Data Processing Method, Device, Medium and Equipment for Satellite Visible Arc Segment

Abstract

The present invention relates to a data processing method, device, medium and equipment for the visible arc segment of a satellite. The method includes: obtaining satellite orbit parameters and the position information of a ground station to be tested; setting a simulation start time, a simulation end time and a preset simulation time interval; calculating the elevation angle and the trajectory position at each preset simulation time interval; determining the starting point of the visible arc segment and the ending point of the visible arc segment; performing interpolation operation to obtain interpolation points; connecting the starting point, the trajectory positions of the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, the interpolation points and the ending point to obtain the simulated motion trajectory of the satellite to be tested. The implementation of the present invention can reduce the amount of data to be collected, reduce the simulation calculation time and improve the simulation efficiency.

Description

Technical Field

[0001] The present invention relates to the field of data processing, and in particular to a method, apparatus, medium and device for processing satellite visible arc segment data. Background Art

[0002] Currently, with the increasing number of satellite applications, space frequency resources have become more precious. Therefore, it is necessary to conduct a detailed review of each satellite declaration document to ensure that the resources such as the frequencies and orbits it uses will not interfere with existing satellites. Therefore, it is necessary to perform software simulation on the operation data provided by satellite declarants. Through the satellite orbit parameters provided by the satellite operation data, the movement trajectories of all satellites can be simulated; through the satellite operating frequency and satellite transmitting beam in the data, the signal transmission situation of the satellite to the ground can be simulated. For the current constellation to be reviewed, through the given operating frequency, GSO satellites or NGSO satellites with relatively close operating frequencies can be searched in the existing satellite network database as possible disturbed objects, and software simulation is also carried out according to their orbit parameters and beam parameters. And a ground station of the disturbed constellation is specified, and through simulation for a period of time, such as one year, sliced simulation is carried out at a time interval of 1 second, and the useless signal transmission situation of the constellation to be reviewed to the disturbed constellation in each time slice is counted, and the limit value specified by the International Telecommunication Union (ITU) is used to determine whether there is interference. For the simulation time of one year and the simulation time interval of 1 second, for a constellation with hundreds or thousands of satellites, there will be a large amount of calculations for calculating the position of each time slice, and a large amount of computing resources and waiting time need to be prepared. Summary of the Invention

[0003] This application aims to solve the technical problems in the prior art, such as excessive calculation amount of satellite simulation data, long calculation period, and excessive resource consumption during the calculation process.

[0004] To solve the above technical problems, an embodiment of this specification provides a method for processing satellite visible arc segment data, and the method includes:

[0005] Obtain the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested;

[0006] Set the simulation start time, simulation end time and preset simulation time interval of the satellite to be tested;

[0007] According to the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested, from the simulation start time to the simulation end time, calculate the elevation angle of the satellite to be tested relative to the ground station to be tested and the trajectory position corresponding to the satellite to be tested at each preset simulation time interval.

[0008] Determine the starting point of the visible arc segment according to the trajectory position of the satellite under test when the first elevation angle is greater than the preset minimum transit angle, and determine the ending point of the visible arc segment according to the trajectory position of the satellite under test when the last elevation angle is greater than the preset minimum transit angle;

[0009] Perform interpolation operations on the trajectory positions corresponding to each preset simulation time interval between the starting point and the ending point of the satellite under test to obtain interpolation points from the starting point to the ending point;

[0010] Connect the starting point, the trajectory positions corresponding to each preset simulation time interval between the starting point and the ending point of the satellite under test, the interpolation points, and the ending point to obtain the simulated motion trajectory of the satellite under test.

[0011] Further, calculating the elevation angle of the satellite under test relative to the ground station under test at each preset simulation time interval from the start time of the simulation to the end time of the simulation according to the satellite orbit parameters of the satellite under test and the position information of the ground station under test includes:

[0012] After calculating the current elevation angle corresponding to the current simulation time interval point, compare the size of the current elevation angle with the preset minimum transit angle. If the current elevation angle is less than the preset minimum transit angle, calculate the elevation angles corresponding to the two adjacent simulation time interval points of the current simulation time interval point;

[0013] Compare the size of the current elevation angle with the elevation angles of the two adjacent simulation time interval points of the current simulation time interval point. If the current elevation angle is greater than the elevation angles of the two adjacent simulation time interval points, skip a specified length of arc segment, re-determine the start time of the simulation, and start calculating the elevation angle of the satellite under test relative to the ground station under test at each preset simulation time interval based on the re-determined start time of the simulation.

[0014] Further, after determining the starting point and the ending point of the visible arc segment of the satellite under test, the method further includes:

[0015] According to the simulation time corresponding to the ending point and the satellite orbit parameters, skip the simulation span period to determine the start time of the simulation for the next visible arc segment, and start calculating the next visible arc segment from the start time of the simulation for the next visible arc segment.

[0016] Further, the step of skipping the simulation span period according to the simulation time corresponding to the ending point and the satellite orbit parameters to determine the start time of the simulation for the next visible arc segment includes:

[0017] Determine the orbital period of the satellite to be tested according to the satellite orbital parameters;

[0018] Calculate the simulation span period according to the orbital period and the simulation span ratio;

[0019] Push the simulation time interval point corresponding to the simulation span period backward from the simulation time interval point corresponding to the termination point as the simulation start time of the next visible arc segment.

[0020] Further, the method further includes:

[0021] If the elevation angle corresponding to the simulation start time is greater than the preset minimum transit angle, push the simulation start time backward by a specified simulation interval to re-determine the simulation start time.

[0022] Further, the interpolation operation using the trajectory positions of the satellite to be tested corresponding to each preset simulation time interval between the start point and the end point to obtain the interpolation points from the start point to the end point includes:

[0023] Insert a plurality of interpolation points at equal intervals between the trajectory positions of the satellite to be tested corresponding to each preset simulation time interval between the start point and the end point to obtain a plurality of interpolation points from the start point to the end point.

[0024] Further, the interpolation operation using the trajectory positions of the satellite to be tested corresponding to each preset simulation time interval between the start point and the end point to obtain the interpolation points from the start point to the end point includes:

[0025] Perform interpolation operation using the cubic spline interpolation algorithm to obtain a plurality of interpolation points from the start point to the end point.

[0026] On the other hand, an embodiment of the present specification provides a data processing device for satellite visible arc segments, and the device includes:

[0027] An information acquisition module configured to acquire the satellite orbital parameters of the satellite to be tested and the position information of the ground station to be tested;

[0028] A simulation parameter configuration module configured to set the simulation start time, the simulation end time, and the preset simulation time interval of the satellite to be tested;

[0029] A calculation module, configured to perform calculations from the simulation start time to the simulation end time according to the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested, at each preset simulation time interval, to calculate the elevation angle of the satellite to be tested relative to the ground station to be tested and the trajectory position corresponding to the satellite to be tested;

[0030] A visible arc segment determination module, configured to perform operations to determine the starting point of the visible arc segment according to the trajectory position of the satellite to be tested when the first elevation angle is greater than the preset minimum transit angle, and determine the ending point of the visible arc segment according to the trajectory position of the satellite to be tested when the last elevation angle is greater than the preset minimum transit angle;

[0031] An interpolation operation module, configured to perform interpolation operations using the trajectory positions corresponding to the satellite to be tested at each preset simulation time interval between the starting point and the ending point to obtain interpolation points from the starting point to the ending point;

[0032] A simulated motion trajectory determination module, configured to perform operations to connect the starting point, the trajectory positions corresponding to the satellite to be tested at each preset simulation time interval between the starting point and the ending point, the interpolation points, and the ending point to obtain the simulated motion trajectory of the satellite to be tested.

[0033] On the other hand, an embodiment of this specification provides a computer-readable storage medium. When the instructions in the computer-readable storage medium are executed by a processor of a data processing device / electronic device for satellite visible arc segments, the data processing device / electronic device for satellite visible arc segments can execute the data processing method for satellite visible arc segments as described above.

[0034] On yet another hand, an embodiment of this specification provides a computer program product, including a computer program / instructions. When the computer program / instructions are executed by a processor, the data processing method for satellite visible arc segments as described above is implemented.

[0035] A data processing method, device, medium, and equipment for the visible arc segment of a satellite provided by an embodiment of this specification can perform simulation calculations on a satellite to be tested according to the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested. At each preset simulation time interval, the elevation angle of the satellite to be tested relative to the ground station to be tested is calculated, and the starting point and ending point at which the ground station to be tested can see the satellite to be tested are determined based on the elevation angle. By setting a relatively long preset simulation time interval, the amount of simulation calculation data can be greatly reduced. Then, interpolation operations are used to calculate the interpolation points corresponding to the trajectory positions of each satellite to be tested between the starting point and the ending point, so as to obtain the simulated motion trajectory of the satellite to be tested, which can avoid the low calculation efficiency caused by excessive simulation calculations within the arc segment. This application only needs to calculate a small number of points and use interpolation operations to calculate all the target points within the visible arc segment, reducing the number of simulation technologies that need to be collected, greatly reducing the simulation time, and accelerating the simulation efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 It is a schematic flowchart of the first data processing method for the visible arc segment of a satellite provided by an embodiment of this specification;

[0037] Figure 2 It is a schematic flowchart of the second data processing method for the visible arc segment of a satellite provided by an embodiment of this specification;

[0038] Figure 3 It is a schematic flowchart of the third data processing method for the visible arc segment of a satellite provided by an embodiment of this specification;

[0039] Figure 4 It is a schematic flowchart of the fourth data processing method for the visible arc segment of a satellite provided by an embodiment of this specification;

[0040] Figure 5 It is a schematic flowchart of the data processing process for the visible arc segment of a satellite in a scenario example of this specification;

[0041] Figure 6 It is a schematic diagram of the principle of the data processing method for the visible arc segment of a satellite in an embodiment of this specification;

[0042] Figure 7 It is a schematic diagram of a data processing device for the visible arc segment of a satellite provided by an embodiment of this specification;

[0043] Figure 8 It is a block diagram of an electronic device provided by an embodiment of this specification. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0044] To make the technical solutions and beneficial effects of the present invention more obvious and understandable, the following provides a detailed description by way of specific examples. Among them, the drawings are not necessarily drawn to scale, and local features can be enlarged or reduced to more clearly show the details of the local features; unless otherwise defined, the technical and scientific terms used herein have the same meanings as those in the technical and scientific fields to which this application belongs.

[0045] Please refer to Figure 1 , Figure 1 which is a schematic flowchart of the data processing method for the first satellite visible arc segment provided by the embodiments of this specification. As Figure 1 shown, the data processing method for the satellite visible arc segment provided by this application may include the following steps:

[0046] S102. Obtain the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested.

[0047] Specifically, the satellite orbit parameters of the satellite to be tested can simulate the movement trajectory of the satellite. The satellite orbit parameters may include parameters such as the position, running speed, running angle, and running attitude of the satellite. The position information of the ground station to be tested can search for GSO satellites or NGSO satellites with relatively close operating frequencies in the existing satellite network database according to the operating frequency of the satellite to be tested and the satellite transmission beam. Similarly, software simulation can be carried out according to the satellite orbit parameters and beam parameters to determine a ground station of the disturbed constellation, that is, the position information of the ground station to be tested is related to the satellite orbit parameters, satellite operating frequency, and satellite transmission beam of the satellite to be tested.

[0048] Among them, the satellite to be tested can be a satellite or a spacecraft, which can be a satellite or spacecraft to be used soon, or a satellite or spacecraft that has been put into use. The ground station to be tested can be a ground station that is already using a satellite or spacecraft.

[0049] S104. Set the simulation start time, simulation end time, and preset simulation time interval of the satellite to be tested.

[0050] In the specific implementation process, the user can define the simulation start time, simulation end time, and preset simulation time interval of the satellite to be tested according to actual needs. For example, the simulation start time is 9:00 am on April 1, 2022, and the simulation end time is 9:00 am on April 30, 2022. Among them, the preset simulation time interval can generally be set to a relatively long time step, such as 60 seconds or 100 seconds, etc., which can be set according to specific usage needs, and this embodiment of the specification does not make specific limitations. Compared with the target time interval of general simulation requirements, such as calculating once every 1 second, the calculation amount of calculating once every preset simulation time interval will be greatly reduced.

[0051] S106. From the simulation start time to the simulation end time according to the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested, calculate the elevation angle of the satellite to be tested relative to the ground station to be tested and the trajectory position corresponding to the satellite to be tested at each preset simulation time interval.

[0052] In the specific implementation process, after determining the position information of the ground station to be tested, the satellite to be tested can be simulated according to the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested. Calculate the elevation angle of the satellite to be tested relative to the ground station to be tested at each preset simulation time interval starting from the simulation start time until the simulation end time. Among them, the elevation angle of the satellite to be tested relative to the ground station to be tested can be understood as the azimuth angle of the satellite to be tested relative to the ground station to be tested.

[0053] S108. Determine the starting point of the visible arc segment according to the trajectory position of the satellite to be tested when the first elevation angle is greater than the preset minimum transit angle, and determine the ending point of the visible arc segment according to the trajectory position of the satellite to be tested when the last elevation angle is greater than the preset minimum transit angle.

[0054] Specifically, the preset minimum transit angle can be understood as the minimum angle at which the ground station to be tested can see the satellite to be tested; the preset minimum transit angle can be determined according to the satellite orbit parameters (such as: trajectory position and the position information of the ground station to be tested). Generally, the preset minimum transit angle is an elevation angle greater than 0 degrees. If the elevation angle of the satellite to be tested relative to the ground station to be tested is greater than this minimum transit angle, it can be stated that the satellite to be tested is within the visible range of the ground station to be tested, and it can also be called the satellite to be tested passing by.

[0055] In the embodiments of this specification, by comparing the calculated altitude angle with a preset minimum transit angle, the starting point and the ending point where the satellite to be tested appears within the visible range of the ground station to be tested are found. Each calculated point can be used as a sampling point, and the altitude angle corresponding to each sampling point is compared with the preset minimum transit angle. The starting point of the visible arc segment is determined based on the trajectory position of the satellite to be tested when the first altitude angle greater than the preset minimum transit angle is reached, and the ending point of the visible arc segment is determined based on the trajectory position of the satellite to be tested when the last altitude angle greater than the preset minimum transit angle is reached. A transit identifier can be marked at the starting point, and an outbound identifier can be marked at the ending point. Subsequently, the arc segment within the visible range of the ground station (i.e., the visible arc segment) can be quickly queried based on the identifiers.

[0056] In the process of judging the transit and outbound situations by calculating the altitude angle, if the judgment result of the current sampling point is transit and the previous sampling point has not transited yet, then the trajectory position of the current sampling point is considered to be the trajectory position of the satellite to be tested when the first altitude angle greater than the preset minimum transit angle is reached. Similarly, if the judgment result of the current sampling point is within the territory and the judgment result of the next sampling point is outbound, then the trajectory position of the current sampling point is considered to be the trajectory position of the satellite to be tested when the last altitude angle greater than the preset minimum transit angle is reached.

[0057] In the actual implementation process, considering that the starting point of the visible arc segment may be between the time of the current sampling point and the time of the previous sampling point, in order to obtain the accurate entry time, these two time points can be searched to determine the starting point of the visible arc segment. Similarly, considering that the ending point of the visible arc segment may be between these two points, the accurate ending point of the visible arc segment can be further searched out (this is generally searched according to the time interval set by the user, such as 1 second). At this time, it is considered that the search for a visible arc segment is completed, and 1 / 3 of the satellite orbit period is skipped, and the rough step search is continued. In other words, since a relatively long preset simulation time interval is set in this application, the sampling sparsity may not exactly encounter the starting point and the ending point of the visible arc segment. In an optional embodiment, to solve the above problem, in the algorithm, the two points before and after crossing this moment at a 60 - second step length (rough step length) are first found. For example: if the satellite enters the territory at 3 minutes and 15 seconds, however, since our sampling points are at 1 minute, 2 minutes, 3 minutes, and 4 minutes, the starting point of the visible arc segment is between the 3 - minute and 4 - minute time points. At this time, special processing will be performed between these two points at 3 minutes and 4 minutes, and the time point of 3 minutes and 15 seconds is accurately found through the search algorithm as the starting point. Similarly, the ending point is determined in a similar way. Therefore, for the arc segment result of the rough step sampling, the first point does not start from 3 minutes but from 3 minutes and 15 seconds. By accurately searching for the starting point and the ending point of the visible arc segment, the accurate time at the 1 - second level set by the user is obtained, preventing the phenomenon of missing points.

[0058] Generally, the elevation angle corresponding to the simulation start time is less than the preset minimum transit angle. However, if the elevation angle corresponding to the simulation start time is greater than the preset minimum transit angle, the simulation start time will be shifted backward by a specified simulation interval to re-determine the simulation start time.

[0059] In a specific implementation process, if the elevation angle corresponding to the simulation start time is greater than the preset minimum transit angle, it indicates that the satellite to be tested corresponding to the simulation start time is already within the visible range of the ground station to be tested. Then, the starting point of the visible arc segment of the satellite to be tested should have appeared before the simulation start time, and the simulation start time has missed the starting point of the visible arc segment. Based on this, the simulation start time can be advanced backward by a specified simulation interval, such as 100 seconds backward, to determine a new simulation start time, and the calculation of the visible arc segment starts from the new simulation start time. Among them, the specific value of the specified simulation interval can be set according to actual needs, and the embodiments of this specification do not make specific limitations. By re-determining the simulation start time, the initial position where the satellite to be tested appears at the ground station to be tested can be accurately queried, laying an accurate data foundation for the subsequent query of the visible arc segment.

[0060] In an alternative embodiment, the elevation angles corresponding to the starting point and the ending point can be equal or unequal. Additionally, the elevation angles corresponding to the points between the starting point and the ending point can first increase and then decrease, that is, gradually increase from the elevation angle corresponding to the starting point to the vertex, and then decrease from the vertex to the elevation angle corresponding to the ending point. Among them, the vertex is the highest elevation angle corresponding between the starting point and the ending point.

[0061] S110. Perform interpolation operations on the trajectory positions corresponding to the satellite to be tested for each preset simulation time interval between the starting point and the ending point to obtain interpolation points from the starting point to the ending point.

[0062] Specifically, the preset simulation time interval set in the embodiments of this specification is generally relatively large. The preset simulation time interval can be set to be greater than a specified time threshold, such as greater than 60 seconds. Therefore, the calculated sampling points are relatively sparse, and subsequent interpolation algorithms need to be used to expand all the required target points. In the embodiments of this specification, interpolation operations are performed using the trajectory positions corresponding to each preset simulation time interval between the starting point and the ending point for the satellite to be tested, and multiple interpolation points from the starting point to the ending point are obtained. For example, multiple interpolation points can be evenly inserted between the trajectory positions corresponding to each preset simulation time interval between the starting point and the ending point for the satellite to be tested, resulting in multiple interpolation points from the starting point to the ending point. The same number of interpolation points can be interpolated between the sampling points corresponding to each preset simulation time interval according to actual needs. To improve the calculation accuracy, more interpolation points can be inserted between each sampling point according to actual needs. The number of interpolation points can be set according to actual needs, and the embodiments of this specification do not make specific limitations.

[0063] S112. Connect the starting point, the trajectory positions corresponding to the satellite to be tested at each preset simulation time interval between the starting point and the ending point, the interpolation points, and the ending point to obtain the simulated motion trajectory of the satellite to be tested.

[0064] Specifically, after obtaining the interpolation points, the curve formed by the starting point, the trajectory positions at each preset simulation time interval, each interpolation point, and the ending point is denoted as the simulated motion trajectory of the satellite to be tested. It can be understood that each trajectory point of the satellite to be tested in the visible arc segment is within the visual range of the ground station. After determining the simulated motion trajectory, it is possible to analyze whether the satellite to be tested interferes with the ground station to be tested or the satellite corresponding to the ground station to be tested based on information such as the position, angle, speed, attitude, and signal emission frequency of the satellite to be tested corresponding to each trajectory point in the visible arc segment.

[0065] A data processing method for the visible arc segment of a satellite provided by an embodiment of this specification can perform simulation calculations on a satellite to be tested according to the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested. At each preset simulation time interval, the elevation angle of the satellite to be tested relative to the ground station to be tested is calculated, and based on the elevation angle, the starting point and the ending point at which the ground station to be tested can see the satellite to be tested are determined. By setting a relatively long preset simulation time interval, the amount of simulation calculation data can be greatly reduced. Then, interpolation operations are used to calculate the interpolation points corresponding to the trajectory positions of each satellite to be tested between the starting point and the ending point, so as to obtain the simulated motion trajectory of the satellite to be tested, which can avoid low calculation efficiency caused by excessive simulation calculations within the arc segment. This application only needs to calculate a small number of points and use interpolation operations to calculate all the target points within the visible arc segment, reducing the number of simulation technologies to be collected, greatly reducing the simulation time, and accelerating the simulation efficiency.

[0066] Based on the above embodiment, in one embodiment of this specification, Figure 2 is a schematic flowchart of the second data processing method for the visible arc segment of a satellite provided by an embodiment of this specification. As Figure 2 shown, the step of calculating the elevation angle of the satellite to be tested relative to the ground station to be tested at each preset simulation time interval from the simulation start time to the simulation end time according to the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested includes:

[0067] S202. After calculating the current elevation angle corresponding to the current simulation time interval point, compare the current elevation angle with the preset minimum transit angle. If the current elevation angle is less than the preset minimum transit angle, calculate the elevation angles corresponding to the two adjacent simulation time interval points of the current simulation time interval point.

[0068] S204. Compare the current elevation angle with the elevation angles of the two adjacent simulation time interval points of the current simulation time interval point. If the current elevation angle is greater than the elevation angles of the two adjacent simulation time interval points and the current elevation angle is less than the preset minimum transit angle, skip a specified length of arc segment, re-determine the simulation start time, and based on the re-determined simulation start time, start calculating the elevation angle of the satellite to be tested relative to the ground station to be tested at each preset simulation time interval again.

[0069] Specifically, when calculating the elevation angle of the satellite under test relative to the ground station under test at each preset simulation time interval, after calculating each elevation angle, the calculated elevation angle can be compared with the preset minimum transit angle. If the current elevation angle corresponding to the current simulation time interval point is less than the preset minimum transit angle, it indicates that the trajectory position of the satellite under test corresponding to the current simulation time interval point is not within the visible range of the ground station under test. At this time, embodiments of this specification can calculate the elevation angles corresponding to two adjacent simulation time interval points of the current simulation time interval point, that is, the elevation angles corresponding to the simulation time points that are one interval of the preset simulation time before or after the current simulation time interval point. Compare the magnitudes of these three elevation angles. If the middle elevation angle, that is, the current elevation angle, is greater than the other two elevation angles, it can be explained that the satellite under test has passed the zenith at the current simulation time interval point. However, even if the satellite under test has passed the zenith and its elevation angle is still less than the preset minimum transit angle, it means that the satellite under test is unlikely to appear within the visible range of the ground station under test in a long arc segment, so the visible arc segment will not appear near the current simulation time interval point. At this time, an arc segment of a specified length can be skipped, the simulation start time can be re-determined, and based on the re-determined simulation start time, the elevation angle of the satellite under test relative to the ground station under test can be recalculated at each preset simulation time interval to recalculate the visible arc segment.

[0070] Among them, passing the zenith can be understood as the elevation angle from the ground station looking at the satellite or spacecraft reaching the maximum value. Since the orbit of the satellite does not necessarily pass directly above the ground station, it is not necessarily 90 degrees. This angle is the limit value of the ground station facing the satellite in the current arc segment. However, due to the sparsity of the sampling points, it may not be exactly encountered. In embodiments of this specification, by continuously sampling three time points, if the satellite passes the zenith when approaching the second time point, then the elevation angle at the second time point will be larger than the angles at the first and third time points.

[0071] It can be understood that the three time points sampled in embodiments of this specification are the current simulation time interval point and two adjacent simulation time interval points, that is, the current simulation time interval point and the previous simulation time interval point and the next simulation time interval point that are one simulation time interval away from the current simulation time interval point. Then the current simulation time point is the middle time point. In actual use, the current simulation time interval point and its first two adjacent simulation time interval points, or the current simulation time interval point and its last two adjacent simulation time interval points can also be taken as three consecutive nodes, depending on the actual situation, and embodiments of this specification do not make specific limitations.

[0072] In addition, the specified arc segment can be preset and can be determined according to actual needs. For example, it can be set to half or 1 / 3 of the operating orbit of the satellite under test, or directly skip one circle of the operating trajectory of the satellite under test and start the simulation calculation from the next circle.

[0073] In the embodiments of this specification, considering the characteristics of the change in the elevation angle repeatedly, when it is determined that the current elevation angle is the over-zenith angle less than the preset minimum transit angle, it is judged whether the satellite to be tested passes over the top at the current time. If so, the trajectory positions of the satellites to be tested in the specified arc segment can be directly skipped, the simulation start time is re-determined, and the calculation of the visible arc segment is restarted. The arc segments that are basically impossible to appear within the visible range of the ground station to be tested are avoided, greatly reducing the simulation calculation amount, and thus improving the data processing efficiency.

[0074] Based on the above embodiments, in the embodiments of this specification, Figure 3 is a schematic flowchart of the data processing method for the third satellite visible arc segment provided by the embodiments of this specification. As Figure 3 shown, the method further includes:

[0075] S302. According to the simulation time corresponding to the termination point and the satellite orbit parameters, skip the simulation span period, determine the simulation start time of the next visible arc segment, and start calculating the next visible arc segment from the simulation start time of the next visible arc segment.

[0076] Specifically, the simulation span period is the time length of a specified multiple of the time for the satellite to be tested to orbit the celestial body where the ground station to be tested is located. It can be understood that the arc segments that do not need to be simulated can be skipped. For example, if the time for the satellite to be tested to orbit the celestial body where the ground station to be tested is located is T, the simulation span period can be half of T or one-third of T.

[0077] In practical applications, considering that the satellite only transits once per orbit, that is, generally, the satellite to be tested only appears within the visible range of the ground station to be tested once during one orbit, and the change in the satellite elevation angle is first increasing and then decreasing. The embodiments of this specification fully consider the characteristics of the elevation angle change. After determining a visible arc segment, the simulation span period can be directly skipped, the simulation start time is re-determined, and the visible arc segment of the next orbit of the satellite is searched for, realizing the rapid search of the visible arc segment and improving the data processing efficiency.

[0078] In an alternative embodiment, Figure 4 is a schematic flowchart of the data processing method for the fourth satellite visible arc segment provided by the embodiments of this specification. As Figure 4 shown, step S302, the determining the simulation start time of the next visible arc segment by skipping the simulation span period according to the simulation time corresponding to the termination point and the satellite orbit parameters, may include:

[0079] S3022. Determine the orbital period of the satellite to be tested according to the satellite orbit parameters.

[0080] Specifically, the satellite orbit parameters may further include the running speed of the satellite to be tested and the running trajectory of the satellite to be tested. Based on the running speed and the running trajectory of the satellite to be tested, the orbit period of the satellite to be tested can be determined. That is to say, the time for the satellite to be tested to run one week, namely the orbit period, can be calculated.

[0081] S3024. Calculate the simulation span period according to the orbit period and the simulation span ratio.

[0082] Specifically, the simulation span ratio can be determined according to actual needs or historical experience. In the embodiments of this specification, the simulation span ratio can be one-third of the orbit period, that is, the simulation span period is one-third of T.

[0083] S3026. Push the simulation time interval point corresponding to the simulation span period backward from the simulation time interval point corresponding to the termination point as the simulation start time of the next visible arc segment.

[0084] Specifically, in the embodiments of this specification, it is considered that the arc length of the satellite passing through the disturbed ground station each time is greater than 1 / 3 of the orbit period (one orbit period is considered to be a 360-degree rotation around the earth). When the search for an arc segment is completed, the search time point for the starting point of the next arc segment can be shifted backward by 1 / 3 of the orbit period. Generally, within 1 / 3 of the orbit period after the end of an arc segment, it is unlikely to be visible again. Skipping 1 / 3 of the orbit period can achieve a more efficient search. The simulation start time of the next visible arc segment can be calculated based on the sum of the simulation time corresponding to the termination point and the simulation span period. That is to say, the simulation start time point of the next visible arc segment is the sum of the simulation time corresponding to the termination point of the previous visible arc segment and one-third of the orbit period T. That is, t2 = t1 + T / 3. Wherein, t1 is the simulation time corresponding to the termination point of the previous visible arc segment, and t2 is the simulation start time point of the next visible arc segment.

[0085] By skipping the corresponding time interval in the way of the simulation span period and restarting to calculate the elevation angle of the satellite to be tested relative to the ground station to be tested every preset simulation period at the simulation start time point of the next visible arc segment, the interference of the invisible arc segment on the simulation calculation can be reduced, the simulation calculation data stream can be reduced, and the simulation calculation efficiency can be improved.

[0086] Figure 5 It is a schematic diagram of the satellite visible arc segment data processing flow in a scenario example of this specification, as Figure 5As shown, a simulation time range can be preset, and within the set time range, simulation calculations of visible arc segments are performed. The elevation angle of the satellite to be tested is calculated every preset simulation period. Based on the elevation angle, it is determined whether the satellite transits, that is, whether the satellite is within the visible range of the ground station to be tested. Specifically, the elevation angle can be compared with a preset minimum transit angle. The specific method can refer to the description of the above embodiments and will not be elaborated here. When the first transit time node is found, a transit identifier can be added, that is, it is marked that the satellite enters the visible range of the ground station, which can also be called the satellite entry identifier. After calculating the elevation angle subsequently, it can first be determined whether the satellite has a transit identifier. If it exists, it means that the satellite is within the visible range of the ground station to be tested, and then it continues to be determined whether the current node exits based on the elevation angle. If it exits, an exit identifier is set. If it does not exit, the calculation of the next time node continues. If the satellite at the current time node does not have a transit identifier, it means that the satellite has not yet appeared within the visible range of the ground station. It can be determined whether it is necessary to continue the calculation by judging whether the satellite passes over the top at the current time node. Specifically, it can be combined with Figure 5 and the processing process of passing over the top in the above embodiments, which will not be elaborated here.

[0087] Based on the above embodiments, in one embodiment of this specification, the interpolation operation using the trajectory positions of the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point to obtain interpolation points from the starting point to the ending point may include:

[0088] Performing an interpolation operation on the trajectory positions of the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point by using a cubic spline interpolation algorithm to obtain multiple interpolation points from the starting point to the ending point.

[0089] Specifically, cubic spline interpolation, abbreviated as Spline interpolation, is a smooth curve passing through a series of shape value points. Mathematically, it is a process of solving a system of three-moment equations to obtain a set of curve functions. This interpolation method is suitable for fitting curves and is relatively matched with the motion curve of the satellite. The following is the process of the cubic spline interpolation method.

[0090] First, extract the points of each arc segment to form a set {t i , pos i}, where t i refers to the time difference between the current point and the starting point, with the unit of seconds, and pos i is the coordinate information at the current moment (the coordinates of the trajectory position of the satellite to be tested).

[0091] Construct a cubic curve equation S i = a i x + b i x2 +c i x 3 +d i x 4 。

[0092] Among them, x can be understood as the time difference, and S i is the longitude coordinate. Since the first derivative of the internal points of the cubic equation should be continuous, therefore, for any interval {x i , x i+1}, where the end point of the i-th interval and the starting point of the i + 1-th interval are the same point, their first derivatives should also be equal, that is, S i '(x i+1 ) = S i+1 '(x i+1 ), and the internal second derivative also needs to be continuous, so S i ”(x i+1 ) = S i+1 ”(x i+1 ).

[0093] The above can obtain an equation as follows:

[0094]

[0095] Among them: h i = x i+1 -x i , m i = S i ”(x i+1 ) = 2c i

[0096] Using the equation described in the above embodiments, a curve can be constructed to simulate the satellite's motion trajectory, and then the satellite's position and time offset are input to simulate the satellite's motion trajectory. For example: input the satellite's longitude and the time difference from the starting point, (110.12, 0), (110.23, 60), (110.35, 120), (110.79, 180), (111.23, 240), (111.44, 300), etc. Through the input points, a system of equations can be listed to obtain each a i , b i , c i , d i . Next, if you want to obtain the longitude coordinate of a certain point within the arc segment, you only need to input the time offset from the starting point into the equation. For example, 15s, and you can immediately obtain the longitude value at this time point without going through complex calculations.

[0097] It can be understood that each visible arc segment is continuous and satisfies the curve characteristics. Therefore, for each arc segment, the common method is to simulate each time slice to be simulated. For example, calculate the spatial position of the satellite and the orientation angle relationship with the perturbed earth station every second. Due to the continuous curve characteristics of each arc segment, in the embodiments of this specification, only calculations need to be performed at a step size of 30 seconds or 60 seconds. After obtaining the spatial position and angle relationship every 60 seconds, through a curve interpolation algorithm for extension, the satellite position and angle information every 1 second can be obtained.

[0098] In the embodiments of this specification, through the method of cubic spline interpolation, operations are performed on each arc segment point in the arc segments of the simulation calculation, thereby reducing the calculation amount of the satellite simulation software. With the interpolation method, the arbitrary position information and angle information of the satellite to be tested corresponding to the corresponding step size can be directly calculated.

[0099] Figure 6 It is a schematic diagram of the principle of the data processing method for the satellite visible arc segment in an embodiment of this specification. As Figure 6 shown, the data processing method for the satellite visible arc segment provided in the embodiments of this specification can first, according to satellite network data, roughly query the visible arc segments of the satellite to be tested within the visible range of the ground station to be tested by setting a relatively large preset simulation time interval, and then perform interpolation calculations on the points within the arc segments to obtain accurate visible arc segments. It can avoid calculating too many points within the arc segments resulting in low calculation efficiency. Only a small number of points need to be calculated and all points within the curve are interpolated, and any fine time interval calculation can be performed. For traditional calculation methods, if the requirement for the time interval reaches within 1 second or even millisecond-level simulation, a large amount of computing resources and time resources will be consumed, and the review progress efficiency of satellite network data will be very low. After using the interpolation method, the simulation time can be greatly reduced and the simulation efficiency can be accelerated.

[0100] On the other hand, Figure 7 It is a schematic diagram of a data processing device for the satellite visible arc segment provided in the embodiments of this specification. As Figure 7 shown, the embodiments of this specification provide a data processing device for the satellite visible arc segment. The device includes:

[0101] An information acquisition module 701, configured to execute the acquisition of the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested;

[0102] A simulation parameter configuration module 702, configured to set the simulation start time, simulation end time, and preset simulation time interval of the satellite to be tested;

[0103] A calculation module 703, configured to perform calculations from the simulation start time to the simulation end time according to the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested, at each preset simulation time interval, to calculate the elevation angle of the satellite to be tested relative to the ground station to be tested and the trajectory position corresponding to the satellite to be tested;

[0104] A visible arc segment determination module 704, configured to perform operations to determine the starting point of the visible arc segment according to the trajectory position of the satellite to be tested when the first elevation angle is greater than the preset minimum transit angle, and determine the ending point of the visible arc segment according to the trajectory position of the satellite to be tested when the last elevation angle is greater than the preset minimum transit angle;

[0105] An interpolation operation module 705, configured to perform interpolation operations using the trajectory positions corresponding to the satellite to be tested at each preset simulation time interval between the starting point and the ending point to obtain interpolation points from the starting point to the ending point;

[0106] A simulated motion trajectory determination module 706, configured to perform operations to connect the starting point, the trajectory positions corresponding to the satellite to be tested at each preset simulation time interval between the starting point and the ending point, the interpolation points, and the ending point to obtain the simulated motion trajectory of the satellite to be tested.

[0107] The satellite visible arc segment data processing device provided in the embodiments of this specification has the same concept as the above-mentioned satellite visible arc segment data processing method, has the same technical features, and therefore also has the same technical effects, which will not be repeated here.

[0108] Figure 8 It is a block diagram of an electronic device provided in the embodiments of this specification. This electronic device may be a terminal, and its internal structure diagram may be as Figure 8 shown. This electronic device includes a processor, a memory, a network interface, a display screen, and an input device connected through a system bus. Among them, the processor of this electronic device is used to provide computing and control capabilities. The memory of this electronic device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of this electronic device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, it implements a method for processing satellite visible arc segments. The display screen of this electronic device may be a liquid crystal display screen or an electronic ink display screen. The input device of this electronic device may be a touch layer covering the display screen, or may be a button, a trackball, or a touchpad provided on the outer shell of the electronic device, or may also be an external keyboard, touchpad, or mouse, etc.

[0109] Those skilled in the art can understand that Figure 8 the structure shown in Figure 8 is only a block diagram of some structures related to the solution of the present disclosure, and does not constitute a limitation on the electronic device to which the solution of the present disclosure is applied. The specific electronic device may include more or fewer components than those shown in the figure, or combine some components, or have a different component arrangement.

[0110] In an exemplary embodiment, an electronic device is further provided, including: a processor; a memory for storing instructions executable by the processor; wherein, the processor is configured to execute the instructions to implement the data processing method of the satellite visible arc segment in the embodiments of the present disclosure.

[0111] In an exemplary embodiment, a computer-readable storage medium is further provided. When the instructions in the computer-readable storage medium are executed by the processor of the electronic device, the electronic device can execute the data processing method of the satellite visible arc segment in the embodiments of the present disclosure. The computer-readable storage medium may be a ROM, a random access memory (RAM), a CD-ROM, a magnetic tape, a floppy disk, an optical data storage device, etc.

[0112] In an exemplary embodiment, a computer program product containing instructions is further provided. When it runs on a computer, the computer is enabled to execute the method for data processing of the satellite visible arc segment in the embodiments of the present disclosure.

[0113] Those of ordinary skill in the art can understand that all or part of the processes in the methods of the above embodiments can be completed by instructing relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it may include the processes of the embodiments of the above methods. Among them, any reference to a memory, storage, database, or other medium used in the various embodiments provided in the present application may include non-volatile and / or volatile memories. The non-volatile memory may include a read-only memory (ROM), a programmable ROM (PROM), an electrically programmable ROM (EPROM), an electrically erasable programmable ROM (EEPROM), or a flash memory. The volatile memory may include a random access memory (RAM) or an external cache memory. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDR SDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0114] It should be understood that the above embodiments are all exemplary and are not used to cover all possible implementation manners included in the claims. Without departing from the scope of the present disclosure, various deformations and changes can also be made on the basis of the above embodiments. Similarly, various technical features of the above embodiments can also be arbitrarily combined to form other embodiments of the present invention that may not be clearly described. Therefore, the above embodiments only represent several implementation manners of the present invention and do not limit the protection scope of the present invention patent.

Claims

1. A method for processing satellite visible arc data, characterized in that, Including: Obtain the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested; Set the simulation start time, simulation end time and preset simulation time interval of the satellite to be tested; According to the satellite orbit parameters and the position information of the ground station to be tested, from the simulation start time to the simulation end time, calculate the elevation angle of the satellite to be tested relative to the ground station to be tested and the trajectory position corresponding to the satellite to be tested at each preset simulation time interval; the preset simulation time interval is greater than the specified time threshold; after calculating the current elevation angle corresponding to the current simulation time interval point, determine whether the current elevation angle is less than the preset minimum transit angle, if so, calculate the elevation angles corresponding to the two adjacent simulation time interval points of the current simulation time interval point; determine whether the current elevation angle is greater than the elevation angles of the two adjacent simulation time interval points of the current simulation time interval point, if so, skip the specified length arc segment, re-determine the simulation start time, and based on the re-determined simulation start time, recalculate the elevation angle of the satellite to be tested relative to the ground station to be tested at each preset simulation time interval, where the three sampled time points are three consecutive nodes; Determine the starting point of the visible arc segment according to the trajectory position of the satellite to be tested when the first elevation angle is greater than the preset minimum transit angle, and determine the ending point of the visible arc segment according to the trajectory position of the satellite to be tested when the last elevation angle is greater than the preset minimum transit angle; Perform interpolation operations using the trajectory positions corresponding to the satellite to be tested at each preset simulation time interval between the starting point and the ending point to obtain interpolation points from the starting point to the ending point; Connect the starting point, the trajectory positions corresponding to the satellite to be tested at each preset simulation time interval between the starting point and the ending point, the interpolation points and the ending point to obtain the simulated motion trajectory of the satellite to be tested.

2. The data processing method for the satellite visible arc segment according to claim 1, wherein, After determining the starting point and the ending point of the visible arc segment of the satellite to be tested, the method further includes: According to the simulation time corresponding to the ending point and the satellite orbit parameters, skip the simulation span period to determine the simulation start time of the next visible arc segment, and start calculating the next visible arc segment from the simulation start time of the next visible arc segment.

3. The data processing method for the satellite visible arc segment according to claim 2, characterized in that The step of according to the simulation time corresponding to the ending point and the satellite orbit parameters, skipping the simulation span period to determine the simulation start time of the next visible arc segment includes: Determine the orbital period of the satellite to be tested according to the satellite orbit parameters; Calculate the simulation span period according to the orbital period and the simulation span ratio; Push the simulation time interval point corresponding to the simulation span period backward from the simulation time interval point corresponding to the ending point as the simulation start time of the next visible arc segment.

4. The data processing method for the satellite visible arc segment according to claim 1, wherein The method further includes: If the elevation angle corresponding to the simulation start time is greater than the preset minimum transit angle, push the simulation start time backward by the specified simulation interval to re-determine the simulation start time.

5. The data processing method for the visible arc segment of a satellite according to claim 1, wherein The step of performing interpolation operations using the trajectory positions corresponding to the satellite to be tested at each preset simulation time interval between the starting point and the ending point to obtain interpolation points from the starting point to the ending point includes: Insert a plurality of interpolation points at equal intervals between the trajectory positions corresponding to the satellite under test at each preset simulation time interval between the starting point and the ending point, to obtain a plurality of interpolation points from the starting point to the ending point.

6. The data processing method for the visible arc segment of a satellite according to claim 1, wherein The interpolation operation using the trajectory positions corresponding to the satellite under test at each preset simulation time interval between the starting point and the ending point to obtain the interpolation points from the starting point to the ending point includes: Perform interpolation operation using the cubic spline interpolation algorithm to obtain a plurality of interpolation points from the starting point to the ending point.

7. A data processing device for a satellite visible arc segment, characterized in that, Includes: An information acquisition module, configured to execute the acquisition of the satellite orbit parameters of the satellite under test and the position information of the ground station under test; A simulation parameter configuration module, configured to set the simulation start time, simulation end time, and preset simulation time interval of the satellite under test; A calculation module, configured to execute the calculation of the elevation angle of the satellite under test relative to the ground station under test and the trajectory position corresponding to the satellite under test at each preset simulation time interval from the simulation start time to the simulation end time according to the satellite orbit parameters and the position information of the ground station under test; the preset simulation time interval is greater than the specified time threshold; after calculating the current elevation angle corresponding to the current simulation time interval point, determine whether the current elevation angle is less than the preset minimum transit angle, if so, calculate the elevation angles corresponding to the two adjacent simulation time interval points of the current simulation time interval point; determine whether the current elevation angle is greater than the elevation angles of the two adjacent simulation time interval points of the current simulation time interval point, if so, skip a specified length of arc segment, re-determine the simulation start time, and re-calculate the elevation angle of the satellite under test relative to the ground station under test at each preset simulation time interval based on the re-determined simulation start time, wherein the three time points sampled during the elevation angle calculation are three consecutive nodes; A visible arc segment determination module, configured to execute the determination of the starting point of the visible arc segment according to the trajectory position of the satellite under test when the first elevation angle is greater than the preset minimum transit angle, and determine the ending point of the visible arc segment according to the trajectory position of the satellite under test when the last elevation angle is greater than the preset minimum transit angle; An interpolation operation module, configured to execute the interpolation operation using the trajectory positions corresponding to the satellite under test at each preset simulation time interval between the starting point and the ending point to obtain the interpolation points from the starting point to the ending point; A simulated motion trajectory determination module, configured to execute the connection of the starting point, the trajectory positions corresponding to the satellite under test at each preset simulation time interval between the starting point and the ending point, the interpolation points, and the ending point to obtain the simulated motion trajectory of the satellite under test.

8. A computer-readable storage medium, characterized in that, When the instructions in the computer-readable storage medium are executed by the processor of the satellite visible arc segment data processing device / electronic device, the satellite visible arc segment data processing device / electronic device can execute the satellite visible arc segment data processing method according to any one of claims 1 to 6.

9. A computer program product, comprising a computer program / instructions, characterized in that, The computer program / instructions, when executed by the processor, implement the satellite visible arc segment data processing method according to any one of claims 1 to 6.

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