A method to eliminate the prediction error of double planet ephemeris based on post-precision ephemeris

Abstract

The present application relates to a method for eliminating dual-planet ephemeris prediction errors based on post-precision ephemeris. The method comprises: predicting the satellite position for the ephemeris reference time based on the dual-planet ephemeris and the SDP4 model; calculating the satellite position for the ephemeris reference time based on the post-precision ephemeris of the dual-planet ephemeris for the ephemeris reference time and using it as the reference satellite position; obtaining the satellite position prediction error by comparing the difference between the predicted satellite position for the ephemeris reference time and the reference satellite position; and obtaining an error function for the dual-planet ephemeris predicted satellite position by fitting the satellite position prediction error within one satellite orbital period; and performing error elimination on the predicted satellite position for the target date based on the error function to obtain the predicted satellite position after error elimination. This method can eliminate the satellite position prediction error of the dual-planet ephemeris and improve the accuracy of the dual-planet ephemeris for medium- and long-term forecasts.

Description

Technical Field

[0001] The present application relates to the field of satellite navigation and simulation technology, and in particular to a method for eliminating double-planet ephemeris prediction errors based on post-precision ephemeris. Background Art

[0002] To achieve high-gain reception of GNSS (Global Navigation Satellite System) satellite signals for refined analysis, ground-based monitoring stations typically use large-aperture, high-gain antennas for real-time satellite tracking and signal acquisition. High-gain antennas for real-time tracking of single satellites require highly accurate orbit predictions. Commonly used prediction methods include broadcast ephemeris, almanac, and dual ephemeris. Broadcast ephemeris and almanac can achieve highly accurate orbit predictions in the short term, but orbit prediction errors increase rapidly with increasing prediction time. Dual ephemeris uses a specific method to remove the square root of the periodic perturbation term and combines it with the SDP4 model (Simplified Deep Space Perturbations 4). While orbit prediction accuracy is not high, it is stable over long periods of time and suitable for medium- to long-term satellite tracking by ground-based monitoring stations. However, the accuracy of dual ephemeris is insufficient for long-term tracking with high-gain antennas, necessitating research into methods to eliminate errors in dual ephemeris predictions. Summary of the Invention

[0003] Based on this, it is necessary to provide a method to eliminate the double planet ephemeris prediction error based on post-precision ephemeris to address the above technical problems.

[0004] A method for eliminating double planet ephemeris prediction errors based on post-precision ephemeris, the method comprising:

[0005] Satellite positions at the ephemeris reference time are predicted based on the dual planet ephemeris and SDP4 model;

[0006] Based on the post-precision ephemeris of the dual planetary ephemeris on the ephemeris reference time, the satellite positions on the ephemeris reference time are calculated and used as the reference satellite positions;

[0007] By comparing the difference between the predicted satellite position at the ephemeris reference time and the reference satellite position, the satellite position prediction error of the dual ephemeris at the ephemeris reference time is obtained. And by fitting the satellite position prediction error within one orbital period of the satellite, the error function of the satellite position predicted by the dual ephemeris is obtained.

[0008] The satellite position of the target date is predicted based on the dual planet ephemeris and the SDP4 model, and the error of the predicted satellite position of the target date is eliminated according to the error function to obtain the predicted satellite position after error elimination.

[0009] In one embodiment, predicting the satellite position at the ephemeris reference time based on the dual planet ephemeris and the SDP4 model includes:

[0010] Download the dual planet ephemeris for the ephemeris reference time and input it into the SDP4 model. The predicted satellite positions in the true equatorial mean equinox coordinate system for the ephemeris reference time are output. After coordinate conversion, the predicted satellite positions in the Earth-centered Earth-fixed coordinate system for the ephemeris reference time are obtained.

[0011] In one embodiment, calculating the satellite position at the ephemeris reference time based on the post-precision ephemeris of the dual planetary ephemeris at the ephemeris reference time and using the calculated position as the reference satellite position includes:

[0012] Download and obtain the SP3 format post-precision ephemeris of the dual planet ephemeris at the ephemeris reference time. Calculate the satellite positions in the Earth-centered Earth-fixed coordinate system at the ephemeris reference time based on the post-precision ephemeris and use them as the reference satellite positions.

[0013] In one embodiment, obtaining the satellite position prediction error of the dual-planetary ephemeris at the ephemeris reference time by comparing the difference between the predicted satellite position at the ephemeris reference time and the reference satellite position includes:

[0014] By comparing the difference between the predicted satellite position and the reference satellite position in the Earth-centered Earth-fixed coordinate system at the ephemeris reference time, the satellite position prediction error of the dual planetary ephemeris at the ephemeris reference time and the error components of each axis of the satellite position prediction error in the Earth-centered Earth-fixed coordinate system are obtained, which can be expressed as:

[0015] ;

[0016] in, Indicates the predicted satellite position, represents the reference satellite position, 、 and They represent the satellite position prediction error in the Earth-centered Earth-fixed coordinate system. axis, Axis and The error component on the axis.

[0017] In one embodiment, the error function of the satellite position predicted by the dual-planetary ephemeris is obtained by fitting the satellite position prediction error within one orbital period of the satellite, including:

[0018] By fitting the error components of each axis of the satellite position prediction error within one orbital period in the Earth-centered Earth-fixed coordinate system, the error function of the satellite position predicted by the dual planetary ephemeris is obtained, which is expressed as:

[0019] ;

[0020] in, represents the ephemeris reference time, is the satellite's orbital period, is any moment in the orbital period; 、 and Represent the Earth-centered Earth-fixed coordinate system axis, Axis and The error function on the axis.

[0021] In one embodiment, predicting satellite positions on a target date based on the dual planetary ephemeris and the SDP4 model includes:

[0022] Download the dual planet ephemeris for the ephemeris reference time and input it into the SDP4 model. The output is the predicted satellite positions at each time on the target date in the true equatorial mean equinox coordinate system. After coordinate conversion, the predicted satellite positions at each time on the target date in the Earth-centered Earth-fixed coordinate system are obtained. The target date is any day between 1 and 30 days from the ephemeris reference time.

[0023] In one embodiment, performing error elimination on the predicted satellite position for the target date according to the error function to obtain the error-eliminated predicted satellite position includes:

[0024] The satellite position error at each moment of the target date is calculated based on the error function and the satellite's orbital period, and the predicted satellite position at each moment of the target date is subtracted from the satellite position error at the corresponding moment to obtain the predicted satellite position at each moment of the target date after the error is eliminated.

[0025] In one embodiment, calculating the satellite position error at each time of the target date based on the error function and the satellite's orbital period, and subtracting the satellite position error at the corresponding time from the predicted satellite position at each time of the target date to obtain the predicted satellite position at each time of the target date after eliminating the error, includes:

[0026] The satellite position error at each moment of the target date is calculated based on the error function and the satellite's orbital period, which is expressed as:

[0027] ;

[0028] in, 、 and Respectively indicate the target date At any moment in the Earth-centered Earth-fixed coordinate system axis, Axis and Satellite position error on the axis; 、 and Represent the Earth-centered Earth-fixed coordinate system axis, Axis and Error function on the axis; represents the ephemeris reference time, is the satellite's orbital period, is any moment in the orbital period; express Time and ephemeris reference time The time difference is modulo the orbital period;

[0029] Subtract the satellite position error at the corresponding time from the predicted satellite position at each time on the target date to obtain the predicted satellite position at each time on the target date after the error is eliminated, which is expressed as:

[0030] ;

[0031] in, 、 and Respectively indicate the target date The predicted satellite position in the Earth-centered Earth-fixed coordinate system after the time error is eliminated axis, Axis and The coordinate components on the axis, 、 and Respectively indicate the target date The predicted satellite position at the time of the Earth-centered Earth-fixed coordinate system axis, Axis and Coordinate components along the axis.

[0032] In one embodiment, after obtaining the predicted satellite position after error elimination, the method further includes:

[0033] The predicted satellite positions at each time of the target date after error elimination are used to calculate the elevation and azimuth angles of the satellite relative to the monitoring station, and the satellite is tracked based on the elevation and azimuth angles.

[0034] In one embodiment, calculating the elevation angle and azimuth angle of the satellite relative to the monitoring station using the predicted satellite positions at each time of the target date after eliminating errors includes:

[0035] The elevation angle of the satellite relative to the monitoring station is expressed as:

[0036] ;

[0037] The azimuth of the satellite relative to the monitoring station is expressed as:

[0038] ;

[0039] in, 、 and They represent the east component, north component and zenith direction component of the satellite relative to the monitoring station in the station center coordinate system, respectively:

[0040] ;

[0041] in, 、 and Respectively indicate the target date The predicted satellite position in the Earth-centered Earth-fixed coordinate system after the time error is eliminated axis, Axis and The coordinate components on the axis, 、 and They represent the monitoring station positions in the Earth-centered Earth-fixed coordinate system. axis, Axis and The coordinate components on the axis, and They represent the longitude and latitude of the monitoring station in the geodetic coordinate system respectively.

[0042] This method, based on post-precision ephemeris, eliminates errors in dual ephemeris predictions. Based on the periodicity of satellites, the method compares the predicted satellite positions based on the dual ephemeris with the reference satellite positions based on post-precision ephemeris, fitting an error function for the dual ephemeris-predicted satellite positions. This error function is then used to eliminate errors in the satellite positions for the target date predicted by the dual ephemeris, yielding the predicted satellite positions after error elimination. This method, based on the periodicity of satellites, applies the error function at the ephemeris reference time to future satellite position predictions, eliminating errors in the dual ephemeris-predicted satellite positions. This improves the accuracy of the dual ephemeris for medium- and long-term predictions and addresses the need for frequent ephemeris updates required by monitoring stations tracking satellites, thus providing practical engineering significance. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1 1 is a flow chart of a method for eliminating double planet ephemeris prediction errors based on post-precision ephemeris in one embodiment;

[0044] Figure 2 A schematic diagram of the elevation angle error of a dual planetary ephemeris relative to a monitoring station before error elimination in one embodiment;

[0045] Figure 3 Schematic diagram of the elevation angle error of the dual planetary ephemeris relative to a monitoring station after error elimination in one embodiment. DETAILED DESCRIPTION

[0046] In order to make the purpose, technical solutions and advantages of this application more clear, the following further describes this application in detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain this application and are not intended to limit this application.

[0047] In one embodiment, Figure 1 As shown, a method for eliminating the prediction error of double planet ephemeris based on post-precision ephemeris is provided, comprising the following steps:

[0048] Step S1: predicting the satellite position at the ephemeris reference time based on the dual planet ephemeris and the SDP4 model.

[0049] A dual planetary ephemeris refers to the ephemeris data for two celestial bodies (such as the Earth-Moon system, the Earth-Sun system, or other binary systems). It can be obtained from the NORAD website or other satellite orbit data services. The SDP4 model is used to predict the orbits of high-orbit satellites. It calculates the gravitational interactions between the satellite and the Earth, Sun, and Moon to predict the satellite's orbit.

[0050] Step S2: Calculate the satellite positions at the ephemeris reference time based on the post-precision ephemeris of the dual planetary ephemeris at the ephemeris reference time and use them as reference satellite positions.

[0051] Both the dual-planet ephemeris and the post-event precise ephemeris are released 1-2 days after the ephemeris reference time. Post-event precise ephemeris is satellite orbit information derived from observation data from multiple satellite tracking stations through post-processing. It is primarily used for applications such as precise satellite positioning. Post-event precise ephemeris provides precise orbit information for the observation period. When using the dual-planet ephemeris and the SDP4 model for satellite position prediction, the prediction error can be evaluated by comparing it with the post-event precise ephemeris.

[0052] Step S3, by comparing the difference between the predicted satellite position on the day of the ephemeris reference time and the reference satellite position, the satellite position prediction error of the dual ephemeris on the day of the ephemeris reference time is obtained, and by fitting the satellite position prediction error within one orbital period of the satellite, the error function of the satellite position predicted by the dual ephemeris is obtained.

[0053] Among them, the satellite's orbital period is the length of time it takes for the satellite to orbit the earth. According to the periodic characteristics of the satellite, the error function of the satellite position predicted by the dual planetary ephemeris is fitted, so that the error function can be used to eliminate errors in the future satellite position prediction process, thereby improving the efficiency of error elimination in the dual planetary ephemeris satellite position prediction.

[0054] Step S4: forecasting the satellite position on the target date based on the dual planet ephemeris and the SDP4 model, and performing error elimination on the forecasted satellite position on the target date according to the error function to obtain the forecasted satellite position after error elimination.

[0055] Among them, according to the periodic characteristics of satellites, the error function of the ephemeris reference time is used in the future satellite position prediction process, which eliminates the satellite position prediction error of the dual planetary ephemeris, improves the accuracy of the dual planetary ephemeris for medium and long-term predictions, and can avoid the problem of frequent updates of the ephemeris when monitoring stations track satellites, and has good application scenarios.

[0056] In one embodiment, predicting the satellite position at the ephemeris reference time based on the dual-planet ephemeris and the SDP4 model includes: downloading the dual-planet ephemeris for the ephemeris reference time and inputting it into the SDP4 model, outputting the predicted satellite position at the ephemeris reference time in the True Equator and Mean Equinox (TEME) coordinate system, and performing coordinate conversion to obtain the predicted satellite position at the ephemeris reference time in the Earth-centered Earth-fixed coordinate system (ITRF2014). The coordinate conversion relationship is:

[0057] ;

[0058] in, represents the satellite position in the Earth-centered Earth-fixed coordinate system, Indicates the satellite position in the true equatorial mean equinox coordinate system; 、 and Respectively represent the axis, Axis and The rotation matrix of the axis; and Respectively Axis and The polar shift parameter of the axis; represents the polar motion correction; represents the Earth rotation correction, Indicates Greenwich sidereal time; represents the nutation correction, For the movement of Huang Jing Zhang, It is the obliquity of the ecliptic.

[0059] For example, 00:00 on March 8, 2025, is used as the ephemeris reference time, and a GPS (Global Positioning System) satellite is selected for position prediction. The dual planetary ephemeris for a GPS satellite on March 8, 2025, is obtained from the NORAD official website. The SDP4 model is used to predict the position from 00:00 on March 8, 2025, to 00:00 on March 9, 2025. After coordinate conversion, the predicted position of the GPS satellite in the Earth-centered, Earth-fixed coordinate system is obtained.

[0060] In one embodiment, based on the post-precision ephemeris of the dual planetary ephemeris on the day of the ephemeris reference time, the satellite position on the day of the ephemeris reference time is calculated and used as the reference satellite position, including: downloading and obtaining the post-precision ephemeris in SP3 format of the dual planetary ephemeris on the day of the ephemeris reference time, calculating the satellite position in the Earth-centered Earth-fixed coordinate system on the day of the ephemeris reference time according to the post-precision ephemeris, and using it as the reference satellite position.

[0061] For example, the post-precision ephemeris of the binary planet ephemeris on March 8, 2025, is downloaded from a university data center. The file name is GRG0OPSULT_20250670000_02D_05M_ORB.SP3, and the position of a GPS satellite in the Earth-centered Earth-fixed coordinate system from 0:00 on March 8, 2025 to 0:00 on March 9, 2025 is calculated and used as the reference position.

[0062] In one embodiment, obtaining the satellite position prediction error of the dual-planetary ephemeris at the ephemeris reference time by comparing the difference between the predicted satellite position at the ephemeris reference time and the reference satellite position includes:

[0063] By comparing the difference between the predicted satellite position and the reference satellite position in the Earth-centered Earth-fixed coordinate system at the ephemeris reference time, the satellite position prediction error of the dual planetary ephemeris at the ephemeris reference time and the error components of each axis of the satellite position prediction error in the Earth-centered Earth-fixed coordinate system are obtained, which can be expressed as:

[0064] ;

[0065] in, Indicates the predicted satellite position, represents the reference satellite position, 、 and They represent the satellite position prediction error in the Earth-centered Earth-fixed coordinate system. axis, Axis and The error component on the axis.

[0066] In one embodiment, the error function of the satellite position predicted by the dual-planetary ephemeris is obtained by fitting the satellite position prediction error within one orbital period of the satellite, including:

[0067] By fitting the error components of each axis of the satellite position prediction error within one orbital period in the Earth-centered Earth-fixed coordinate system, the error function of the satellite position predicted by the dual planetary ephemeris is obtained, which is expressed as:

[0068] ;

[0069] in, represents the ephemeris reference time, is the satellite's orbital period, is any moment in the orbital period; 、 and Represent the Earth-centered Earth-fixed coordinate system axis, Axis and The error function on the axis.

[0070] For example, the time it takes for a GPS satellite to orbit the earth is 11 hours and 58 minutes. The error function from 0:00 on March 8, 2025 to 11:58 on March 8, 2025 is obtained from the above satellite position prediction error. At this time, =00:00 on March 8, 2025, T = 11:58. The satellite positions predicted by the double planetary ephemeris on March 8 are different from the precise ephemeris after the event. X axis, Y Axis and Z The axis error is about 50km.

[0071] In one embodiment, forecasting the satellite position on a target date based on the dual planet ephemeris and the SDP4 model includes: downloading the dual planet ephemeris of the day of the ephemeris reference time and inputting it into the SDP4 model, outputting the forecast satellite position at each moment of the target date in the true equatorial mean equinox coordinate system, and after coordinate conversion, obtaining the forecast satellite position at each moment of the target date in the Earth-centered Earth-fixed coordinate system; wherein the target date is any day between 1 day and 30 days from the ephemeris reference time.

[0072] For example, the position of a GPS satellite from 00:00 on March 23, 2025 to 00:00 on March 24, 2025 is predicted using the dual planetary calendar of March 8, 2025. X axis, Y Axis and Z The axis error is about 55km.

[0073] In one embodiment, performing error elimination on the predicted satellite position for the target date according to the error function to obtain the error-eliminated predicted satellite position includes:

[0074] The satellite position error at each time on the target date is calculated based on the error function and the satellite's orbital period. The predicted satellite position at each time on the target date is subtracted from the satellite position error at the corresponding time to obtain the predicted satellite position at each time on the target date after the error is eliminated. Specifically, first, the satellite position error at each time on the target date is calculated based on the error function and the satellite's orbital period, which can be expressed as:

[0075] ;

[0076] in, 、 and Respectively indicate the target date At any moment in the Earth-centered Earth-fixed coordinate system axis, Axis and Satellite position error on the axis; 、 and Represent the Earth-centered Earth-fixed coordinate system axis, Axis and Error function on the axis; represents the ephemeris reference time, is the satellite's orbital period, is any moment in the orbital period; express Time and ephemeris reference time The time difference modulo the orbital period, that is Time at the ephemeris reference time The orbital period relative to the ephemeris reference time time difference.

[0077] For example, It is 00:00 on March 23, 2025. It is 00:00 on March 8, 2025. Equal to 11:58, substitute Calculated is equal to one hour, and then substituting it into the error function we get At this time, the error value at 0:00 on March 23, 2025 corresponds to the error value at 0:00 on March 8, 2025. Similarly, the error value from 0:00 on March 23, 2025 to 0:00 on March 24, 2025 can be obtained.

[0078] Then, the predicted satellite position at each time on the target date is subtracted from the satellite position error at the corresponding time to obtain the predicted satellite position at each time on the target date after the error is eliminated, which is expressed as:

[0079] ;

[0080] in, 、 and Respectively indicate the target date The predicted satellite position in the Earth-centered Earth-fixed coordinate system after the time error is eliminated axis, Axis and The coordinate components on the axis, 、 and Respectively indicate the target date The predicted satellite position at the time of the Earth-centered Earth-fixed coordinate system axis, Axis and Coordinate components along the axis.

[0081] For example, the position of a GPS satellite at any time between 00:00 on March 23, 2025, and 00:00 on March 24, 2025, calculated above, is subtracted from the error value at the corresponding time to obtain the predicted position of the GPS satellite at each time after the error is eliminated. Specifically, the error in each axis after the error is subtracted is approximately 10 km.

[0082] In one embodiment, after obtaining the error-eliminated predicted satellite position, the method further includes: calculating the elevation angle and azimuth angle of the satellite relative to the monitoring station using the error-eliminated predicted satellite position at each time on the target date, and tracking the satellite based on the elevation angle and azimuth angle. The elevation angle of the satellite relative to the monitoring station is expressed as:

[0083] ;

[0084] The azimuth of the satellite relative to the monitoring station is expressed as:

[0085] ;

[0086] in, 、 and They represent the east component, north component and zenith direction component of the satellite relative to the monitoring station in the station center coordinate system, respectively:

[0087] ;

[0088] in, 、 and Respectively indicate the target date The predicted satellite position in the Earth-centered Earth-fixed coordinate system after the time error is eliminated axis, Axis and The coordinate components on the axis, 、 and They represent the monitoring station positions in the Earth-centered Earth-fixed coordinate system. axis, Axis and The coordinate components on the axis, and They represent the longitude and latitude of the monitoring station in the geodetic coordinate system respectively.

[0089] It can be understood that the elevation and azimuth angles are calculated based on the predicted satellite position after error elimination and the position of the monitoring station for satellite tracking, so that signal quality monitoring can be continuously performed while the monitoring station is tracking the satellite. This is suitable for medium- and long-term high-precision satellite tracking at ground monitoring stations.

[0090] Furthermore, in order to verify the effect of this method on satellite tracking accuracy, the elevation angle errors of the double planetary ephemeris relative to a monitoring station before and after error elimination were calculated, as shown in the following example: Figure 2 and Figure 3 As shown in the figure, the elevation angle error after error elimination is about 0.04 degrees, which is 0.11 degrees higher than 0.15 degrees before error elimination. This method greatly improves the accuracy of satellite tracking and monitoring. Figure 2 and Figure 3 The prn in represents pseudorandom noise.

[0091] It should be understood that although Figure 1 The steps in the flowchart are shown in sequence as indicated by the arrows, but these steps are not necessarily executed in the order indicated by the arrows. Unless otherwise specified in this document, there is no strict order restriction for the execution of these steps, and these steps can be executed in other orders. In addition, Figure 1 At least part of the steps may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily executed at the same time, but can be executed at different times. The execution order of these sub-steps or stages is not necessarily sequential, but can be executed in turn or alternately with other steps or at least part of the sub-steps or stages of other steps.

[0092] The technical features of the above embodiments can be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0093] The above embodiments merely illustrate several implementation methods of the present application. While the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the present application. It should be noted that a person skilled in the art could make various modifications and improvements without departing from the spirit of the present application, all of which fall within the scope of protection of the present application.

Claims

1. A method for eliminating double planet ephemeris prediction errors based on post-precision ephemeris, characterized in that: The method comprises: Satellite positions at the ephemeris reference time are predicted based on the dual planet ephemeris and SDP4 model; Based on the post-precision ephemeris of the dual planetary ephemeris on the ephemeris reference time, the satellite positions on the ephemeris reference time are calculated and used as the reference satellite positions; By comparing the difference between the predicted satellite position at the ephemeris reference time and the reference satellite position, the satellite position prediction error of the dual ephemeris at the ephemeris reference time is obtained, and by fitting the satellite position prediction error within one orbital period of the satellite, the error function of the dual ephemeris predicted satellite position is obtained; The satellite position of the target date is predicted based on the dual planet ephemeris and the SDP4 model, and the error of the predicted satellite position of the target date is eliminated according to the error function to obtain the predicted satellite position after the error is eliminated.

2. The method for eliminating double planet ephemeris prediction errors based on post-precision ephemeris according to claim 1, characterized in that: Satellite positions at the ephemeris reference time are predicted based on the dual planet ephemeris and SDP4 model, including: Download the dual planet ephemeris for the ephemeris reference time and input it into the SDP4 model. The predicted satellite positions in the true equatorial mean equinox coordinate system for the ephemeris reference time are output. After coordinate conversion, the predicted satellite positions in the Earth-centered Earth-fixed coordinate system for the ephemeris reference time are obtained.

3. The method for eliminating double planet ephemeris prediction errors based on post-precision ephemeris according to claim 1, characterized in that: Based on the post-precision ephemeris of the dual planetary ephemeris on the day of the ephemeris reference time, the satellite positions on the day of the ephemeris reference time are calculated and used as the reference satellite positions, including: Download and obtain the SP3 format post-precision ephemeris of the dual planet ephemeris on the ephemeris reference time, calculate the satellite position in the Earth-centered Earth-fixed coordinate system on the ephemeris reference time based on the post-precision ephemeris, and use it as the reference satellite position.

4. The method for eliminating double planet ephemeris prediction errors based on post-precision ephemeris according to claim 1, characterized in that: By comparing the difference between the predicted satellite position and the reference satellite position at the ephemeris reference time, the satellite position prediction error of the dual planet ephemeris at the ephemeris reference time is obtained, including: By comparing the difference between the predicted satellite position and the reference satellite position in the Earth-centered Earth-fixed coordinate system on the day of the ephemeris reference time, the satellite position prediction error of the dual planetary ephemeris on the day of the ephemeris reference time and the error components of each axis of the satellite position prediction error in the Earth-centered Earth-fixed coordinate system are obtained, which are expressed as: ； in, Indicates the predicted satellite position, represents the reference satellite position, 、 and They represent the satellite position prediction error in the Earth-centered Earth-fixed coordinate system. axis, Axis and The error component on the axis.

5. The method for eliminating double planet ephemeris prediction errors based on post-precision ephemeris according to claim 4, characterized in that: By fitting the satellite position prediction error within one orbital period, the error function of the satellite position predicted by the dual planetary ephemeris is obtained, including: By fitting the error components of each axis of the satellite position prediction error within one orbital period in the Earth-centered Earth-fixed coordinate system, the error function of the satellite position predicted by the dual planetary ephemeris is obtained, which is expressed as: ； in, represents the ephemeris reference time, is the satellite's orbital period, is any moment in the orbital period; 、 and Represent the Earth-centered Earth-fixed coordinate system axis, Axis and The error function on the axis.

6. The method for eliminating double planet ephemeris prediction errors based on post-precision ephemeris according to claim 1, characterized in that: Satellite positions for the target date are predicted based on the dual planetary ephemeris and the SDP4 model, including: Download the dual planet ephemeris for the ephemeris reference time and input it into the SDP4 model. The output is the predicted satellite positions at each time on the target date in the true equatorial mean equinox coordinate system. After coordinate conversion, the predicted satellite positions at each time on the target date in the Earth-centered Earth-fixed coordinate system are obtained. The target date is any day between 1 and 30 days from the ephemeris reference time.

7. The method for eliminating double planet ephemeris prediction errors based on post-precision ephemeris according to claim 1, characterized in that: Eliminating errors in the predicted satellite positions on the target date according to the error function to obtain the predicted satellite positions after error elimination, including: The satellite position error at each moment of the target date is calculated based on the error function and the satellite's orbital period, and the predicted satellite position at each moment of the target date is subtracted from the satellite position error at the corresponding moment to obtain the predicted satellite position at each moment of the target date after the error is eliminated.

8. The method for eliminating double planet ephemeris prediction errors based on post-precision ephemeris according to claim 7, characterized in that: The method comprises: calculating the satellite position error at each time of the target date according to the error function and the orbital period of the satellite, and subtracting the satellite position error at the corresponding time from the predicted satellite position at each time of the target date to obtain the predicted satellite position at each time of the target date after eliminating the error, including: The satellite position error at each moment of the target date is calculated based on the error function and the satellite's orbital period, and is expressed as: ； in, 、 and Respectively indicate the target date At any moment in the Earth-centered Earth-fixed coordinate system axis, Axis and Satellite position error on the axis; 、 and Represent the Earth-centered Earth-fixed coordinate system axis, Axis and Error function on the axis; represents the ephemeris reference time, is the satellite's orbital period, is any moment in the orbital period; express Time and ephemeris reference time The time difference is modulo the orbital period; Subtract the satellite position error at the corresponding time from the predicted satellite position at each time on the target date to obtain the predicted satellite position at each time on the target date after the error is eliminated, which is expressed as: ； in, 、 and Respectively indicate the target date The predicted satellite position in the Earth-centered Earth-fixed coordinate system after the time error is eliminated axis, Axis and The coordinate components on the axis, 、 and Respectively indicate the target date The predicted satellite position at the time of the Earth-centered Earth-fixed coordinate system axis, Axis and Coordinate components along the axis.

9. The method for eliminating double planet ephemeris prediction errors based on post-precision ephemeris according to claim 8, characterized in that: After obtaining the predicted satellite position after error elimination, the method further includes: The predicted satellite positions at each time of the target date after error elimination are used to calculate the elevation angle and azimuth angle of the satellite relative to the monitoring station, and the satellite is tracked based on the elevation angle and azimuth angle.

10. The method for eliminating double planet ephemeris prediction errors based on post-precision ephemeris according to claim 9, characterized in that: The satellite elevation and azimuth relative to the monitoring station are calculated using the predicted satellite positions at each time of the target date after error elimination, including: The elevation angle of the satellite relative to the monitoring station is expressed as: ； The azimuth of the satellite relative to the monitoring station is expressed as: ； in, 、 and They represent the east component, north component and zenith component of the satellite relative to the monitoring station in the station center coordinate system, respectively: ； in, 、 and Respectively indicate the target date The predicted satellite position in the Earth-centered Earth-fixed coordinate system after the time error is eliminated axis, Axis and The coordinate components on the axis, 、 and They represent the monitoring station positions in the Earth-centered Earth-fixed coordinate system. axis, Axis and The coordinate components on the axis, and They represent the longitude and latitude of the monitoring station in the geodetic coordinate system respectively.

Images