Satellite orbit circle number prediction method and device, computer device and storage medium

Abstract

The application relates to a satellite orbit circle number prediction method and device, computer equipment and a storage medium. Initial orbit data of a target satellite is acquired based on a first satellite identifier of the target satellite, corresponding initial ephemeris data is determined according to the initial orbit data of the target satellite and a first time parameter configured in advance, and an initial circle number list corresponding to the initial ephemeris data is determined. In the case that orbit measurement data of the target satellite is received, corresponding periodic ephemeris data is determined according to the orbit measurement data, the initial orbit data and a second time parameter configured in advance, the periodic ephemeris data and the initial circle number list are used to generate a periodic circle number list corresponding to the periodic ephemeris data, and the initial circle number list and the periodic circle number list are used to generate a circle number prediction list. The final circle number prediction list is generated based on the initial short-term prediction and the periodic prediction of precise orbit determination, so that long-term high-precision prediction of future circle numbers can be realized.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of space data processing, and in particular to a satellite orbit circle number prediction method and device, computer equipment, computer readable storage medium and computer program product. BACKGROUND

[0002] The satellite orbit circle number refers to a continuous number of the circle of a satellite around the Earth since the satellite is launched into orbit. The circle number count usually starts from the first time the satellite flies over a certain specified starting point (also known as a circle dividing point, usually the descending node or ascending node). When the satellite completes a circle of operation and passes through the circle dividing point again, the circle number is incremented by 1. Therefore, the circle number is a continuous sequential number, which will always increase as long as the satellite is in orbit. In the process of satellite measurement and control, management and application, the satellite orbit circle number can be used to accurately identify the position and task execution phase of the satellite at a specific time. Therefore, circle number prediction is crucial for remote control instruction execution, ground tracking and data transmission reception.

[0003] In the traditional technology, the satellite orbit circle number prediction usually adopts the calculation method of the orbit period. However, since the satellite orbit perturbation will cause the period to change continuously, a large cumulative error will be generated after long-term operation, which will further cause the circle number prediction error. SUMMARY

[0004] Therefore, it is necessary to provide a satellite orbit circle number prediction method, device, computer equipment, computer readable storage medium and computer program product capable of improving the accuracy of circle number prediction in view of the above technical problems.

[0005] In a first aspect, the present application provides a satellite orbit circle number prediction method, which comprises:

[0006] obtaining initial orbit data of a target satellite based on a first satellite identifier of the target satellite, wherein the initial orbit data comprises an orbit injection time of the target satellite and corresponding initial orbit elements;

[0007] determining corresponding initial ephemeris data according to the initial orbit data of the target satellite and a first time parameter configured in advance, and determining an initial circle number list corresponding to the initial ephemeris data;

[0008] in a case where orbit measurement data of the target satellite is received, determining corresponding periodic ephemeris data according to the orbit measurement data, the initial orbit data and a second time parameter configured in advance;

[0009] generating a periodic circle number list corresponding to the periodic ephemeris data according to the periodic ephemeris data and the initial circle number list;

[0010] A predicted orbit number list is generated based on the initial orbit number list and the periodic orbit number list. The predicted orbit number list includes the first satellite identifier of the target satellite, the predicted orbit point time, and the corresponding predicted orbit number.

[0011] In one embodiment, determining the initial orbit number list corresponding to the initial ephemeris data includes: determining the first orbital point time from the initial ephemeris data, and determining the orbital number corresponding to the first orbital point time as the first orbital number; traversing the other orbital point times in the initial ephemeris data, and determining the orbital numbers corresponding to the other orbital point times in the initial ephemeris data respectively based on the first orbital number corresponding to the first orbital point time; the other orbital point times are the orbital point times in the initial ephemeris data other than the first orbital point time; generating the initial orbit number list of the initial ephemeris data based on the first orbital number corresponding to the first orbital point time in the initial ephemeris data and the orbital numbers corresponding to the other orbital point times respectively; the initial orbit number list includes the first satellite identifier of the target satellite, the orbital point times in the initial ephemeris data, and the corresponding orbital numbers.

[0012] In one embodiment, generating a periodic orbit number list corresponding to the periodic ephemeris data based on the periodic ephemeris data and the initial orbit number list includes: determining the first orbit division point time from the periodic ephemeris data; searching the initial orbit number list for an orbit division point time that has a first relationship with the first orbit division point time; the first relationship is used to characterize that the difference between the first orbit division point time and the orbit division point time in the initial orbit number list is less than or equal to a first threshold; and using the orbit number corresponding to the found orbit division point time as the orbit number corresponding to the first orbit division point time in the periodic ephemeris data. The process iterates through the other orbital points in the periodic ephemeris data, and determines the orbital numbers corresponding to the other orbital points in the periodic ephemeris data based on the orbital number corresponding to the first orbital point. The other orbital points are the orbital points in the periodic ephemeris data other than the first orbital point. Based on the orbital number corresponding to the first orbital point in the periodic ephemeris data and the orbital numbers corresponding to the other orbital points, a periodic orbital number list of the periodic ephemeris data is generated. The periodic orbital number list includes the first satellite identifier of the target satellite, the orbital points in the periodic ephemeris data, and the corresponding orbital numbers.

[0013] In one embodiment, generating the orbit number prediction list based on the initial orbit number list and the periodic orbit number list includes: determining the orbit number corresponding to the first orbit point time in the periodic ephemeris data; deleting records greater than or equal to the orbit number from the initial orbit number list; and merging the periodic orbit number list with the initial orbit number list after deleting records to obtain the orbit number prediction list.

[0014] In one embodiment, after generating the orbit number prediction list based on the initial orbit number list and the periodic orbit number list, the method further includes: upon receiving post-hoc orbit data for the target satellite, correcting the orbit number prediction list based on the post-hoc orbit data to obtain a corrected orbit number prediction list; the post-hoc orbit data includes post-hoc precise ephemeris data, post-hoc instantaneous root, and corresponding on-board accumulated orbit numbers of the target satellite.

[0015] In one embodiment, after generating a predicted orbit number list based on the initial orbit number list and the periodic orbit number list, the method further includes: upon receiving post-hoc orbit data for the target satellite, determining the measurement orbit time from the post-hoc orbit data; searching the predicted orbit time in the predicted orbit number list for a predicted orbit time that has a second relationship with the measurement orbit time; the second relationship is used to characterize that the difference between the measurement orbit time and the predicted orbit time in the predicted orbit number list is less than or equal to a first threshold; determining the orbit number corresponding to the predicted orbit time, obtaining the corresponding orbit time deviation based on the orbit number; and dynamically correcting the orbit time deviation.

[0016] In one embodiment, the step of dynamically correcting based on the orbital point time deviation includes: if there is an orbital point time deviation greater than a second threshold, correcting the orbital number prediction list based on the post-event root of the corresponding measured orbital point time and the on-board accumulated orbital number, to obtain a corrected orbital number prediction list.

[0017] In one embodiment, the method further includes: if there is no case where the deviation of the lap point time is greater than the second threshold, determining the smoothing deviation based on UKF-RTS filtering; and correcting the initial deviation according to the smoothing deviation.

[0018] In one embodiment, after generating the orbital number prediction list based on the initial orbital number list and the periodic orbital number list, the method further includes: responding to a satellite tracking command from the target station, querying the corresponding satellite tracking information in the orbital number prediction list based on the satellite tracking command; the satellite tracking command carries a second satellite identifier of the satellite to be tracked, the station identifier of the target station, the corresponding arc segment identifier, the arrival time, and the departure time; generating satellite orbital number prediction information based on the satellite tracking command and the corresponding satellite tracking information.

[0019] In one embodiment, the step of querying the corresponding satellite tracking information in the orbit number prediction list according to the satellite tracking instruction includes: determining a target orbit number prediction list that matches the second satellite identifier of the satellite to be tracked based on the first satellite identifier in the orbit number prediction list; if the predicted orbit point time in the target orbit number prediction list is determined to be a descending node, querying the target predicted orbit point time that is greater than the arrival time and closest to the arrival time in the target orbit number prediction list; determining the target predicted orbit number corresponding to the target predicted orbit point time, and determining the target predicted orbit point time and the target predicted orbit number as the corresponding satellite tracking information.

[0020] In one embodiment, the step of querying the corresponding satellite tracking information in the orbit number prediction list according to the satellite tracking instruction includes: determining a target orbit number prediction list that matches the second satellite identifier of the satellite to be tracked based on the first satellite identifier in the orbit number prediction list; if the predicted orbit point time in the target orbit number prediction list is determined to be the ascending node, querying the target predicted orbit point time in the target orbit number prediction list that is less than the arrival time and closest to the arrival time; determining the target predicted orbit number corresponding to the target predicted orbit point time, and determining the target predicted orbit point time and the target predicted orbit number as the corresponding satellite tracking information.

[0021] Secondly, this application also provides a satellite orbit number prediction device, the device comprising:

[0022] The initial data acquisition module is used to acquire the initial orbit data of the target satellite based on the first satellite identifier of the target satellite. The initial orbit data includes the orbit insertion time of the target satellite and the corresponding initial orbital elements.

[0023] The initial orbit number determination module is used to determine the corresponding initial ephemeris data based on the initial orbit data of the target satellite and the pre-configured first time parameters, and to determine the initial orbit number list corresponding to the initial ephemeris data;

[0024] The periodic data acquisition module is used to determine the corresponding periodic ephemeris data based on the orbit measurement data, the initial orbit data, and the pre-configured second time parameter when the orbit measurement data for the target satellite is received.

[0025] The periodic circle number determination module is used to generate a periodic circle number list corresponding to the periodic ephemeris data based on the periodic ephemeris data and the initial circle number list.

[0026] The prediction orbit number generation module is used to generate a prediction orbit number list based on the initial orbit number list and the periodic orbit number list. The prediction orbit number list includes the first satellite identifier of the target satellite, the prediction orbit point time, and the corresponding prediction orbit number.

[0027] Thirdly, this application also provides a computer device, including a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to implement the steps of the method described in the first aspect.

[0028] Fourthly, this application also provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the steps of the method described in the first aspect.

[0029] Fifthly, this application also provides a computer program product, including a computer program that, when executed by a processor, implements the steps of the method described in the first aspect above.

[0030] The aforementioned method, apparatus, computer equipment, computer-readable storage medium, and computer program product for predicting satellite orbit numbers acquire initial orbit data of the target satellite based on a first satellite identifier. It then determines corresponding initial ephemeris data and an initial orbit number list corresponding to the initial ephemeris data based on the initial orbit data and pre-configured first time parameters. Upon receiving orbit measurement data for the target satellite, it determines corresponding periodic ephemeris data based on the orbit measurement data, initial orbit data, and pre-configured second time parameters. Based on the periodic ephemeris data and the initial orbit number list, it generates a periodic orbit number list corresponding to the periodic ephemeris data, and finally generates a predicted orbit number list based on the initial orbit number list and the periodic orbit number list. By generating the final orbit number predicted list based on initial short-term forecasts combined with periodic forecasts obtained through precise orbit determination, it can achieve long-term, high-precision prediction of future orbit numbers. Attached Figure Description

[0031] To more clearly illustrate the technical solutions in the embodiments of this application or related technologies, the drawings used in the description of the embodiments of this application or related technologies will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0032] Figure 1 This is a flowchart illustrating a method for predicting satellite orbit numbers in one embodiment;

[0033] Figure 2 This is a flowchart illustrating the initial circle number list step in one embodiment;

[0034] Figure 3 This is a flowchart illustrating the steps for generating a list of periodic circle numbers in one embodiment.

[0035] Figure 4 This is a flowchart illustrating the steps for generating a circle number prediction list in one embodiment;

[0036] Figure 5 This is a flowchart illustrating the dynamic correction steps in one embodiment;

[0037] Figure 6 This is a flowchart illustrating the forecast response steps in one embodiment;

[0038] Figure 7 This is a flowchart illustrating the steps for determining ephemeris data in one embodiment;

[0039] Figure 8 This is a flowchart illustrating a method for predicting satellite orbit numbers in another embodiment;

[0040] Figure 9 This is a structural block diagram of a satellite orbit number prediction device in one embodiment;

[0041] Figure 10 This is an internal structural diagram of a computer device in one embodiment. Detailed Implementation

[0042] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0043] It should be noted that the terms "first," "second," etc., used in this application can be used to describe various elements, but these elements are not limited by these terms. These terms are only used to distinguish the first element from the second element. The terms "comprising" and "having," and any variations thereof, used in this application, are intended to cover non-exclusive inclusion. The term "multiple" used in this application refers to two or more. The term "and / or" used in this application refers to one of the embodiments, or any combination of multiple embodiments.

[0044] In the traditional method of predicting satellite orbit numbers using orbital period calculations, the predicted satellite approach times are typically used. The first orbital point after entering orbit The interval between and combined with orbital period (in, For the semi-major axis, (where gravitational constant is the constant of Earth's gravity), and the final orbit number is calculated. ( (This is a function for rounding down).

[0045] However, due to the periodicity caused by satellite orbital perturbations Constant change, which leads to Rounding errors exist, and after long-term operation (more than 30 days), significant cumulative errors will inevitably occur, leading to incorrect orbital numbers. Typically, to correct the orbital period, the period deviation is calculated using two-line elements (TLE) and simplified conventional perturbation (SGP4) models based on predicted ephemeris values. Then, filtering algorithms (such as α-β filters or Kalman filters) are applied to correct the deviation. Perform smoothing and updating to obtain more accurate results. and use Replace the old And predict the orbit number for the next and even further orbits. This is due to the average orbital period. It is relatively stable in a short period of time (a few days). Therefore, although the improved method can improve the accuracy of forecasts in the short term, it will still have the problem of incorrect prediction of zoning numbers after long-term operation.

[0046] Based on this, embodiments of this application provide a method for predicting satellite orbit numbers, such as... Figure 1 As shown, the specific steps may include:

[0047] Step 102: Obtain the initial orbital data of the target satellite based on the first satellite identifier of the target satellite.

[0048] The target satellite can be a satellite for which orbital number prediction is required. The first satellite identifier can be a mark or symbol used to distinguish different target satellites; typically, a first satellite identifier can uniquely identify a target satellite. For example, the first satellite identifier can be a satellite number.

[0049] Initial orbital data refers to the initial data after a satellite enters its orbit, including the target satellite's orbital insertion time and the corresponding initial orbital elements. The orbital insertion time refers to the instant the satellite successfully separates from the launch vehicle after the final stage engine shuts down. The initial orbital elements are a set of six independent orbital parameters describing the satellite's orbital shape, size, spatial orientation, and specific position within its orbit at the orbital insertion time.

[0050] In this embodiment, satellite-related information that requires orbit number prediction can be pre-configured, for example, configuring the first satellite identifier of the corresponding satellite. Circle number forecast type cnpt (e.g.) Initial forecast Periodic forecasts (Manual forecasting), orbital identifiers (e.g., node=DN descending node, node=AN ascending node), etc. Satellite physical characteristic parameters can also be set, and specified perturbation models and parameters can be configured. This allows for monitoring of the target satellite's status based on the configured first satellite identifier. Upon detecting the target satellite's entry into orbit, the system automatically acquires the target satellite's initial orbital data and determines its corresponding orbital circle number based on subsequent steps.

[0051] Step 104: Determine the corresponding initial ephemeris data based on the initial orbit data of the target satellite and the pre-configured first time parameters, and determine the initial orbit number list corresponding to the initial ephemeris data.

[0052] The initial ephemeris data can be predicted within minutes of the satellite's orbit insertion, based on the target satellite's initial orbital data and pre-configured first-time parameters. Ephemeris data refers to the satellite's continuous trajectory in space, including epoch time, three-dimensional position, and three-dimensional velocity. The initial orbit number list is a list of orbit numbers obtained based on the initial ephemeris data and orbit number prediction.

[0053] The first time parameter can be the predicted initial time, prediction step size, and prediction duration of the pre-configured initial ephemeris data. Among them, the predicted initial time can be the target satellite's orbit insertion time, the prediction step size can be 3 seconds, and the prediction duration can be 1 day.

[0054] Specifically, within minutes of the target satellite entering orbit, the telemetry, tracking, and command (TT&C) center can determine the initial orbit data based on ground-based external measurement data, and automatically predict the ephemeris based on the initial orbital elements (such as the Kepler six elements) to obtain initial ephemeris data. The predicted initial time is the satellite's orbit entry time, the prediction duration is 1 day (one day after the orbit entry time), and the step size is steps of seconds (e.g., 3 seconds). Then, based on the initial ephemeris data, orbit number prediction is performed to obtain an initial orbit number list.

[0055] Step 106: Upon receiving orbit measurement data for the target satellite, determine the corresponding periodic ephemeris data based on the orbit measurement data, initial orbit data, and pre-configured second time parameters.

[0056] The periodic ephemeris data can be ephemeris data that is periodically predicted within a few hours after the satellite enters orbit, based on the target satellite's orbital measurement data, initial orbital data, and pre-configured second time parameters. Specifically, the target satellite's orbital measurement data can be on-board GNSS (Global Navigation Satellite System) engineering telemetry data. The second time parameter can be the pre-configured prediction initial time, prediction step size, and prediction duration of the periodic ephemeris data.

[0057] For example, within hours of the target satellite entering orbit, the telemetry, tracking, and command (TT&C) center can determine the initial orbit data based on ground-based external measurement data and integrate it with GNSS engineering telemetry data (i.e., orbit measurement data for the target satellite) to perform precise orbit determination and obtain the instantaneous elements for precise orbit determination. Then, based on the instantaneous elements (such as the Kepler six elements), periodic ephemeris predictions are made to obtain periodic ephemeris data. The initial prediction time... ,in, This represents the moment corresponding to the instantaneous elements of precise orbit determination. This indicates the pre-configured forecast initial time deviation. The forecast duration can be 30 days (30 days after the forecast initial time), and the forecast step size is step seconds (e.g., 3 seconds).

[0058] Step 108: Generate a periodic circle number list corresponding to the periodic ephemeris data based on the periodic ephemeris data and the initial circle number list.

[0059] The periodic orbital number list is a list of orbital numbers obtained by predicting orbital numbers based on periodic ephemeris data and combining it with an initial orbital number list. Since orbital numbers are sequentially consecutive, the initial orbital number list needs to be considered during the prediction of orbital numbers from the periodic ephemeris data to ensure the continuity of the final orbital number list.

[0060] Step 110: Generate a lap number prediction list based on the initial lap number list and the periodic lap number list.

[0061] The orbit number prediction list is the final orbit number list obtained by fusing the initial orbit number list and the periodic orbit number list. Specifically, the orbit number prediction list includes the first satellite identifier of the target satellite, the predicted orbit division time, and the corresponding predicted orbit number.

[0062] In the aforementioned method for predicting satellite orbit numbers, the initial orbit data of the target satellite is obtained based on its first satellite identifier. Then, based on the initial orbit data and pre-configured first time parameters, the corresponding initial ephemeris data and an initial orbit number list corresponding to the initial ephemeris data are determined. Upon receiving orbit measurement data for the target satellite, the corresponding periodic ephemeris data is determined based on the orbit measurement data, the initial orbit data, and pre-configured second time parameters. Based on the periodic ephemeris data and the initial orbit number list, a periodic orbit number list corresponding to the periodic ephemeris data is generated. Finally, a orbit number prediction list is generated based on the initial orbit number list and the periodic orbit number list. This method generates the final orbit number prediction list based on initial short-term predictions combined with periodic predictions from precise orbit determination, thereby enabling long-term, high-precision prediction of future orbit numbers.

[0063] In one exemplary embodiment, such as Figure 2 As shown, in step 104, the initial orbit number list corresponding to the initial ephemeris data is determined, which may specifically include:

[0064] Step 202: Determine the first orbital interval time from the initial ephemeris data, and determine the orbital interval number corresponding to the first orbital interval time as the first orbital interval number.

[0065] The first epoch time can be the epoch time corresponding to the first predicted ephemeris data in the initial ephemeris data. Specifically, it can be found in the first predicted ephemeris data in the initial ephemeris data, at the two epoch times corresponding to the first change of the satellite position Z component from positive to negative (i.e., the descending node changes from positive to negative; the ascending node changes from negative to positive). and The midpoint between two epochs is taken as the first epoch-breaking point. .

[0066] Therefore, the orbital circle number corresponding to the first orbital division point is determined as the first orbital circle number. For example, if the first orbital division point time in the initial ephemeris data is... ,but The corresponding orbital loop number is the first orbital loop number. Let Corresponding to the first orbit number Then, proceed with subsequent steps to generate the corresponding initial circle number list.

[0067] Step 204: Iterate through the other sub-circle times in the initial ephemeris data, and determine the orbit numbers corresponding to the other sub-circle times in the initial ephemeris data based on the first orbit number corresponding to the first sub-circle time.

[0068] The other sub-circle times are the sub-circle times in the initial ephemeris data other than the first sub-circle time mentioned above. Specifically, by traversing the other sub-circle times in the initial ephemeris data and determining the orbital numbers corresponding to the other sub-circle times in the initial ephemeris data based on the first orbital number corresponding to the first sub-circle time, the orbital numbers corresponding to the other sub-circle times in the initial ephemeris data are determined.

[0069] Step 206: Generate an initial orbit number list for the initial ephemeris data based on the first orbit number corresponding to the first orbit point time in the initial ephemeris data, and the orbit numbers corresponding to the other orbit point times.

[0070] The initial orbit number list includes the first satellite identifier of the target satellite, the orbital timestamps in the initial ephemeris data, and the corresponding orbit numbers.

[0071] In this embodiment, by traversing the initial ephemeris data, the times of all sub-circles are obtained. If the total... Add one to the initial circle number list above. In the middle, store it in a database table and record the satellite number. (i.e., the first satellite identifier), orbital circle number , circling point time . middle From the The counting begins with the first circle. (Right now ) corresponds to the Circle, the second one Corresponding to the ( Circles, and so on, with the circle numbers increasing sequentially, the 1st circle... indivual Corresponding to the lock up, Based on this, the initial orbital number list for the initial ephemeris data can be obtained. .

[0072] In the above embodiments, a few minutes after the satellite enters orbit, initial ephemeris data is obtained by using initial orbit data prediction, and then short-term (e.g., 1 day) orbit number prediction is quickly generated to obtain an initial orbit number list.

[0073] In one exemplary embodiment, such as Figure 3As shown, in step 108, a periodic circle number list corresponding to the periodic ephemeris data is generated based on the periodic ephemeris data and the initial circle number list. Specifically, this may include:

[0074] Step 302: Determine the time of the first circumference from the periodic ephemeris data.

[0075] Specifically, the time corresponding to the first predicted ephemeris data in the periodic ephemeris data is determined as the first time of the first time of the first time of the first time of the first time of the first time of the second ... third time of the second time of the second time of the third time of the second time of the second time of the third time of the second time of the

[0076] Step 304: Based on the first lap point time, search the initial lap number list for the lap point time that has a first relationship with the first lap point time.

[0077] The first relationship is used to characterize that the difference between the time of the first lap point and the time of the lap point in the initial lap number list is less than or equal to a first threshold. The first threshold can be a preset time threshold, for example, the first threshold can be 60 seconds.

[0078] For example, if the time of the first circumference determined from the periodic ephemeris data is Then and In Perform a line-by-line comparison; if it meets the requirements... seconds, then As the time of the first lap point search The moment when the first relation exists at the dividing point.

[0079] Step 306: The orbit number corresponding to the found sub-circle point time is used as the orbit number corresponding to the first sub-circle point time in the periodic ephemeris data.

[0080] Specifically, the search can identify the time points that have a primary relationship with the first lap point time. Corresponding circle number This is recorded as the first sub-circle time of this forecast. Corresponding orbit number ,Right now And copy the above. To generate ,exist Delete the satisfied The record.

[0081] Step 308: Iterate through the other sub-circle times in the periodic ephemeris data, and determine the orbit numbers corresponding to the other sub-circle times in the periodic ephemeris data based on the orbit number corresponding to the first sub-circle time.

[0082] Among them, the other circumference points are those in the periodic ephemeris data excluding the first circumference point mentioned above. Other than the designated lap times.

[0083] Specifically, by traversing the other sub-circle times in the periodic ephemeris data, and based on the orbital circle number corresponding to the first sub-circle time, the orbital circle numbers corresponding to the other sub-circle times in the periodic ephemeris data are determined.

[0084] Step 310: Generate a list of periodic circle numbers for the periodic ephemeris data based on the orbital circle number corresponding to the first sub-circle point in the periodic ephemeris data and the orbital circle numbers corresponding to the other sub-circle point points respectively.

[0085] The periodic orbit number list includes the target satellite's first satellite identifier, the orbital interval times in the periodic ephemeris data, and the corresponding orbital orbit number.

[0086] In this embodiment, by traversing the periodic ephemeris data, all circumference point times are obtained and appended to the above. In the middle, the satellite number is stored in a database table. (i.e., the first satellite identifier), orbital circle number , circling point time . The first one (Right now ) corresponds to the first Right now , Then the second one Corresponding to the ( Circles, and so on, with the circle numbers added sequentially, until the 1st circle is reached. indivual Corresponding to the lock up, Based on this, a list of periodic circle numbers for periodic ephemeris data can be obtained. The above process is repeated after the next ephemeris forecast, thus updating the forecast cyclically. .

[0087] In the aforementioned periodic forecasting process, the periodic ephemeris data is forecasted by combining the initial circle number list from the short-term forecast, thereby obtaining a periodic circle number list with relatively reliable temporal sequence.

[0088] In one exemplary embodiment, such as Figure 4 As shown, in step 110, a lap number prediction list is generated based on the initial lap number list and the periodic lap number list, which may specifically include:

[0089] Step 402: Determine the orbit number corresponding to the first orbit point in the periodic ephemeris data, and delete records with orbit numbers greater than or equal to the initial orbit number list.

[0090] Specifically, determine the time of the first circumference point in the periodic ephemeris data. Corresponding orbit number and from the initial circle number list Delete the number of orbits that is greater than or equal to the orbit number. The record.

[0091] Step 404: Merge the periodic circle number list with the initial circle number list after deleting records to obtain the circle number prediction list.

[0092] By using the above-determined list of periodic circle numbers The initial circle number list after deleting records in the above steps Merge the periodic circle number list. The initial circle number list appended to the above deleted records In order to obtain a merged list of continuous circle number forecasts. 。

[0093] In an exemplary embodiment, after generating the orbit number prediction list based on the initial orbit number list and the periodic orbit number list in step 110, the method may further include: upon receiving post-hoc orbit data for the target satellite, revising the orbit number prediction list based on the post-hoc orbit data to obtain a revised orbit number prediction list. The post-hoc orbit data includes the target satellite's post-hoc precise ephemeris data, post-hoc instantaneous root, and the corresponding on-board accumulated orbit number.

[0094] For example, several hours after the satellite enters orbit, the telemetry, tracking, and command (TT&C) center receives raw GNSS measurement data (RENIX format), navigation message data, and other data transmission data. After fusion processing, it generates post-hoc precise ephemeris data and post-hoc instantaneous root data. For instance, this post-hoc precise ephemeris data can be released weekly. The post-hoc precise ephemeris data can contain data from the past approximately 11 days, with each point every 15 seconds providing the satellite's epoch time, three-dimensional position, and three-dimensional velocity in the J2000.0 geocentric inertial frame.

[0095] Then, the time of the first eclipse point is determined from post-hoc, precise ephemeris data. The corresponding circle number .make The remaining orbital times are then traversed through the subsequent precise ephemeris data to determine the orbital numbers corresponding to each of these times. Based on this, the orbital times calculated in this study are used to determine the orbital numbers of the remaining orbital times. and circle number For the above list of circle number forecasts Make corrections. For example, you could delete the lap number prediction list. Records with orbit numbers greater than or equal to the accumulated orbit number M on the satellite, and include all orbit point times calculated in this operation. and circle number Add to In this process, a revised list of lake number predictions is obtained. By dynamically correcting the lake numbers using post-event orbital data, the prediction list continuously adapts to changes caused by orbital perturbations, thus maintaining long-term, high-precision predictions of future lake numbers and significantly improving the accuracy of lake number predictions.

[0096] In one exemplary embodiment, such as Figure 5 As shown, after generating the round number prediction list based on the initial round number list and the periodic round number list in step 110, the above method may further include:

[0097] Step 502: Upon receiving the post-hoc orbit data for the target satellite, determine the measurement sub-circle time from the post-hoc orbit data.

[0098] The post-orbital data includes the target satellite's precise post-orbital ephemeris data, post-orbital root of reference, and corresponding on-board accumulated orbit numbers. Specifically, several hours after the satellite enters orbit, the telemetry, tracking, and command (TT&C) center receives the raw GNSS measurement data (RENIX format), navigation message data, and other data transmission data, and can then perform precise post-orbital orbit determination to generate precise post-orbital ephemeris data. For example, this precise post-orbital ephemeris data can be released weekly. The precise post-orbital ephemeris data can contain data from the past approximately 11 days, with each point every 15 seconds providing the satellite's epoch time, three-dimensional position, and three-dimensional velocity in the J2000.0 geocentric inertial frame.

[0099] Then, the time of the first sub-circle point in the post-hoc precise ephemeris data is calculated. This involves finding the two epochs in the manually subscribed latest post-hoc precise ephemeris data corresponding to the first change in the Z-component from positive to negative (decreasing node from positive to negative; ascending node from negative to positive). and The midpoint between the two times is taken as the first lap point. , The corresponding first circle number is denoted as .

[0100] Step 504: Based on the measured lap time, search the lap number prediction list for the predicted lap time that has a second relationship with the measured lap time.

[0101] The second relationship is used to characterize a situation where the difference between the measured lap time and the predicted lap time in the lap number prediction list is less than or equal to a second threshold. The second threshold can be a preset time threshold, for example, 60 seconds.

[0102] For example, by retrieving the previously saved list of lap number predictions from a database table. ,Will and In Compare each item one by one and find the first one that satisfies the condition. seconds ,but The predicted lap time is the time that has a second relationship with the measured lap time.

[0103] Step 506: Determine the orbit number corresponding to the predicted orbital time, and obtain the corresponding orbital time deviation based on the orbital number.

[0104] Pennant time deviation refers to the time difference between the measured lap time and the predicted lap time for laps with the same lap number. Specifically, based on the above steps, the predicted lap time that has a second relationship with the measured lap time is determined. Then, in the lap number prediction list Search and Corresponding circle number and will Recorded as Corresponding circle number .

[0105] Then iterate through the other eclipse points in the post-hoc precise ephemeris data, and based on the first eclipse point time... Corresponding orbit number To determine the times of all orbital points in the subsequent precise ephemeris data. and the corresponding circle number Among them, circle number From the The circles begin to accumulate, thus generating a list of circle numbers. And record it in the log, and identify the first satellite. , , The value is appended to the circle number list. middle.

[0106] Then calculate the list of circle numbers. With the list of circle numbers The time deviation of the lap points for laps with the same middle circle number. Specifically, when and When the middle circle numbers are the same, calculate the time deviation of the corresponding lap points one by one. And record it in the log.

[0107] Step 508: Dynamically correct based on the time deviation of the lap point.

[0108] In one scenario, dynamic correction is performed based on the deviation of the orbiting point time. Specifically, this may include: if there is a situation where the deviation of the orbiting point time is greater than the second threshold, the orbit number prediction list is corrected based on the ex-post instantaneous root of the corresponding measured orbiting point time and the accumulated orbit number on the satellite, so as to obtain the corrected orbit number prediction list.

[0109] For example, taking a second threshold of 60 seconds as an example, if there is satisfy If the time is less than 1 second, manually input the post-event root and its corresponding ephemeris time and the accumulated orbit number M. Then, predict the ephemeris based on high-precision orbit extrapolation, and set cnpt=cnpt_3 to predict orbit numbers to update the orbit number prediction list. ， Implement a list of zodiac number predictions The correction involves manually forecasting zonal numbers when the forecast error at each zonal point consistently exceeds a threshold, thereby correcting the zonal number list for future periods and improving the accuracy of zonal number forecasts.

[0110] In another scenario, dynamic correction based on the deviation of the lap point time can also include: if there is no lap point time deviation greater than the second threshold, determining the smoothing deviation based on UKF-RTS filtering; and correcting the initial deviation based on the smoothing deviation.

[0111] For example, taking a second threshold of 60 seconds as an example, if all conditions are met... For seconds, UKF-RTS is used. Filtering and smoothing are then performed. For example, the parameters of the UKF (Unscented Kalman Filter) are first initialized, including the state vector, covariance matrix, process noise covariance, and measurement noise covariance. The state vector contains six orbital states (position and velocity components) and... The state dimension is 7, the observation dimension is 1, and only observations are performed. The initial state is based on post-hoc, precise ephemeris data. Position, velocity and .

[0112] Then, forward UKF filtering is performed. The first step generates a σ-point, which is used for prediction. The second step calculates the predicted process noise, mean, and covariance based on the σ-point and weights, and updates the state estimate using the predicted σ-point and the measured value. The third step calculates the Kalman gain based on the predicted covariance and the covariance of the measurement noise. The Kalman gain is used to update the mean and covariance of the state until iteration stops 30 days after the initial time. The fourth step stores the forward-filtered state and covariance, and the predicted state and covariance for all time points.

[0113] Then, reverse smoothing (RTS, a type of smoother) is performed. Based on the state and covariance of the UKF output, a high-precision initial state after smoothing is obtained by reverse recursion. The last time step of smoothing is equal to the last time step of filtering. Reverse smoothing begins from the second-to-last time step and continues until the first time step, calculating the smoothed state and smoothing covariance for all time steps. The smoothing gain is calculated using the state transition matrix, the smoothed state and smoothing covariance are updated, and the smoothing results for all time steps are stored. Since UKF-RTS can improve the accuracy of state estimation for nonlinear systems, and forward UKF filtering handles nonlinear problems through unscented transformation, it can provide more accurate state mean and covariance estimates; backward RTS smoothing performs backward correction on state estimation by integrating past and future observation data, thus effectively compensating for the accumulated error of UKF and improving prediction accuracy.

[0114] Finally, during the initialization of the extrapolation model, the closest match is found from the smoothed results. (The six root numbers correspond to epochal times) ,make ,based on The forecast initial time deviation of the periodic ephemeris data is updated to correct the forecast initial time of the periodic ephemeris data, thereby enabling the updating of the periodic circle number list and the correction of the circle number forecast list.

[0115] The above embodiment realizes a closed-loop feedback control of "forecast-measurement-correction". The closed loop is formed by measurement (on-board GNSS measurement), and the extrapolation error is corrected by forecast and subsequent precise ephemeris. The orbit number is predicted in a loop, so that the output of the system (the predicted orbit number and the time of the orbit point) continuously converges to the true value, which further suppresses the divergence caused by extrapolation error and perturbation, and improves the accuracy of orbit number prediction.

[0116] In one exemplary embodiment, such as Figure 6 As shown, after generating the round number prediction list based on the initial round number list and the periodic round number list in step 110, the above method may further include:

[0117] Step 602: In response to the satellite tracking command from the target station, query the corresponding satellite tracking information in the circle number prediction list according to the satellite tracking command.

[0118] The satellite tracking command includes the second satellite identifier of the satellite to be tracked, the station identifier of the target station, the corresponding arc segment identifier, the arrival time, and the departure time. The satellite tracking command can be an instruction or command for tracking the satellite; it can be issued by the target station or obtained from the message middleware, and this embodiment does not limit this.

[0119] Specifically, upon receiving a satellite tracking command, a target orbit number prediction list matching the second satellite identifier can be determined from the orbit number prediction list. A match can occur if the first satellite identifier in the orbit number prediction list is the same as the second satellite identifier. In this case, the target orbit number prediction list is a selection of orbit number prediction information related to the first satellite identifier that matches the second satellite identifier. Then, orbit number prediction is performed based on the identifiers of the predicted orbit times in the target orbit number prediction list. These identifiers include the descending node identifier (DN) and the ascending node identifier (AN).

[0120] For example, if the predicted orbital point time in the target orbit number prediction list is determined to be the descending node, the target predicted orbital point time that is greater than the arrival time and closest to the arrival time is queried in the target orbit number prediction list, and the target predicted orbital number corresponding to the target predicted orbital point time is determined. The target predicted orbital point time and the target predicted orbital number are determined as the corresponding satellite tracking information.

[0121] For example, if the predicted orbital point time in the target orbital number prediction list is determined to be the ascending node, the target predicted orbital point time that is less than the arrival time and closest to the arrival time is queried in the target orbital number prediction list, and the target predicted orbital number corresponding to the target predicted orbital point time is determined. The target predicted orbital point time and the target predicted orbital number are determined as the corresponding satellite tracking information.

[0122] Step 604: Generate satellite orbit number prediction information based on satellite tracking instructions and corresponding satellite tracking information.

[0123] Specifically, satellite tracking commands and corresponding satellite tracking information can be merged to generate satellite orbital circle number prediction information. The final satellite orbital circle number prediction information can include satellite identifiers, orbital circle numbers, station identifiers, arc segment identifiers, arrival times, and departure times. This prediction information can then be disseminated or returned to a message middleware based on mission requirements, thus providing relatively accurate orbital circle number data for planning ground control station tracking plans, data transmission and reception plans, remote control command plans, or remote sensing imaging missions.

[0124] In an exemplary embodiment, the aforementioned ephemeris data (including initial ephemeris data and periodic ephemeris data) can be determined using a high-precision orbit extrapolation model. This high-precision orbit extrapolation model can calculate two-body acceleration and perturbation acceleration based on Kepler six roots (initial orbit roots or instantaneous roots for precise orbit determination) and a dynamic model. Then, using numerical integration, the continuous time interval is discretized. At each discrete time point, the satellite perturbation acceleration, position, and velocity at the current time point are integrated to obtain the position and velocity vectors at the next time point.

[0125] Numerical integration methods solve the differential equations of satellite motion directly using numerical methods. The first-order differential equations of satellite motion can be described by the following equation (1):

[0126] (1)

[0127] in, Represents the satellite's position vector. Represents the satellite's velocity vector. Represents the Earth's gravitational constant. This represents the acceleration generated by various perturbation forces.

[0128] Satellite motion equations are typically described in the J2000.0 geocentric inertial coordinate system, and satellite motion integrals are also calculated in this coordinate system. The specific calculation process is as follows: Figure 7 As shown, it includes:

[0129] (1) Initialization

[0130] Specifically, initialization can be based on input parameters. For example, input parameters may include the six Keplerian roots (semi-major axis, eccentricity, inclination, right ascension of the ascending node, argument of perihelion, and mean perihelion), and the corresponding epoch times for the six roots. Extrapolated time parameters (including forecast initial time) Forecast duration Forecast step length Prediction of initial time deviation Satellite physical characteristics (including satellite mass, equivalent windward area, atmospheric damping coefficient CD, and solar radiation pressure coefficient CR) and perturbation models and parameters (including Earth rotation parameters and Earth's gravitational constant) Geomagnetic AP, solar activity index F10.7, mean solar radiation flux, etc.

[0131] The configuration of the specified perturbation model can include the Earth gravitational field model EGM2008 (70x70), the atmospheric density model NRLMSISE-00 / 2000, the planetary ephemeris DE405, the solid tide JERS2010 standard, the ocean tide FES2004 model, the semi-diurnal tide IERS2010 standard, the nutation model IAU2000, the N-body perturbation DE421, the light pressure model ECOM2 empirical model (Arnold D, 2015), the relativistic effects IERS2010 (Schwartzchild), and the latest IERS files, etc.

[0132] Initialization includes loading parameters and models, including the Kepler six roots, extrapolated time parameters, satellite physical characteristic parameters, perturbation models, and parameters into memory; and setting the initial forecast time. Set the integrator parameters; for example, the integrator type can be fourth-order Runge-Kutta (RK4), and the initial step size can be... Relative error tolerance Absolute error tolerance .

[0133] (2) Determine the initial state vector

[0134] Specifically, the six roots can be converted into initial state vectors of position and velocity based on Kepler's equations.

[0135] (3) Calculate all perturbation accelerations

[0136] Based on the satellite's physical characteristics parameters, the specified perturbation models and parameters, calculate the perturbation acceleration of the satellite at the current moment. Then calculate the sum of all perturbation accelerations. .

[0137] (4) Calculate the total acceleration

[0138] Total acceleration This is the sum of the two-body acceleration and all perturbation accelerations. First, calculate the acceleration of the two bodies at the current moment. Then calculate the total acceleration. .

[0139] (5) Numerical integration

[0140] Numerical integration can use RK4 to balance accuracy and efficiency. Based on the current state... and Solve the new state iteratively. Each step-size integral outputs the epoch time, position X component, position Y component, position Z component, velocity X component, velocity Y component, and velocity Z component under J2000.0.

[0141] (6) Update time and status

[0142] The epoch time of the forecast output is based on Starting from a certain point, every other step... Forecast a point, update the state vector, and continue until the forecast ends. Stop forecasting. Update the state and time in each iteration. , , and recalculate , This serves as the input to the integrator. Based on this, long-term, high-precision forecasts of ephemeris data can be achieved.

[0143] In one exemplary embodiment, such as Figure 8 As shown, the above-mentioned method for predicting satellite orbit numbers is further illustrated below through a specific embodiment, which specifically includes:

[0144] (1) Initialization

[0145] Configure satellite number (i.e., satellite identifiers), circle number forecast type ( -Initial forecast -Periodic forecast, - Manual forecast), zone markings ( -Descending intersection, - Ascending node).

[0146] Configure orbit extrapolation time parameters, including the predicted initial time. The default is the satellite's orbital insertion time and the forecast duration. (Day), forecast step length (seconds), forecast initial time deviation 0.000 (seconds).

[0147] Configure satellite physical characteristic parameters, and configure the specified perturbation model and parameters.

[0148] The satellite's orbit insertion time and initial orbit elements are automatically obtained from the message middleware of the telemetry, tracking, and command center.

[0149] A unified coordinate and time system is implemented, converting all input data and calculation processes to the geocentric inertial coordinate system J2000.0 and Beijing time for processing.

[0150] (2) High-precision orbit extrapolation

[0151] Within minutes of the satellite entering orbit, the telemetry, tracking, and command (TT&C) center determines the initial orbital elements based on ground-based external measurement data and automatically predicts the ephemeris based on these initial orbital elements (Kepler six elements). , The satellite's orbital insertion time. (One day after the time of entry into orbit), step size Second.

[0152] Within hours of the satellite's entry into orbit, the telemetry, tracking, and command (TT&C) center will receive ground-based external measurement data and onboard GNSS engineering telemetry data, which will be combined with the initial orbit data to perform precise orbit determination. During the satellite's on-orbit operation, precise orbit determination results will be released at least twice daily. This is based on the instantaneous roots (Kepler six roots) and their corresponding times for each precise orbit determination. Automatic ephemeris prediction, making , , (from (30 days after the start date), step length Second.

[0153] When periodically revising the circle number dynamically, it is also possible to base it on the post-event instantaneous root and its corresponding time. Manually predict ephemeris, making , , Step length Second.

[0154] (3) Forecast circle number

[0155] Determining the forecast type based on high-precision forecast ephemeris. Initial forecasts, periodic forecasts, and manual forecasts are performed separately, recording satellite numbers, orbital orbit numbers, and orbital interval times, and saving these records to a database table. The orbital orbit number list is automatically updated at least twice daily.

[0156] (4) Dynamically correct circle number

[0157] Several hours after the satellite enters orbit, the telemetry, tracking, command and control center receives raw GNSS measurement data (RENIX format), navigation message data, and other data transmission data. It then conducts post-orbit precise orbit determination to generate a precise ephemeris, which is released weekly. The post-orbit precise ephemeris contains data from the past approximately 11 days, providing information such as the satellite's epoch time, three-dimensional position, and three-dimensional velocity in the J2000.0 geocentric inertial frame at 1 point every 15 seconds.

[0158] We manually subscribe to the latest post-event precise ephemeris every week, iterate through all measured circle point times, calculate the deviation between the measured circle point times and the predicted circle point times, and determine whether the deviation exceeds a threshold. If all deviations do not exceed the threshold, we use UKF-RTS filtering to calculate the average deviation. ,use Correct the initial state of the extrapolation model; if there is a deviation exceeding the threshold, manually predict the ephemeris and orbit number, and input the post-event instantaneous root and its corresponding time. Adding circles to stars ,make Execute steps (2) and (3) to update the circle number list.

[0159] (5) Locate the circle number corresponding to the measurement and control arc segment.

[0160] Automatically retrieves tracking and forecast information from domestic stations via the message middleware, including satellite identification numbers. Station code, measurement and control arc segment Arrival time, departure time.

[0161] Based on the arrival time of each measurement and control arc segment, if Find the circle number in the circle number list that corresponds to the arrival time being less than the descending intersection time and the closest time to the descending intersection. This circle number is the circle number for that telemetry and control arc segment; if Then, we should look for the circle number corresponding to the entry time being greater than the ascending node time and the time closest to the ascending node.

[0162] (6) Merging forecast information

[0163] Merge satellite numbers Track circle number, station code, and telemetry arc segment The system automatically publishes forecast information such as arrival and departure times to the message middleware, providing circle number forecasts. This information is then used to support ground control station tracking plans, data transmission and reception plans, remote control command plans, and remote sensing imaging mission planning.

[0164] It should be understood that although the steps in the flowcharts of the embodiments described above are shown sequentially according to the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless explicitly stated herein, there is no strict order restriction on the execution of these steps, and they can be executed in other orders. Moreover, at least some steps in the flowcharts of the embodiments described above may include multiple steps or multiple stages. These steps or stages are not necessarily completed at the same time, but can be executed at different times. The execution order of these steps or stages is not necessarily sequential, but can be performed alternately or in turn with other steps or at least some of the steps or stages in other steps. It is understood that the steps in different embodiments can be freely combined as needed, and all non-contradictory solutions formed by such combinations are within the scope of protection of this application.

[0165] Based on the same inventive concept, this application also provides a satellite orbit number prediction device for implementing the satellite orbit number prediction method described above. The solution provided by this device is similar to the implementation described in the above method; therefore, the specific limitations in one or more satellite orbit number prediction device embodiments provided below can be found in the limitations of the satellite orbit number method described above, and will not be repeated here.

[0166] In one exemplary embodiment, such as Figure 9 As shown, a satellite orbit number prediction device is provided, comprising: an initial data acquisition module 902, an initial orbit number determination module 904, a periodic data acquisition module 906, a periodic orbit number determination module 908, and a prediction orbit number generation module 910, wherein:

[0167] The initial data acquisition module 902 is used to acquire the initial orbit data of the target satellite based on the first satellite identifier of the target satellite. The initial orbit data includes the orbit insertion time of the target satellite and the corresponding initial orbital elements.

[0168] The initial orbit number determination module 904 is used to determine the corresponding initial ephemeris data based on the initial orbit data of the target satellite and the pre-configured first time parameters, and to determine the initial orbit number list corresponding to the initial ephemeris data.

[0169] The periodic data acquisition module 906 is used to determine the corresponding periodic ephemeris data based on the orbit measurement data, the initial orbit data, and the pre-configured second time parameter when it receives orbit measurement data for the target satellite.

[0170] The periodic circle number determination module 908 is used to generate a periodic circle number list corresponding to the periodic ephemeris data based on the periodic ephemeris data and the initial circle number list.

[0171] The prediction orbit number generation module 910 is used to generate a prediction orbit number list based on the initial orbit number list and the periodic orbit number list. The prediction orbit number list includes the first satellite identifier of the target satellite, the prediction orbit point time, and the corresponding prediction orbit number.

[0172] In an exemplary embodiment, the initial orbit number determination module is further configured to: determine the first orbital point time from the initial ephemeris data, and determine the orbital orbit number corresponding to the first orbital point time as the first orbital orbit number; traverse the other orbital point times in the initial ephemeris data, and determine the orbital orbit numbers corresponding to the other orbital point times in the initial ephemeris data according to the first orbital orbit number corresponding to the first orbital orbit number; the other orbital point times are the orbital point times in the initial ephemeris data other than the first orbital point time; generate an initial orbital orbit number list for the initial ephemeris data according to the first orbital orbit number corresponding to the first orbital point time in the initial ephemeris data and the orbital orbit numbers corresponding to the other orbital point times; the initial orbital orbit number list includes the first satellite identifier of the target satellite, the orbital point times in the initial ephemeris data, and the corresponding orbital orbit numbers.

[0173] In an exemplary embodiment, the periodic circle number determination module is further configured to: determine the first sub-circle point time from the periodic ephemeris data; search the initial circle number list for a sub-circle point time that has a first relationship with the first sub-circle point time based on the first sub-circle point time; the first relationship is used to characterize that the difference between the first sub-circle point time and the sub-circle point time in the initial circle number list is less than or equal to a first threshold; use the orbital circle number corresponding to the found sub-circle point time as the orbital circle number corresponding to the first sub-circle point time in the periodic ephemeris data; and traverse other sub-circles in the periodic ephemeris data. At each point in time, based on the orbital orbit number corresponding to the first orbital orbit point, the orbital orbit numbers corresponding to other orbital orbit points in the periodic ephemeris data are determined; the other orbital orbit points are the orbital orbit points in the periodic ephemeris data other than the first orbital orbit point; based on the orbital orbit number corresponding to the first orbital orbit point in the periodic ephemeris data and the orbital orbit numbers corresponding to the other orbital orbit points, a periodic orbital ...

[0174] In an exemplary embodiment, the prediction orbit number generation module is further configured to: determine the orbit number corresponding to the first orbit point time in the periodic ephemeris data; delete records greater than or equal to the orbit number from the initial orbit number list; and merge the periodic orbit number list with the initial orbit number list after deleting records to obtain an orbit number prediction list.

[0175] In an exemplary embodiment, the apparatus further includes a correction module, configured to, upon receiving post-hoc orbit data for the target satellite, correct the orbit number prediction list based on the post-hoc orbit data to obtain a corrected orbit number prediction list; the post-hoc orbit data includes post-hoc precise ephemeris data, post-hoc instantaneous root data, and corresponding on-board accumulated orbit numbers of the target satellite.

[0176] In an exemplary embodiment, the correction module is further configured to: upon receiving post-hoc orbit data for the target satellite, determine the measurement orbital time from the post-hoc orbit data; based on the measurement orbital time, search the orbital number prediction list for a predicted orbital time that has a second relationship with the measurement orbital time; the second relationship is used to characterize that the difference between the measurement orbital time and the predicted orbital time in the orbital number prediction list is less than or equal to a first threshold; determine the orbital number corresponding to the predicted orbital time, obtain the corresponding orbital time deviation based on the orbital number; and perform dynamic correction based on the orbital time deviation.

[0177] In an exemplary embodiment, the correction module is further configured to: if there is a case where the deviation of the orbiting point time is greater than the second threshold, correct the orbit number prediction list based on the ex-post instantaneous root of the corresponding measured orbiting point time and the accumulated orbit number on the satellite, to obtain a corrected orbit number prediction list.

[0178] In an exemplary embodiment, the correction module is further configured to: if there is no case where the deviation of the lap point time is greater than the second threshold, determine the smoothing deviation based on UKF-RTS filtering; and correct the initial deviation according to the smoothing deviation.

[0179] In an exemplary embodiment, a forecast response module is further included, configured to: respond to a satellite tracking instruction from a target station, query the corresponding satellite tracking information in the orbit number forecast list according to the satellite tracking instruction; the satellite tracking instruction carries a second satellite identifier of the satellite to be tracked, the station identifier of the target station, the corresponding arc segment identifier, the entry time and the exit time; and generate satellite orbit number forecast information according to the satellite tracking instruction and the corresponding satellite tracking information.

[0180] In an exemplary embodiment, the forecast response module is further configured to: determine a target orbit number forecast list that matches the second satellite identifier of the satellite to be tracked, based on the first satellite identifier in the orbit number forecast list; if the forecast sub-circle time in the target orbit number forecast list is determined to be a descending node, query the target orbit number forecast list for a target forecast sub-circle time that is greater than the arrival time and closest to the arrival time; determine the target forecast orbit number corresponding to the target forecast sub-circle time, and determine the target forecast sub-circle time and the target forecast orbit number as corresponding satellite tracking information.

[0181] In an exemplary embodiment, the forecast response module is further configured to: determine a target orbit number forecast list that matches the second satellite identifier of the satellite to be tracked, based on the first satellite identifier in the orbit number forecast list; if the forecast sub-circle time in the target orbit number forecast list is determined to be the ascending node, query the target orbit number forecast list for a target forecast sub-circle time that is less than the arrival time and closest to the arrival time; determine the target forecast orbit number corresponding to the target forecast sub-circle time, and determine the target forecast sub-circle time and the target forecast orbit number as corresponding satellite tracking information.

[0182] Each module in the aforementioned satellite orbit number prediction device can be implemented entirely or partially through software, hardware, or a combination thereof. These modules can be embedded in or independent of the processor in a computer device, or stored in the computer device's memory as software, so that the processor can call and execute the corresponding operations of each module.

[0183] In one exemplary embodiment, a computer device is provided, the internal structure of which can be as shown in the figure. Figure 10As shown, the computer device includes a processor, memory, input / output interface, communication interface, display unit, and input device. The processor, memory, and input / output interface are connected via a system bus, and the communication interface, display unit, and input device are also connected to the system bus via the input / output interface. The processor provides computational and control capabilities. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs stored in the non-volatile storage media. The input / output interface is used for exchanging information between the processor and external devices. The communication interface is used for wired or wireless communication with external terminals; wireless communication can be achieved through Wi-Fi, mobile cellular networks, Near Field Communication (NFC), or other technologies. When executed by the processor, the computer program implements a method for predicting satellite orbit numbers. The display unit is used to create a visually visible image and can be a display screen, projection device, or virtual reality imaging device. The display screen can be an LCD screen or an e-ink screen. The input device of the computer device can be a touch layer covering the display screen, or buttons, trackballs, or touchpads set on the casing of the computer device, or external keyboards, touchpads, or mice, etc.

[0184] Those skilled in the art will understand that Figure 10 The structure shown is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the computer device to which the present application is applied. Specific computer devices may include more or fewer components than those shown in the figure, or combine certain components, or have different component arrangements.

[0185] In one exemplary embodiment, a computer device is provided, including a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to implement the steps in the above-described method embodiments.

[0186] In one embodiment, a computer-readable storage medium is provided having a computer program stored thereon, which, when executed by a processor, implements the steps in the above method embodiments.

[0187] In one embodiment, a computer program product is provided, including a computer program that, when executed by a processor, implements the steps in the above method embodiments.

[0188] It should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data used for analysis, data stored, data displayed, etc.) involved in this application are all information and data authorized by the user or fully authorized by all parties, and the collection, use and processing of the relevant data must comply with relevant regulations.

[0189] Those skilled in the art will understand that all or part of the processes in the methods of the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods. Any references to memory, databases, or other media used in the embodiments provided in this application can include at least one of non-volatile memory and volatile memory. Non-volatile memory can include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random access memory (ReRAM), magnetic random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc. Volatile memory can include random access memory (RAM) or external cache memory, etc. By way of illustration and not limitation, RAM can take many forms, such as Static Random Access Memory (SRAM) or Dynamic Random Access Memory (DRAM). The databases involved in the embodiments provided in this application may include at least one type of relational database and non-relational database. Non-relational databases may include, but are not limited to, blockchain-based distributed databases. The processors involved in the embodiments provided in this application may be general-purpose processors, central processing units, graphics processing units, digital signal processors, programmable logic devices, quantum computing-based data processing logic devices, artificial intelligence (AI) processors, etc., and are not limited to these.

[0190] The technical features of the above embodiments can be combined in any way. For the sake of brevity, 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 application.

[0191] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of this patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this application should be determined by the appended claims.

Claims

1. A method for predicting satellite orbit numbers, characterized in that, The method includes: The initial orbit data of the target satellite is obtained based on the first satellite identifier of the target satellite. The initial orbit data includes the orbit insertion time of the target satellite and the corresponding initial orbital elements. The initial ephemeris data corresponding to the target satellite and the pre-configured first time parameters are determined, and the initial orbit number list corresponding to the initial ephemeris data is determined. Upon receiving orbit measurement data for the target satellite, the corresponding periodic ephemeris data is determined based on the orbit measurement data, the initial orbit data, and the pre-configured second time parameter. Based on the periodic ephemeris data and the initial circle number list, generate a periodic circle number list corresponding to the periodic ephemeris data; A predicted orbit number list is generated based on the initial orbit number list and the periodic orbit number list. The predicted orbit number list includes the first satellite identifier of the target satellite, the predicted orbit point time, and the corresponding predicted orbit number.

2. The method according to claim 1, characterized in that, The process of determining the initial orbit number list corresponding to the initial ephemeris data includes: The first orbital division point time is determined from the initial ephemeris data, and the orbital circle number corresponding to the first orbital division point time is determined as the first orbital circle number; Iterate through the other orbital times in the initial ephemeris data, and determine the orbital numbers corresponding to the other orbital times in the initial ephemeris data based on the first orbital number corresponding to the first orbital time; the other orbital times are the orbital times in the initial ephemeris data other than the first orbital time. Based on the first orbit number corresponding to the first orbital ...

3. The method according to claim 1, characterized in that, The step of generating a periodic circle number list corresponding to the periodic ephemeris data based on the periodic ephemeris data and the initial circle number list includes: The first circumference point time is determined from the periodic ephemeris data; Based on the first lap division time, find a lap division time in the initial lap number list that has a first relationship with the first lap division time; the first relationship is used to characterize that the difference between the first lap division time and the lap division time in the initial lap number list is less than or equal to a first threshold. The orbit number corresponding to the found sub-circle point time is used as the orbit number corresponding to the first sub-circle point time in the periodic ephemeris data. The system iterates through the other orbital moments in the periodic ephemeris data, and determines the orbital numbers corresponding to the other orbital moments in the periodic ephemeris data based on the orbital number corresponding to the first orbital moment; the other orbital moments are the orbital moments in the periodic ephemeris data other than the first orbital moment. Based on the orbital orbit number corresponding to the first orbital orbit point in the periodic ephemeris data, and the orbital orbit numbers corresponding to the other orbital orbit points, a periodic orbital ...

4. The method according to claim 1, characterized in that, The step of generating a zoning number prediction list based on the initial zoning number list and the periodic zoning number list includes: Determine the orbit number corresponding to the first orbit point in the periodic ephemeris data, and delete records that are greater than or equal to the orbit number from the initial orbit number list; The periodic circle number list is merged with the initial circle number list after deleting records to obtain the circle number prediction list.

5. The method according to claim 1, characterized in that, After generating the lap number prediction list based on the initial lap number list and the periodic lap number list, the method further includes: Upon receiving post-hoc orbit data for the target satellite, the orbit number prediction list is corrected based on the post-hoc orbit data to obtain a corrected orbit number prediction list; the post-hoc orbit data includes the target satellite's post-hoc precise ephemeris data, post-hoc instantaneous root, and corresponding on-board accumulated orbit number.

6. The method according to claim 1, characterized in that, After generating the lap number prediction list based on the initial lap number list and the periodic lap number list, the method further includes: Upon receiving post-hoc orbital data for the target satellite, the measurement declination time is determined from the post-hoc orbital data; Based on the measured lap time, a predicted lap time that has a second relationship with the measured lap time is found in the lap number prediction list; the second relationship is used to characterize that the difference between the measured lap time and the predicted lap time in the lap number prediction list is less than or equal to a first threshold. Determine the orbit number corresponding to the predicted orbital point time, and obtain the corresponding orbital point time deviation based on the orbital circle number; Dynamic correction is performed based on the time deviation of the lap point.

7. The method according to claim 6, characterized in that, The dynamic correction based on the time deviation of the lap point includes: If there is a case where the deviation of the orbital point time is greater than the second threshold, the orbital number prediction list is corrected based on the post-event root of the corresponding measured orbital point time and the accumulated orbital number on the satellite, to obtain the corrected orbital number prediction list.

8. The method according to claim 7, characterized in that, The method further includes: If there is no case where the deviation of the lap point time is greater than the second threshold, the smoothing deviation is determined based on UKF-RTS filtering; The initial deviation is corrected based on the smoothing deviation.

9. The method according to any one of claims 1 to 8, characterized in that, After generating the lap number prediction list based on the initial lap number list and the periodic lap number list, the method further includes: In response to a satellite tracking command from the target station, the corresponding satellite tracking information is queried from the circle number prediction list according to the satellite tracking command; the satellite tracking command carries the second satellite identifier of the satellite to be tracked, the station identifier of the target station, the corresponding arc segment identifier, the entry time and the exit time; Satellite orbit number prediction information is generated based on the satellite tracking instructions and corresponding satellite tracking information.

10. The method according to claim 9, characterized in that, The step of querying the corresponding satellite tracking information in the circle number prediction list according to the satellite tracking command includes: Based on the first satellite identifier in the circle number prediction list, determine the target circle number prediction list that matches the second satellite identifier of the satellite to be tracked; If the predicted lap time in the target lap number prediction list is determined to be a descending intersection, then the target predicted lap time that is greater than the arrival time and closest to the arrival time is queried from the target lap number prediction list. Determine the target's predicted orbit number corresponding to the predicted orbital time of the target, and then use the predicted orbital time of the target and the predicted orbital number as the corresponding satellite tracking information.

11. The method according to claim 9, characterized in that, The step of querying the corresponding satellite tracking information in the circle number prediction list according to the satellite tracking command includes: Based on the first satellite identifier in the circle number prediction list, determine the target circle number prediction list that matches the second satellite identifier of the satellite to be tracked; If the predicted lap time in the target lap number prediction list is determined to be the ascending node, then the target predicted lap time that is less than the arrival time and closest to the arrival time is queried from the target lap number prediction list. Determine the target's predicted orbit number corresponding to the predicted orbital time of the target, and then use the predicted orbital time of the target and the predicted orbital number as the corresponding satellite tracking information.

12. A satellite orbit number prediction device, characterized in that, The device includes: The initial data acquisition module is used to acquire the initial orbit data of the target satellite based on the first satellite identifier of the target satellite. The initial orbit data includes the orbit insertion time of the target satellite and the corresponding initial orbital elements. The initial orbit number determination module is used to determine the corresponding initial ephemeris data based on the initial orbit data of the target satellite and the pre-configured first time parameters, and to determine the initial orbit number list corresponding to the initial ephemeris data; The periodic data acquisition module is used to determine the corresponding periodic ephemeris data based on the orbit measurement data, the initial orbit data, and the pre-configured second time parameter when the orbit measurement data for the target satellite is received. The periodic circle number determination module is used to generate a periodic circle number list corresponding to the periodic ephemeris data based on the periodic ephemeris data and the initial circle number list. The prediction orbit number generation module is used to generate a prediction orbit number list based on the initial orbit number list and the periodic orbit number list. The prediction orbit number list includes the first satellite identifier of the target satellite, the prediction orbit point time, and the corresponding prediction orbit number.

13. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that, When the processor executes the computer program, it implements the steps of the method according to any one of claims 1 to 11.

14. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 11.

15. A computer program product, comprising a computer program, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 11.

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