbital plane and the equatorial plane is called a descending intersection point, and the vernality point is the intersection point of the ecliptic plane and the equatorial plane on the celestial sphere.
S300: and (4) carrying out iterative processing on the synchronous belt virtual satellite orbit and the ascent point right ascension to obtain the fixed point longitude of the optical observation data.
In some embodiments, the position of the observation point can be calculated through orbit prediction of the synchronous belt virtual satellite orbit, and the distance R between the observation station and the observation point is obtained; and calculating the fixed point longitude by using the distance R and the observation station position at the observation time, wherein the fixed point longitude can be used for correcting the standard orbit, and repeating the steps to obtain the fixed point longitude (Lon 3) of the optical observation data through a plurality of iterative calculations.
S400: and obtaining the right ascension variation of the earth rotation according to the fixed point longitude and the preset fixed time.
S500: and drawing a scatter diagram of the two-dimensional coordinate system according to the fixed point longitude and the right ascension variation.
Exemplarily, a two-dimensional coordinate system scatter diagram is drawn, and the abscissa is set as the fixed point longitude and the ordinate is the right ascension variation; and inputting the data in the fixed point longitude and the right ascension variation into a coordinate system, and drawing to obtain a scatter diagram of the two-dimensional coordinate system.
S600: and performing linear fitting on the scatter diagram to obtain a fitting curve, wherein coordinate points on the fitting curve are a result set of synchronous belt satellite matching.
Illustratively, from the image distribution, a plurality of scatter curves can be seen, and the value of K is obtained using y = Kx + b fitting; by setting the threshold range of K, outliers on the scatter plot can be removed.
Illustratively, a linear fit is a form of curve fitting. Let x and y both be the quantities observed, and y be a function of x: y = f (x; b), and curve fitting is to find the best estimate of the parameter b by the observed values of x, y, and find the best theoretical curve y = f (x; b). When the function y = f (x; b) is a linear function with respect to b, then such a curve fit is said to be a linear fit.
Illustratively, the result of the points on the fitted curve is saved, i.e. the result set of matching is obtained.
In some implementation scenes, the data matching method of the synchronous belt satellite avoids the fundamental problems of difficult orbit determination and large deviation of short arc section data, generates a synchronous belt virtual satellite orbit through optical observation data of the synchronous belt satellite, calculates the virtual position according to the synchronous belt virtual satellite orbit, namely calculates the ascent point right ascension, the fixed point longitude, the ascent point variable quantity and the like, so as to obtain the three-point sub-satellite point position, corrects the standard orbit through the fixed point longitude of the sub-satellite point, obtains a new sub-satellite point longitude, converts the complex initial orbit determination calculation into simple geometric relation mapping, calculates the sub-satellite point position of the current data arc section, and greatly improves the calculation efficiency; and finally fitting according to a scatter diagram drawn by the fixed point longitude and the right ascension variation to further obtain a synchronous belt satellite matching result. Therefore, the method can reduce the calculation error and accurately acquire the number of the orbits, and achieves the technical effect of improving the success rate of the synchronous belt satellite matching association.
Referring to fig. 2, fig. 2 is a schematic flow chart of another data matching method for a synchronous belt satellite according to an embodiment of the present application.
Exemplarily, S100: after the step of acquiring the optical observation data of the synchronous belt satellite, the method further comprises the following steps:
s110: and denoising the optical observation data based on the 3 sigma criterion of normal distribution.
Illustratively, the optical observation data is denoised through a 3 sigma criterion, so that data of a noise point and a noise point in the optical observation data are removed, the quality of the optical observation data can be effectively improved, and the accuracy of a data matching result is improved.
Illustratively, a Normal distribution (also called "Normal distribution"), also known as a Gaussian distribution (Gaussian distribution), was first obtained by junior (Abraham de Moivre) in an asymptotic formula for a binomial distribution. C.f. gaussian derives it from another angle when studying the measurement error. P.s. laplace and gaussian investigated its properties. Is a probability distribution which is very important in the fields of mathematics, physics, engineering and the like and has great influence on many aspects of statistics. The normal curve is bell-shaped, with low ends and high middle, and is symmetrical left and right, so it is often called bell-shaped curve.
Illustratively, by utilizing the property of normal distribution, a group of detection data is assumed to only contain random errors, the detection data is calculated to obtain a standard deviation, an interval is determined according to a certain probability, the errors exceeding the interval are considered not to belong to the random errors but to be gross errors, and the data containing the errors are removed.
Illustratively, σ represents the standard deviation in a normal distribution, μ represents the mean x = μ is the axis of symmetry of the image, and 3 σ is: the probability of the numerical distribution in (μ - σ, μ + σ) is 0.6826, the probability of the numerical distribution in (μ -2 σ, μ +2 σ) is 0.9544, and the probability of the numerical distribution in (μ -3 σ, μ +3 σ) is 0.9974, and it can be considered that the values of Y are almost entirely concentrated in the interval of (μ -3 σ, μ +3 σ), and the probability of exceeding this range is only less than 0.3%.
Exemplarily, S200: before the step of generating the synchronous belt virtual satellite orbit according to the optical observation data, the method further comprises the following steps:
s120: and calculating the position of the measuring station in a J2000 inertial coordinate system to obtain the position information of the measuring station.
Illustratively, J2000.0 is an astronomically used epoch, and the prefix "J" represents that this is a julian epoch, rather than a bessel epoch. It refers to julian date at 2451545.0 at TT or at 12 at 1 month, 2000 at TT, i.e., 11:59:27.816 or 1 month, 1 day, 11:58:55.816 at 2000 at UTC time relative to TAI at 1 month, 1 day, 2000. The equator and the bipartite point at time J2000 are used to define a celestial sphere reference coordinate system, which may also be written as J2000 coordinates, a J2000 inertial coordinate system, or simply J2000.
S130: and respectively calculating the fixed point longitudes of the starting time, the middle time and the ending time of the optical observation data according to the position information of the observation station and the preset space-based platform measuring distance to obtain a fixed point longitude average value and a fixed point longitude interval.
Exemplarily, setting the maximum value and the minimum value of the measurement distance of the space-based platform, namely the semimajor axis of the synchronous track belt + the semimajor axis of the space-based platform, and the semimajor axis of the synchronous track belt-the semimajor axis of the space-based platform; then, the fixed point longitudes at the start, middle, and end times of the optical observation data are calculated, respectively, to obtain a fixed point longitude average (Lon1) and a fixed point longitude interval.
Exemplarily, S200: the method comprises the steps of generating a synchronous belt virtual satellite orbit according to optical observation data and acquiring the ascension point right ascension of the synchronous belt virtual satellite orbit, and comprises the following steps:
s210: setting the initial epoch time of the synchronous belt virtual satellite orbit according to the observation optical data;
s220: calculating the fixed point longitude of the initial epoch moment;
s230: and calculating the average value of the fixed point longitudes and the fixed point longitude at the initial epoch moment to obtain the ascent point right ascension of the synchronous belt virtual satellite orbit.
Illustratively, a synchronous belt virtual satellite orbit is generated according to the optical observation data, wherein the semi-major axis of the synchronous belt virtual satellite orbit is 42165200 meters, the initial epoch is the starting time of the space-based observation optical data, and the eccentricity, the inclination angle, the ascension of the ascending intersection point, the argument of the near place and the angle of the mean and the near point are all 0; calculating a fixed point longitude (Lon 2) of an initial epoch time; and (4) subtracting the fixed point longitude (Lon 2) at the initial epoch time from the fixed point longitude average (Lon1) to obtain a value, and performing modulo operation to obtain the ascent point right ascension of the new track.
Exemplarily, S400: the step of obtaining the right ascension variation of the earth rotation according to the fixed point longitude and the preset fixed time comprises the following steps:
s410: calculating a difference value between preset fixed time and the initial time of the optical observation data to obtain a relative time difference;
s420: and calculating the relative time difference, the degree of the earth rotation and the fixed point longitude to obtain the right ascension variation of the earth rotation.
Illustratively, a fixed time T1 (0 th day of the optical observation data) is set, and a relative time difference DT between the optical observation data start time point and T1 is calculated; the relative time difference DT is multiplied by 360.9865 (degrees of earth rotation per day), then the fixed point longitude (Lon 3) is added, and the change Y of the right ascension channel of the sphere rotation in DT time is eliminated.
Illustratively, the right ascension variation Y value and the fixed point longitude (Lon 3) are stored.
In some embodiments, the flow of the data matching method using the synchronous belt satellite shown in fig. 1 to 2 is schematically as follows:
s1: optical observation data of a synchronous belt satellite (space base) is read.
Illustratively, by analyzing the optical observation data, the time, right ascension and declination data are respectively obtained, and the relevant information of the observation station is obtained through the station address file.
S2: and (4) preprocessing the read right ascension and declination data, and removing impurity points and noise points by using a 3 sigma criterion calculation method.
S3: a fixed point longitude interval of the optical observation data is calculated from the distance range position.
Exemplarily, calculating the position of an inertial coordinate system of an observation station J2000, and setting the maximum value and the minimum value of the measurement distance of the space-based platform, wherein the maximum value and the minimum value are respectively a semi-long shaft of the synchronous track belt + a semi-long shaft of the space-based platform, and the semi-long shaft of the synchronous track belt-the semi-long shaft of the space-based platform; fixed point longitudes at the start time, the middle time and the end time of observation data are calculated respectively, and a fixed point longitude average value (Lon1) and a fixed point longitude interval are obtained.
S4: and setting a synchronous belt virtual satellite orbit.
Exemplarily, setting various parameters of a synchronous belt virtual satellite orbit, wherein a semi-major axis is 42165200 meters, an initial epoch is the starting time of optical observation data, and eccentricity, an inclination angle, a rising intersection declination, an argument of a near place and an average angle of a near point are all 0; calculating a fixed point longitude (Lon 2) of an initial epoch time; and performing modulo operation on a value obtained by subtracting the fixed point longitude (Lon 2) from the fixed point longitude (Lon1) to obtain the ascending crossing right ascension of the new track.
S5: calculating the position of an observation point through synchronous belt virtual satellite orbit forecasting to obtain the distance R between the observation station and the observation point; and (4) calculating the fixed point longitude by using the distance R and the observation station position at the observation time to correct the standard orbit, repeating the step S5, and performing iterative calculation for multiple times to obtain the fixed point longitude (Lon 3) of the final observation data.
S6: setting a fixed time T1 (0 point of the day of the optical observation data), and calculating a relative time difference DT between the starting time point of the optical observation data and T1;
s7: the relative time difference DT is multiplied by 360.9865 (degrees of earth rotation per day), then the fixed point longitude (Lon 3) is added, and the change Y of the right ascension channel of the sphere rotation in DT time is eliminated.
S8: the right ascension variation Y value and the fixed point longitude (Lon 3) are stored.
S9: drawing a two-dimensional coordinate system scatter diagram, setting the abscissa as fixed point longitude (Lon 3) and the ordinate as right ascension variation Y; the data in step S9 is input to the coordinate system and plotted.
S10: according to the image distribution, a plurality of scatter curves can be seen, and a value of K is obtained by fitting y = Kx + b; by setting the threshold range of K, outliers on the scatter plot can be removed.
S11: and (4) storing the result of the points on the fitting curve, namely obtaining a matched result set.
S12: and (5) performing a plurality of loops on the rest data, and repeating the steps S7-S11 until the screening is finished.
Exemplarily, the data matching method for the synchronous belt satellite provided by the embodiment of the application avoids the fundamental problems of difficult orbit determination and large deviation of short arc section data; in the aspect of calculation efficiency, the method adopts virtual position calculation to obtain the three-point intersatellite point position, obtains new intersatellite point longitude by correcting a standard orbit through the fixed point longitude of the intersatellite point, converts complex initial orbit determination calculation into simple geometric relation mapping, calculates the intersatellite point position of the current data arc section, greatly improves the calculation efficiency, and has better matching correlation effect on short arc section synchronous belt space-based optical data.
In some embodiments, all core algorithms in the data matching method of the synchronous belt satellite are independently controllable, can be independently used and integrated; can be used across platforms, such as: windows system, Ubuntu series system, CentOS series system, kylin Linux operating system, etc.
Referring to fig. 3, fig. 3 is a schematic structural diagram of a data matching device for a synchronous belt satellite according to an embodiment of the present application, where the data matching device for a synchronous belt satellite includes:
the acquisition module 100 is used for acquiring optical observation data of a synchronous belt satellite;
the generating module 200 is configured to generate a synchronous belt virtual satellite orbit according to the optical observation data, and acquire a right ascension of a rising intersection point of the synchronous belt virtual satellite orbit;
the iteration module 300 is configured to perform iteration processing on the synchronous belt virtual satellite orbit and the ascent point right ascension to obtain the fixed point longitude of the optical observation data;
the right ascension calculation module 400 is configured to obtain a right ascension variation of the earth's rotation according to the fixed-point longitude and a preset fixed time;
the drawing module 500 is used for drawing a scatter diagram of the two-dimensional coordinate system according to the fixed point longitude and the right ascension variation;
and the fitting module 600 is configured to perform linear fitting according to the scatter diagram to obtain a fitting curve, where a coordinate point on the fitting curve is a result set of synchronous belt satellite matching.
Referring to fig. 4, fig. 4 is a schematic structural diagram of another data matching device for a synchronous belt satellite according to an embodiment of the present application.
Exemplarily, the data matching device for the synchronous belt satellite further comprises: the preprocessing module 110 is configured to preprocess the optical observation data based on a 3 σ criterion of normal distribution to remove noise and noise in the optical observation data.
Exemplarily, the data matching device for the synchronous belt satellite further comprises:
the position calculation module 120 is configured to calculate a position of the measurement station in a J2000 inertial coordinate system, and obtain position information of the measurement station;
and the fixed point longitude calculating module 130 is configured to calculate fixed point longitudes of the start time, the middle time, and the end time of the optical observation data according to the position information of the observation station and a preset space-based platform measurement distance, and obtain a fixed point longitude average value and a fixed point longitude interval.
Please refer to fig. 5, fig. 5 is a schematic structural diagram of a generating module according to an embodiment of the present disclosure.
Illustratively, the generating module 200 includes:
a setting unit 210, configured to set an initial epoch time of the synchronous belt virtual satellite orbit according to the observation optical data;
a first calculating unit 220, configured to calculate a fixed point longitude at an initial epoch time;
and a second calculating unit 230, configured to calculate the fixed point longitude average and the fixed point longitude at the initial epoch time, and obtain the ascent point right ascension of the synchronous belt virtual satellite orbit.
Referring to fig. 6, fig. 6 is a schematic structural diagram of a right ascension calculating module according to an embodiment of the present application.
Illustratively, the right ascension calculation module 400 includes:
a third calculating unit 410, configured to calculate a difference between a preset fixed time and a start time of the optical observation data, so as to obtain a relative time difference;
and a fourth calculating unit 420, configured to calculate the relative time difference, the degree of rotation of the earth, and the fixed-point longitude, and obtain a right ascension variation of the rotation of the earth.
It should be understood that the embodiments of the apparatus shown in fig. 3 to 6 correspond to the embodiments of the method shown in fig. 1 to 2, and are not repeated herein to avoid repetition.
Fig. 7 shows a structural block diagram of an apparatus according to an embodiment of the present application. The device may include a processor 510, a communication interface 520, a memory 530, and at least one communication bus 540. Wherein the communication bus 540 is used for realizing direct connection communication of these components. The communication interface 520 of the device in the embodiment of the present application is used for performing signaling or data communication with other node devices. Processor 510 may be an integrated circuit chip having signal processing capabilities.
The Processor 510 may be a general-purpose Processor including a Central Processing Unit (CPU), a Network Processor (NP), and the like; but may also be a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), an off-the-shelf programmable gate array (FPGA) or other programmable logic device, discrete gate or transistor logic, discrete hardware components. The various methods, steps, and logic blocks disclosed in the embodiments of the present application may be implemented or performed. A general purpose processor may be a microprocessor or the processor 510 may be any conventional processor or the like.
The Memory 530 may be, but is not limited to, a Random Access Memory (RAM), a Read Only Memory (ROM), a Programmable Read Only Memory (PROM), an Erasable Read Only Memory (EPROM), an electrically Erasable Read Only Memory (EEPROM), and the like. The memory 530 stores computer readable instructions that, when executed by the processor 510, cause the apparatus to perform the steps associated with the method embodiments of fig. 1-2 described above.
Optionally, the device may further include a memory controller, an input output unit.
The memory 530, the memory controller, the processor 510, the peripheral interface, and the input/output unit are electrically connected to each other directly or indirectly, so as to implement data transmission or interaction. For example, these elements may be electrically coupled to each other via one or more communication buses 540. The processor 510 is adapted to execute executable modules stored in the memory 530, such as software functional modules or computer programs comprised by the device.
The input and output unit is used for providing a task for a user to create and start an optional time period or preset execution time for the task creation so as to realize the interaction between the user and the server. The input/output unit may be, but is not limited to, a mouse, a keyboard, and the like.
It will be appreciated that the configuration shown in figure 7 is merely illustrative and that the apparatus may also include more or fewer components than shown in figure 7 or have a different configuration than shown in figure 7. The components shown in fig. 7 may be implemented in hardware, software, or a combination thereof.
The embodiment of the present application further provides a storage medium, where the storage medium stores instructions, and when the instructions are run on a computer, when the computer program is executed by a processor, the method in the method embodiment is implemented, and in order to avoid repetition, details are not repeated here.
The present application also provides a computer program product which, when run on a computer, causes the computer to perform the method of the method embodiments.
In the embodiments provided in the present application, it should be understood that the disclosed apparatus and method can be implemented in other ways. The apparatus embodiments described above are merely illustrative, and for example, the flowchart and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of apparatus, methods and computer program products according to various embodiments of the present application. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
In addition, functional modules in the embodiments of the present application may be integrated together to form an independent part, or each module may exist separately, or two or more modules may be integrated to form an independent part.
The functions, if implemented in the form of software functional modules and sold or used as a stand-alone product, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present application or portions thereof that substantially contribute to the prior art may be embodied in the form of a software product stored in a storage medium and including instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present application. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
The above description is only an example of the present application and is not intended to limit the scope of the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present application, and shall be covered by the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
Claims (10)
1. A data matching method for a synchronous belt satellite is characterized by comprising the following steps:
acquiring optical observation data of a synchronous belt satellite;
generating a synchronous belt virtual satellite orbit according to the optical observation data, and acquiring a rising point right ascension of the synchronous belt virtual satellite orbit;
carrying out iterative processing on the synchronous belt virtual satellite orbit and the ascension point right ascension to obtain the fixed point longitude of the optical observation data;
obtaining the right ascension variation of the earth rotation according to the fixed point longitude and the preset fixed time;
drawing a scatter diagram of a two-dimensional coordinate system according to the fixed point longitude and the right ascension variation;
and performing linear fitting on the scatter diagram to obtain a fitting curve, wherein coordinate points on the fitting curve are a result set matched by the synchronous belt satellite.
2. The data matching method for a synchronous belt satellite according to claim 1, wherein the step of acquiring optical observation data of a synchronous belt satellite is followed by further comprising:
and denoising the optical observation data based on a 3 sigma criterion of normal distribution.
3. The method for data matching of a synchronous belt satellite according to claim 1, wherein the step of generating a synchronous belt virtual satellite orbit from the optical observation data is preceded by the steps of:
calculating the position of the measuring station in a J2000 inertial coordinate system to obtain the position information of the measuring station;
and respectively calculating the fixed point longitudes of the starting time, the middle time and the ending time of the optical observation data according to the position information of the observation station and the preset space-based platform measuring distance to obtain a fixed point longitude average value and a fixed point longitude interval.
4. The data matching method for the synchronous belt satellite according to claim 3, wherein the step of generating a synchronous belt virtual satellite orbit according to the optical observation data and obtaining the ascent point right ascension of the synchronous belt virtual satellite orbit comprises:
setting the initial epoch time of the synchronous belt virtual satellite orbit according to the optical observation data;
calculating the fixed point longitude of the initial epoch moment;
and calculating the fixed point longitude average value and the fixed point longitude at the initial epoch moment to obtain the ascent point right ascension of the synchronous belt virtual satellite orbit.
5. The data matching method for the geostationary-belt satellite according to claim 1, wherein the step of obtaining the variation of right ascension of earth rotation according to the fixed-point longitude and a preset fixed time comprises:
calculating a difference value between the preset fixed time and the starting moment of the optical observation data to obtain a relative time difference;
and calculating the relative time difference, the degree of the earth rotation and the fixed point longitude to obtain the right ascension variation of the earth rotation.
6. A data matching device for a synchronous belt satellite is characterized by comprising:
the acquisition module is used for acquiring optical observation data of the synchronous belt satellite;
the generating module is used for generating a synchronous belt virtual satellite orbit according to the optical observation data and acquiring the ascent point right ascension of the synchronous belt virtual satellite orbit;
the iteration module is used for performing iteration processing on the synchronous belt virtual satellite orbit and the ascension point right ascension to obtain the fixed point longitude of the optical observation data;
the right ascension computing module is used for obtaining the right ascension variable quantity of the earth rotation according to the fixed-point longitude and the preset fixed time;
the drawing module is used for drawing a scatter diagram of a two-dimensional coordinate system according to the fixed point longitude and the right ascension variation;
and the fitting module is used for performing linear fitting according to the scatter diagram to obtain a fitting curve, and coordinate points on the fitting curve are a result set matched by the synchronous belt satellite.
7. The data matching device for synchronous belt satellite according to claim 6, further comprising:
and the preprocessing module is used for preprocessing the optical observation data based on a 3 sigma criterion of normal distribution so as to remove noise and noise in the optical observation data.
8. The data matching device for synchronous belt satellite according to claim 6, further comprising:
the position calculation module is used for calculating the position of the measuring station in a J2000 inertial coordinate system to obtain the position information of the measuring station;
and the fixed point longitude calculation module is used for respectively calculating the fixed point longitudes of the starting time, the middle time and the ending time of the optical observation data according to the position information of the observation station and the preset space-based platform measuring distance to obtain a fixed point longitude average value and a fixed point longitude interval.
9. An apparatus, comprising: memory, a processor and a computer program stored in the memory and executable on the processor, the processor implementing the steps of the data matching method for synchronous belt satellites as claimed in any one of claims 1 to 5 when executing the computer program.
10. A storage medium having stored thereon instructions which, when run on a computer, cause the computer to perform the data matching method for a synchronous belt satellite according to any one of claims 1 to 5.
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