High-orbit satellite state monitoring method and device, electronic equipment and storage medium

Abstract

The present disclosure relates to a high-orbit satellite state monitoring method and device, electronic equipment and storage medium, and relates to the technical field of satellites. The method comprises: determining a first position corresponding to a first time, a second position corresponding to a second time, and a time difference according to two orbit data; determining the first initial speed and the second initial speed according to the first position, the second position and the time difference; predicting the third position according to the first position and the first initial speed; determining the deviation between the second position and the third position; and in response to determining that the deviation is less than a preset deviation threshold, taking the first initial speed as the first target speed and the second initial speed as the second target speed and outputting. The present disclosure can improve the accuracy of the speed change before and after the high-orbit satellite applies the pulse.

Description

Technical Field

[0001] This application relates to the field of satellite technology, specifically to the field of spacecraft design, and particularly to a method, device, electronic equipment, and storage medium for monitoring the status of high-orbit satellites. Background Technology

[0002] Geostationary orbit (GEO) satellites, with their fixed hull trajectories, provide users with numerous services such as relay communication, navigation and positioning, and early warning and surveillance, making them crucial in space target systems. In recent years, the number of GEO satellites deployed has increased significantly. Under ideal two-body conditions, GEO satellites are stationary relative to Earth observers. However, in actual space motion, GEO satellites are affected by various perturbations, no longer remaining stationary relative to Earth observers, but exhibiting complex perturbation motion patterns. These satellites undergo multiple maneuvers during their on-orbit operation, remaining in a state of stationary-drift-stationary for extended periods. These maneuvers pose significant challenges to space surveillance operations. Failure to capture GEO satellite maneuvers in a timely manner can lead to the loss of target cataloging, threatening space security.

[0003] Currently, the identification of GEO satellite orbital maneuvering behavior is mainly achieved by fitting TLE (Two-Line Orbital Element) data. The purpose of this invention is to optimize and output the calculation method of orbit change parameters for high-orbit satellites, overcoming the problems of orbit discontinuity at orbit splicing points and large estimation errors of orbit change parameters in traditional methods. Summary of the Invention

[0004] Embodiments of this disclosure provide a method, apparatus, electronic device, and storage medium for monitoring the status of high-orbit satellites.

[0005] In a first aspect, embodiments of this disclosure provide a method for monitoring the status of a high-orbit satellite, comprising: acquiring two lines of orbital data of a high-orbit satellite within a preset time period; determining, based on the two lines of orbital data, a first position corresponding to a first epoch, a second position corresponding to a second epoch, and a time difference between the first epoch and the second epoch; and, based on the first position, the second position, and the time difference, performing the following determination steps: determining a first initial velocity corresponding to the first epoch and a second initial velocity corresponding to the second epoch; predicting a third position based on the first position and the first initial velocity; determining the deviation between the second position and the third position; comparing the error with a preset deviation threshold; and, in response to determining that the deviation is less than the preset deviation threshold, outputting the first initial velocity as a first target velocity and the second initial velocity as a second target velocity.

[0006] Secondly, embodiments of this disclosure provide a high-orbit satellite status monitoring device, comprising: a data acquisition unit configured to acquire two lines of orbit data of a high-orbit satellite within a preset time period; an information determination unit configured to determine, based on the two lines of orbit data, a first position corresponding to a first epoch, a second position corresponding to a second epoch, and a time difference between the first epoch and the second epoch; an iterative calculation unit configured to perform the following determination steps based on the first position, the second position, and the time difference: determining a first initial velocity corresponding to the first epoch and a second initial velocity corresponding to the second epoch; predicting a third position based on the first position and the first initial velocity; determining the deviation between the second position and the third position; and comparing the error with a preset deviation threshold; and an information output unit configured to, in response to determining that the deviation is less than the preset deviation threshold, output the first initial velocity as a first target velocity and the second initial velocity as a second target velocity.

[0007] Thirdly, embodiments of this disclosure provide an electronic device including a memory, a processor, a bus, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the high-orbit satellite status monitoring method as described in the first aspect.

[0008] Fourthly, embodiments of this disclosure provide a non-transitory computer-readable storage medium having a computer program stored thereon that, when executed by a processor, implements the high-orbit satellite status monitoring method as described in the first aspect.

[0009] By applying the technical solution disclosed herein, two lines of orbital data of a high-orbit satellite within a preset time period can be acquired first. Based on the two lines of orbital data, the first position corresponding to the first epoch, the second position corresponding to the second epoch, and the time difference between the two epochs are calculated. Further, based on the first position, the second position, and the time difference, the first initial velocity corresponding to the first epoch and the second initial velocity corresponding to the second epoch are determined; based on the first position and the first initial velocity, the third position is predicted; the deviation between the second and third positions is determined; the error is compared with a preset deviation threshold; if the deviation is less than the preset deviation threshold, the first initial velocity is used as the first target velocity, and the second initial velocity is used as the second target velocity, and both are output. In this way, the velocity of the high-orbit satellite can be accurately calculated, improving the accuracy of monitoring the status of the high-orbit satellite.

[0010] It should be understood that the description in this section is not intended to identify key or essential features of the embodiments of this disclosure, nor is it intended to limit the scope of this disclosure. Other features of this disclosure will become readily apparent from the following description. Attached Figure Description

[0011] The accompanying drawings are provided to better understand this solution and do not constitute a limitation of this disclosure. Wherein:

[0012] Figure 1 This is an exemplary system architecture diagram in which an embodiment of the high-orbit satellite status monitoring method disclosed herein can be applied;

[0013] Figure 2 This is a flowchart illustrating one embodiment of the high-orbit satellite status monitoring method disclosed herein.

[0014] Figure 3 This is a flowchart illustrating yet another embodiment of the high-orbit satellite status monitoring method disclosed herein;

[0015] Figure 4 This is a schematic diagram of the structure of one embodiment of the high-orbit satellite status monitoring device disclosed herein;

[0016] Figure 5 This is a schematic diagram of the structure of an embodiment of the electronic device disclosed herein. Detailed Implementation

[0017] It should be noted that the following detailed descriptions are exemplary and intended to provide further illustration of this disclosure. Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure pertains.

[0018] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this disclosure. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms “comprising” and / or “including” are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0019] Where there is no conflict, the embodiments and features described herein can be combined with each other.

[0020] To make the technical solutions and advantages of this disclosure clearer, the following description, in conjunction with the accompanying drawings and specific embodiments, will provide a more detailed account of this disclosure.

[0021] Figure 1 An exemplary system architecture 100 is shown, in which embodiments of the high-orbit satellite status monitoring method or high-orbit satellite status monitoring device of the present disclosure can be applied.

[0022] like Figure 1As shown, the system architecture 100 may include a high-orbit satellite 101, a ground communication station 102, and terminal equipment 103. The high-orbit satellite 101 can operate in geostationary orbit and can communicate with the ground communication station via radio.

[0023] Ground communication station 102 can receive data from high-orbit satellite 101 and can also send commands to high-orbit satellite 101.

[0024] Terminal device 103 can obtain TLE data of high-orbit satellite 101 from a designated website, analyze it, and determine the status information of high-orbit satellite 101. This status information can be used to track high-orbit satellite 101. Terminal device 103 can also send the tracking results to ground communication station 102, so that ground communication station 102 can control high-orbit satellite 101 based on the tracking results.

[0025] It should be noted that the high-orbit satellite status monitoring method provided in this embodiment can be executed by the ground communication station 102 or by the terminal device 103. Accordingly, the high-orbit satellite status monitoring device can be installed in the ground communication station 102 or in the terminal device 103.

[0026] It should be understood that Figure 1 The number of high-orbit satellites, ground communication stations, and terminal equipment shown is merely illustrative. Depending on the implementation requirements, any number of high-orbit satellites, ground communication stations, and terminal equipment can be included.

[0027] Figure 2 A flow 200 of one embodiment of the high-orbit satellite status monitoring method of this disclosure is shown. For example... Figure 2 As shown, the high-orbit satellite status monitoring method of this embodiment may include the following steps:

[0028] Step 201: Obtain two lines of orbital data of the high-orbit satellite within a preset time period.

[0029] In this embodiment, the executing entity of the high-orbit satellite status monitoring method (e.g., Figure 1The ground communication station 102 or terminal device 103 shown can obtain TLE data of high-orbit satellites within a preset time period from a designated website. TLE data is a standard method for describing the position parameters of satellites or space debris in Earth orbit. It includes the satellite's position and velocity information in space, which can be used to calculate the satellite's orbital position and predict its position changes. TLE data typically consists of two rows of numbers, each containing specific orbital parameters such as orbital inclination, right ascension of the ascending node, pericentric distance, orbital eccentricity, mean anomaly, and satellite orbital period. By continuously tracking the satellite's TLE orbital data over a certain period, fitting the variation patterns of its orbital parameters, and detecting orbital anomalies, the timing and manner of satellite orbital maneuvers can be estimated.

[0030] Step 202: Based on the two lines of orbital data, determine the first position corresponding to the first epoch, the second position corresponding to the second epoch, and the time difference between the first epoch and the second epoch.

[0031] After acquiring two lines of orbital data, they can be analyzed to determine the first position corresponding to the first epoch and the second position corresponding to the second epoch. Here, the first and second epochs can be any two epochs. For ease of calculation, two epochs with a time difference less than a preset threshold can be selected as the first and second epochs, respectively. The time difference between the first and second epochs can also be calculated.

[0032] Step 203: Based on the first position, the second position, and the time difference, perform the following determination steps:

[0033] After determining the first position, the second position, and the time difference, the following determination steps can be performed:

[0034] Step 2031: Determine the first initial velocity corresponding to the first epoch and the second initial velocity corresponding to the second epoch.

[0035] First, determine the first initial velocity corresponding to the first epoch and the second initial velocity corresponding to the second epoch. Specifically, the first and second initial velocities can be calculated using Lambert's time-of-flight theorem.

[0036] Lambert's time-of-flight theorem describes the relationship between the time of flight between two points on an orbit and the orbital parameters. The theorem states that in an elliptical orbit, the time of flight between two points is determined only by the semi-major axis, the sum of the radii of the initial and final positions, and the length of the chord connecting the two points, and is independent of the specific shape of the orbit.

[0037] Lambert's time-of-flight theorem states that: given two positions P1 and P2 in space (the corresponding position vectors in the geocentric inertial coordinate system are respectively...) and Given the flight time Δt and the flight direction, the problem of finding the distance from position P1 to the Keplerian orbit at position P2 after time Δt is essentially a two-point boundary value problem of solving a differential equation.

[0038] The semi-major axis of a high-orbit satellite's orbit can be calculated using the TLE data of the high-orbit satellite. Specifically, it can be calculated using the following formula:

[0039]

[0040] Where GM is the gravitational constant of the central body. For Earth, GM≈3.986×10¹⁴ m³ / s². o This represents the average motion of the orbit.

[0041] After obtaining the above positions, the first position can be used as the initial position. Take the second position as the target position. The above time difference is taken as the orbital transfer time Δt. Δt is used as the initial input to the two-body Lambert problem to obtain the velocity vector corresponding to the Lambert problem. This velocity is the velocity of the high-orbit satellite after the pulse is applied, i.e., the first initial velocity, denoted as Δt.

[0042] Step 2032: Based on the first position and the first initial velocity, predict the third position.

[0043] After determining the first position and the first initial velocity, and Substituting the values ​​into the SGP4 (Simplified General Perturbations 4) model for orbital recursion, we obtain the third position, denoted as...

[0044] Step 2033: Determine the error between the second and third positions.

[0045] Determine the third position With the second position The deviation between them is denoted as

[0046] Step 2034: Compare the deviation with a preset deviation threshold.

[0047] After obtaining the above deviation, it is compared with a preset deviation threshold. Here, the absolute value of the deviation can be used. Compare with the preset deviation threshold ε.

[0048] Step 204: In response to determining that the deviation is less than a preset deviation threshold, the first initial velocity is used as the first target velocity and the second initial velocity is used as the second target velocity and output.

[0049] If the deviation is less than the preset deviation threshold, the current velocity calculation is considered correct. Then, the first initial velocity can be used as the first target velocity, and the second initial velocity can be used as the second target velocity, and output. In this way, the velocity of the high-orbit satellite before and after the pulse transmission can be calculated.

[0050] The high-orbit satellite status monitoring method provided in the above embodiments of this disclosure can first acquire two lines of orbit data of the high-orbit satellite within a preset time period. Based on the two lines of orbit data, a first position corresponding to a first epoch, a second position corresponding to a second epoch, and the time difference between the two epochs are calculated. Further, based on the first position, the second position, and the time difference, a first initial velocity corresponding to the first epoch and a second initial velocity corresponding to the second epoch are determined; a third position is predicted based on the first position and the first initial velocity; the deviation between the second and third positions is determined; the error is compared with a preset deviation threshold; if the deviation is less than the preset deviation threshold, the first initial velocity is used as the first target velocity, and the second initial velocity is used as the second target velocity, and both are output. In this way, the velocity of the high-orbit satellite can be calculated, improving the accuracy of high-orbit satellite status monitoring.

[0051] See also Figure 3 This illustrates flow 300 of another embodiment of the high-orbit satellite status monitoring method according to this disclosure. Figure 3 As shown, the method in this embodiment may include the following steps:

[0052] Step 301: Obtain two lines of orbital data of the high-orbit satellite within a preset time period.

[0053] Step 302: Determine the characteristic parameters based on the two lines of orbital data; determine the first position, the second position, and the time difference between the first epoch and the second epoch based on the characteristic parameters.

[0054] In this embodiment, after determining the first epoch and the second epoch, characteristic parameters can be determined based on the two rows of orbital data. These characteristic parameters may include the semi-major axis a, orbital eccentricity e, orbital inclination angle, and perigee altitude h. p apogee altitude h a α, fixed point longitude.

[0055] Of the parameters mentioned above, the orbital inclination and eccentricity can be directly read from the TLE file. The orbital semi-major axis (a) and apogee altitude (h) are also relevant.a Perimeter altitude h p The fixed-point longitude α needs to be obtained through the transformation of characteristic quantities. Specifically, it can be calculated using the following formula:

[0056]

[0057] Where, n o h is the average orbital motion. a h is the altitude of the orbit's apogee. p R is the altitude of the orbital perigee. E =6378.137km is the Earth's radius, x E y E The coordinates of the high-orbit satellite in the geocentric fixed coordinate system.

[0058] After obtaining the above parameters, the first and second positions can be calculated. The time difference can be obtained by directly subtracting the two epoch times.

[0059] Step 303: Based on the first position, the second position, and the time difference, perform the following determination steps:

[0060] Step 3031: Determine the first initial velocity corresponding to the first epoch and the second initial velocity corresponding to the second epoch.

[0061] Step 3032: Based on the first position and the first initial velocity, predict the third position.

[0062] Step 3033: Determine the deviation between the second position and the third position.

[0063] Step 3034: Compare the error with a preset deviation threshold.

[0064] Step 304: In response to determining that the deviation is less than a preset deviation threshold, the first initial velocity is used as the first target velocity and the second initial velocity is used as the second target velocity and output.

[0065] Step 305: In response to determining that the deviation is greater than or equal to a preset deviation threshold, the second position is corrected using the third position and the deviation; using the corrected second position, the first position and the time difference, the determination steps 3031 to 3034 are executed again.

[0066] In this embodiment, if the above deviation is greater than a preset deviation threshold, that is... Then, the third position and the aforementioned deviation can be used to correct the second position. That is... Then, using the corrected second position, first position, and time difference, steps 3031 to 3034 are executed again until...

[0067] Step 306: Based on the two rows of orbit data, determine the fourth position in the first row of orbit data and the fifth position in the second row of orbit data corresponding to the initial pulse application time of the satellite; determine the fourth velocity corresponding to the fourth position and the fifth velocity corresponding to the fifth position; based on the fourth velocity and the fifth velocity, determine the pulse application time of the target satellite and the velocity change of the satellite before and after the pulse application.

[0068] In this embodiment, the initial satellite pulse application time can be further determined based on the two rows of orbit data, specifically at the fourth position in the first row of orbit data and the fifth position in the second row of orbit data. Here, the initial satellite pulse application time can be any epoch. The position of the initial satellite pulse application time in the first row of orbit data is denoted as the fourth position, and the position in the second row of orbit data is denoted as the fifth position.

[0069] Using the information provided in steps 302-305, the fourth velocity corresponding to the fourth position and the fifth velocity corresponding to the fifth position are determined. Finally, based on the aforementioned fourth and fifth velocities, the timing of the pulse application to the target satellite and the velocity change before and after the pulse application are determined. This allows for an accurate calculation of the velocity change of the high-orbit satellite before and after the pulse application.

[0070] In some optional implementations of this embodiment, the timing of the pulse application and the velocity change of the target satellite can be determined by the following steps: determining the objective function based on the fourth velocity and the fifth velocity; using the timing of the pulse application as a variable of the objective function, and determining the timing of the pulse application corresponding to the minimum value of the objective function as the timing of the pulse application of the target satellite.

[0071] In this implementation, the difference between the fourth and fifth velocities can be used as the objective function. Then, the time when the satellite applies the pulse can be used as a variable in the objective function, and the values ​​of the objective function at different epochs are calculated. The epoch corresponding to the minimum value of the objective function is taken as the time when the target satellite applies the pulse.

[0072] After determining the moment when the target satellite applies the pulse, the velocity before and after that moment can be calculated. Subtracting the two velocities will give the change in the two velocities.

[0073] The high-orbit satellite status monitoring method provided in the above embodiments of this disclosure can improve the accuracy of calculating the velocity change of high-orbit satellites.

[0074] Further reference Figure 4 As an implementation of the methods shown in the above figures, this disclosure provides an embodiment of a high-orbit satellite status monitoring device, which is similar to... Figure 2Corresponding to the method embodiments shown, this device can be specifically applied to various electronic devices.

[0075] like Figure 4 As shown, the high-orbit satellite status monitoring device 400 in this embodiment includes: a data acquisition unit 401, a first determination unit 402, a second determination unit 403, an iterative calculation unit 404, and an information output unit 405.

[0076] The data acquisition unit 401 is configured to acquire two lines of orbit data of a high-orbit satellite within a preset time period.

[0077] The information determination unit 402 is configured to determine, based on two lines of orbital data, the first position corresponding to the first epoch, the second position corresponding to the second epoch, and the time difference between the first epoch and the second epoch.

[0078] The iterative calculation unit 403 is configured to perform the following determination steps based on the first position, the second position, and the time difference: determine the first initial velocity corresponding to the first epoch and the second initial velocity corresponding to the second epoch; predict the third position based on the first position and the first initial velocity; determine the deviation between the second position and the third position; and compare the error with a preset deviation threshold.

[0079] The information output unit 404 is configured to output a first initial velocity as a first target velocity and a second initial velocity as a second target velocity in response to a determination that the deviation is less than a preset deviation threshold.

[0080] In addition, an electronic device is also proposed in the technical solution of this application.

[0081] Figure 5 A schematic diagram of the structure of an electronic device provided in one embodiment of the present disclosure is shown.

[0082] like Figure 5As shown, the electronic device may include a processor 501, a memory 502, a bus 503, and a computer program stored in the memory 502 and executable on the processor 501. The processor 501 and the memory 502 communicate with each other via the bus 503. When the processor 501 executes the computer program, it implements the steps of the above method, including, for example: acquiring two lines of orbital data of a high-orbit satellite within a preset time period; determining, based on the two lines of orbital data, a first position corresponding to a first epoch, a second position corresponding to a second epoch, and the time difference between the first and second epochs; and, based on the first position, the second position, and the time difference, performing the following determination steps: determining a first initial velocity corresponding to the first epoch and a second initial velocity corresponding to the second epoch; predicting a third position based on the first position and the first initial velocity; determining the deviation between the second and third positions; comparing the error with a preset deviation threshold; and, in response to determining that the deviation is less than the preset deviation threshold, outputting the first initial velocity as a first target velocity and the second initial velocity as a second target velocity.

[0083] In addition, one embodiment of this disclosure also provides a non-transitory computer-readable storage medium storing a computer program thereon. When executed by a processor, the computer program implements the steps of the above-described method, including, for example,: acquiring two lines of orbit data of a high-orbit satellite within a preset time period; determining, based on the two lines of orbit data, a first position corresponding to a first epoch, a second position corresponding to a second epoch, and a time difference between the first epoch and the second epoch; and, based on the first position, the second position, and the time difference, performing the following determination steps: determining a first initial velocity corresponding to the first epoch and a second initial velocity corresponding to the second epoch; predicting a third position based on the first position and the first initial velocity; determining the deviation between the second position and the third position; comparing the error with a preset deviation threshold; and, in response to determining that the deviation is less than the preset deviation threshold, outputting the first initial velocity as a first target velocity and the second initial velocity as a second target velocity.

[0084] In summary, the technical solution disclosed herein first acquires two lines of orbital data from a high-orbit satellite within a preset time period. Based on these two lines of orbital data, the first position corresponding to the first epoch, the second position corresponding to the second epoch, and the time difference between the two epochs are calculated. Further, based on the first position, the second position, and the time difference, the first initial velocity corresponding to the first epoch and the second initial velocity corresponding to the second epoch are determined. Based on the first position and the first initial velocity, a third position is predicted. The deviation between the second and third positions is determined. The error is compared with a preset deviation threshold. If the deviation is less than the preset deviation threshold, the first initial velocity is used as the first target velocity, and the second initial velocity is used as the second target velocity, and both are output. In this way, the velocity of the high-orbit satellite before and after the application of a pulse can be calculated, improving the accuracy of monitoring high-orbit satellite information.

[0085] The above description is merely a preferred embodiment of this disclosure and is not intended to limit this disclosure. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this disclosure should be included within the scope of protection of this disclosure.

Claims

1. A method for monitoring the status of a high-orbit satellite, comprising: Acquire two lines of orbital data from a high-orbit satellite within a preset time period; Based on the two rows of orbital data, determine the first position corresponding to the first epoch, the second position corresponding to the second epoch, and the time difference between the first epoch and the second epoch; Based on the first position, the second position, and the time difference, the following determination steps are performed: determine the first initial velocity corresponding to the first epoch time and the second initial velocity corresponding to the second epoch time; Based on the first position and the first initial velocity, a third position is predicted; the deviation between the second position and the third position is determined; the error is compared with a preset deviation threshold. In response to determining that the deviation is less than the preset deviation threshold, the first initial velocity is used as the first target velocity and the second initial velocity is used as the second target velocity and output.

2. The method according to claim 1, wherein, The method further includes: In response to determining that the deviation is greater than or equal to the preset deviation threshold, the second position is corrected using the third position and the deviation; The determination step is performed again using the corrected second position, the first position, and the time difference.

3. The method according to claim 1, wherein, The step of determining the first position corresponding to the first epoch, the second position corresponding to the second epoch, and the time difference between the first epoch and the second epoch based on the two lines of orbital data includes: Based on the two lines of track data, determine the characteristic parameters; The first position and the second position are determined based on the feature parameters; The time difference is determined based on the first epoch time and the second epoch time.

4. The method according to claim 1, wherein, The method further includes: Based on the two rows of orbit data, the initial satellite pulse application time is determined to be the fourth position in the first row of orbit data and the fifth position in the second row of orbit data. Determine the fourth velocity corresponding to the fourth position and the fifth velocity corresponding to the fifth position; Based on the fourth velocity and the fifth velocity, determine the time when the target satellite applies the pulse and the velocity change before and after the pulse is applied.

5. The method according to claim 4, wherein, The step of determining the moment when the pulse is applied to the target satellite and the change in velocity before and after the pulse is applied, based on the fourth velocity and the fifth velocity, includes: Determine the objective function based on the fourth velocity and the fifth velocity; The timing of the satellite pulse application is used as a variable in the objective function, and the timing of the satellite pulse application corresponding to the minimum value of the objective function is determined as the timing of the target satellite pulse application.

6. The method according to claim 5, wherein, The step of determining the objective function based on the fourth velocity and the fifth velocity includes: The absolute value of the difference between the fourth speed and the fifth speed is determined to be the objective function.

7. The method according to claim 2, wherein, The step of correcting the second position using the third position and the error includes: The difference between the third position and the error is determined to be the corrected second position.

8. A high-orbit satellite status monitoring device, comprising: The data acquisition unit is configured to acquire two lines of orbital data from a high-orbit satellite within a preset time period; The information determination unit is configured to determine, based on the two lines of orbital data, the first position corresponding to the first epoch, the second position corresponding to the second epoch, and the time difference between the first epoch and the second epoch. The iterative calculation unit is configured to perform the following determination steps based on the first position, the second position, and the time difference: determining the first initial velocity corresponding to the first epoch time and the second initial velocity corresponding to the second epoch time; Based on the first position and the first initial velocity, the third position is predicted; Determine the deviation between the second position and the third position; The error is compared with a preset deviation threshold. The information output unit is configured to output the first initial velocity as the first target velocity and the second initial velocity as the second target velocity in response to determining that the deviation is less than the preset deviation threshold.

9. An electronic device comprising a memory, a processor, a bus, and a computer program stored in the memory and executable on the processor, wherein, When the processor executes the computer program, it implements the high-orbit satellite status monitoring method as described in any one of claims 1 to 7.

10. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that, When executed by a processor, the computer program implements the high-orbit satellite status monitoring method as described in any one of claims 1 to 7.

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