CN114757035A - Data processing method, device, medium and equipment for satellite visible arc - Google Patents

Abstract

The invention relates to a data processing method, a device, a medium and equipment of a satellite visible arc segment, wherein the method comprises the following steps: acquiring satellite orbit parameters and position information of a ground station to be tested; setting simulation starting time, simulation ending time and a preset simulation time interval; calculating the altitude angle and the track position at intervals of preset simulation time; determining a starting point of the visible arc segment and determining an end point of the visible arc segment; carrying out interpolation operation to obtain an interpolation point; and connecting the starting point, the track position corresponding to the satellite to be tested corresponding to each preset simulation time interval from the starting point to the ending point, the interpolation point and the ending point to obtain the simulated motion track of the satellite to be tested. The implementation of the invention can reduce the data quantity to be collected, reduce the simulation calculation time and improve the simulation efficiency.

Description

Data processing method, device, medium and equipment for satellite visible arc

technical field

The invention relates to the field of data processing, in particular to a data processing method, device, medium and equipment for a satellite visible arc segment.

Background technique

At present, 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 application data to ensure that the frequency, orbit and other resources used will not cause interference to existing satellites. Therefore, it is necessary to carry out software simulation on the operation data provided by the satellite filer. Through the satellite orbit parameters provided by the satellite operation data, the motion trajectories of all satellites can be simulated; through the satellite operating frequencies and satellite emission beams in the data, the satellite can be simulated. Signal transmission to the ground. 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 also according to their orbit parameters and beams. The parameters are simulated by software, and a ground station of the disturbed constellation is specified. By simulating for a period of time, such as one year, sliced simulation is performed according to the time interval of 1 second, and the constellation to be reviewed in each time slice is calculated. In the case of unwanted signal emission, it is determined whether there is interference with the limit specified by the International Telecommunication Union (ITU). For the simulation time of one year, the simulation time interval of one second, for the constellation with hundreds or even thousands of satellites, there will be a lot of calculations to calculate the position of each time slice, which requires large computing resources and waiting time. time.

SUMMARY OF THE INVENTION

The present application aims to solve the technical problems in the prior art that the calculation amount of satellite simulation data is too large, the calculation period is long, and the resource consumption in the calculation process is too much.

In order to solve the above technical problems, the embodiments of this specification provide a data processing method for a satellite visible arc segment, the method comprising:

Obtain the satellite orbit parameters of the satellite to be tested and the location 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 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 termination time, the satellite to be tested is calculated every preset simulation time interval The altitude angle relative to the ground station to be tested and the trajectory position corresponding to the satellite to be tested;

The starting point of the visible arc is determined according to the trajectory position of the satellite to be tested when the first altitude angle is greater than the preset minimum transit angle, and the starting point of the visible arc is determined according to the trajectory position of the satellite to be tested when the last altitude angle is greater than the preset minimum transit angle The end point of the visible arc segment;

Perform interpolation operation using the trajectory position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, to obtain an interpolation point from the starting point to the ending point;

connecting the starting point, the trajectory position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, the interpolation point and the ending point, Obtain the simulated motion trajectory of the satellite to be tested.

Further, 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 termination time, the calculation is performed at every preset simulation time interval. The altitude angle of the satellite to be tested relative to the ground station to be tested, including:

After calculating the current altitude angle corresponding to the current simulation time interval point, compare the size of the current altitude angle and the preset minimum transit angle, if the current altitude angle is smaller than the preset minimum transit angle, calculate the The altitude angle corresponding to the two adjacent simulation time interval points of the current simulation time interval point;

Compare the size of the altitude angle of the current altitude angle and the two adjacent simulation time interval points of the current simulation time interval point, if the current altitude angle is greater than the altitude angle of the two adjacent simulation time interval points, then skip A length arc segment is specified, the simulation start time is re-determined, and the altitude angle of the satellite to be tested relative to the ground station to be tested is recalculated every preset simulation time interval based on the re-determined simulation start time.

Further, after determining the starting point and the ending point of the visible arc of the satellite to be measured, the method further includes:

According to the simulation time corresponding to the termination point and the satellite orbit parameters, the simulation span period is skipped, the simulation start time of the next visible arc is determined, and the simulation start time of the next visible arc is started from the simulation start time of the next visible arc. The next visible arc segment is calculated.

Further, according to the simulation time corresponding to the termination point and the satellite orbit parameters, skip the simulation span period, and determine the simulation start time of the next visible arc segment, including:

Determine the orbital period of the satellite to be tested according to the satellite orbit parameters;

Calculate the simulation span period according to the orbit period and the simulation span ratio;

The simulation time interval point corresponding to the simulation span period is shifted backward from the simulation time interval point corresponding to the termination point, as the simulation start time of the next visible arc segment.

Further, the method also includes:

If the altitude angle corresponding to the simulation start time is greater than the preset minimum transit angle, the simulation start time is moved backward by a specified simulation interval, and the simulation start time is re-determined.

Further, the interpolation operation is performed using the trajectory position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, to obtain from the starting point to the ending point. interpolation points, including:

Insert multiple interpolation points at equal intervals between the trajectory positions corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, to obtain the starting point to the ending point Multiple interpolation points for points.

Further, the interpolation operation is performed using the trajectory position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, to obtain from the starting point to the ending point. interpolation points, including:

The cubic spline interpolation algorithm is used to perform the interpolation operation to obtain a plurality of interpolation points from the starting point to the ending point.

On the other hand, an embodiment of the present specification provides a data processing device for a visible arc segment of a satellite, the device comprising:

an information acquisition module, configured to perform acquisition of satellite orbit parameters of the satellite to be tested and location information of the ground station to be tested;

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

A calculation module, configured to execute the simulation start time to the simulation termination time according to the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested, every preset simulation time Calculate the altitude 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 intervals;

The visible arc segment determination module is configured to determine the starting point of the visible arc segment according to the trajectory position of the satellite to be tested when the first altitude angle is greater than the preset minimum transit angle, and according to the last altitude angle greater than the preset minimum transit angle When the trajectory position of the satellite to be tested determines the termination point of the visible arc segment;

An interpolation operation module, configured to perform interpolation operation using the trajectory position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, to obtain the distance from the starting point to the the interpolation point of the termination point;

The simulated motion trajectory determination module is configured to perform the process of determining the starting point, the trajectory position corresponding to the satellite under test corresponding to each preset simulation time interval between the starting point and the ending point, the The interpolation point and the termination point are connected to obtain the simulated motion trajectory of the satellite to be tested.

On the other hand, an embodiment of the present specification provides a computer-readable storage medium, when instructions in the computer-readable storage medium are executed by a processor of a data processing apparatus/electronic device in a satellite visible arc, the satellite is The data processing device/electronic device for the visible arc segment can execute the above-mentioned data processing method for the visible arc segment of the satellite.

In another aspect, the embodiments of the present specification provide a computer program product, including computer programs/instructions, when the computer programs/instructions are executed by a processor, the above-mentioned data processing method for a visible arc of a satellite is implemented.

The data processing method, device, medium and equipment for the visible arc segment of a satellite provided by the embodiments of this specification can perform simulation calculation on the satellite to be tested according to the obtained satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested, The altitude angle of the satellite to be tested relative to the ground station to be tested is calculated every preset simulation time interval, and the starting point and the ending point that the ground station to be tested can see the satellite to be tested is determined based on the altitude angle. By setting a longer preset simulation time interval, the amount of simulation calculation data can be greatly reduced, and then the interpolation point corresponding to the trajectory position of each satellite to be tested between the starting point and the end point is calculated by interpolation, so as to obtain the satellite to be tested. Simulating the motion trajectory can avoid too many simulation calculations in the arc segment, which leads to low calculation efficiency. The present application only needs to calculate a small number of points and use interpolation operation to calculate all the target points in the visible arc segment, reduce the number of simulation techniques to be collected, greatly reduce the simulation time, and speed up the simulation efficiency.

Description of drawings

1 is a schematic flowchart of a first method for processing data of a satellite visible arc segment provided by an embodiment of the present specification;

2 is a schematic flowchart of a data processing method for a second satellite visible arc segment provided by an embodiment of the present specification;

3 is a schematic flowchart of a third method for processing data of a satellite visible arc segment provided by an embodiment of the present specification;

4 is a schematic flowchart of a fourth method for processing data of a satellite visible arc segment provided by an embodiment of the present specification;

Fig. 5 is a schematic diagram of the processing flow of satellite visible arc segment data in a scene example of this specification;

Fig. 6 is the principle schematic diagram of the data processing method of the satellite visible arc segment in one embodiment of this specification;

7 is a schematic diagram of a data processing device for a satellite visible arc segment provided by an embodiment of the present specification;

FIG. 8 is a block diagram of an electronic device according to an embodiment of the present specification.

Detailed ways

In order to make the technical solutions and beneficial effects of the present invention more obvious and easy to understand, the following detailed description is given by way of specific embodiments. Wherein, the accompanying drawings are not necessarily drawn to scale, and local features may be enlarged or reduced to more clearly show the details of local features; unless otherwise defined, the technical and scientific terms used herein are related to the technical field to which this application belongs. The technical and scientific terms in the text have the same meaning.

Please refer to FIG. 1. FIG. 1 is a schematic flowchart of a first method for processing data of a visible arc of a satellite provided by an embodiment of this specification. As shown in FIG. 1, the method for processing data of a visible arc of a satellite provided by the present application, the The method can include the following steps:

S102. Acquire satellite orbit parameters of the satellite to be tested and location information of the ground station to be tested.

Specifically, the satellite orbit parameters of the satellite to be tested can simulate the motion trajectory of the satellite, and the satellite orbit parameters may include parameters such as the position, running speed, running angle, and running attitude of the satellite. The location information of the ground station to be tested can be based on the satellite operating frequency of the satellite to be tested and the satellite transmission beam, and a GSO satellite or NGSO satellite with a relatively close operating frequency is searched in the existing satellite network database as a possible disturbed object. Software simulation is performed according to the satellite orbit parameters and beam parameters to determine a ground station in the disturbed constellation, that is, the location information of the ground station to be tested is related to the satellite orbit parameters, satellite operating frequency and satellite emission beam of the satellite to be tested.

The satellite to be tested may be a satellite or a spacecraft, a satellite or a spacecraft to be used, or a satellite or a spacecraft that has been put into use. The ground station to be tested may be a ground station that is already using satellites or spacecraft.

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

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 use needs, and the embodiment of this specification does not specifically limit, compared to general simulation needs The target time interval of , such as 1 second simulation calculation, the calculation amount of every preset simulation time interval will be greatly reduced.

S106. Start the simulation end time from the simulation start time according to the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested, and calculate the to-be-tested time interval every preset simulation time interval. The altitude angle of the satellite relative to the ground station to be tested and the trajectory position corresponding to the satellite to be tested.

In a specific implementation process, after the location information of the ground station to be tested is determined, the satellite to be tested can be simulated according to the satellite orbit parameters of the satellite to be tested and the location information of the ground station to be tested. The altitude angle of the satellite to be tested relative to the ground station to be tested is calculated at every preset simulation time interval from the start time of the simulation until the end time of the simulation. The altitude 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.

S108. Determine the starting point of the visible arc segment according to the trajectory position of the satellite to be tested when the first altitude angle is greater than the preset minimum transit angle, and the trajectory of the satellite to be tested when the last altitude angle is greater than the preset minimum transit angle The position determines the end point of the visible arc segment.

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 based on satellite orbit parameters (such as trajectory position and position information of the ground station to be tested) It is determined that, generally, the preset minimum transit angle is an altitude angle greater than 0 degrees. If the altitude angle of the satellite to be tested relative to the ground station to be tested is greater than the minimum transit angle, it can indicate that the satellite to be tested is within the visible range of the ground station to be tested, which can also be referred to as the transit of the satellite to be tested.

In the embodiment of this specification, by comparing the calculated altitude angle with the preset minimum transit angle, the starting point and the ending point of the satellite to be tested appearing in the visible range of the ground station to be tested are found. You can use each calculation point as a sampling point, compare the height angle corresponding to each sampling point and the preset minimum transit angle, and determine the visible arc segment according to the trajectory position of the satellite to be tested when the first one is greater than the preset minimum transit angle. Starting point, the end point of the visible arc is determined according to the trajectory position of the satellite to be tested when the last one is greater than the preset minimum transit angle. A transit sign can be marked at the starting point, and an exit sign can be marked at the end point, and then the arcs (that is, visible arcs) within the visible range of the ground station can be quickly queried based on the signs.

In the process of judging the transit and exit situations by calculating the altitude angle, if the judgment result of the current sampling point is transit, but the last sampling point has not passed the border, it is considered that the trajectory position of the current sampling point is the first one greater than the preset minimum The trajectory position of the satellite to be tested at the transit angle. In the same way, if the judgment result of the current sampling point is within the territory, and the judgment result of the next sampling point is outbound, it is considered that the trajectory position of the current sampling point is the trajectory position of the satellite to be tested when the last one is greater than the preset minimum transit angle. .

In the actual implementation process, considering that the starting point of the visible arc may be located in the middle of the time of the current sampling point and the time of the last 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 end point of the visible arc segment may be located between these two points, it is possible to further search for the precise end point of the visible arc segment (this is generally searched according to the time interval set by the user, such as 1 second) , at this time, it is considered that a visible arc search is over, skip 1/3 of the satellite orbit period, and continue the coarse step search. In other words, since the present application sets a long preset simulation time interval, the sampling sparsity may not necessarily hit the start point and the end point of the visible arc segment exactly. In an optional embodiment, in order to solve the above problem, the algorithm will first find two points before and after the moment with a step size of 60 seconds (coarse step size). , the satellite enters. However, since our sampling points are at the time points of 1, 2, 3, and 4, it can be seen that the starting point of the arc is between the time points of 3 and 4. At this time, it will be 3 minutes. Special processing is performed between the two points of 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 termination point is also determined by a similar method. Therefore, in the arc segment result of the last coarse step sampling, the first point does not start from 3 minutes, but from 3 minutes and 15 seconds. The precise time of 1 second is set to prevent the phenomenon of leakage.

Generally, the altitude angle corresponding to the simulation start time is smaller than the preset minimum transit angle, but if the altitude angle corresponding to the simulation start time is greater than the preset minimum transit angle, the simulation start time Move the specified simulation interval backward to re-determine the simulation start time.

In the specific implementation process, if the altitude angle corresponding to the simulation start time is greater than the preset minimum transit angle, it means 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 satellite to be tested is within the visual range of the ground station to be tested. The starting point of the visible arc should come before the simulation start time, which has missed the starting point of the visible arc. Based on this, the simulation start time can be pushed back by a specified simulation interval, for example, by 100 seconds, a new simulation start time can be determined, and the visible arcs can be calculated from the new simulation start time. The specific value of the specified simulation interval may be set according to actual needs, which is not specifically limited in the embodiment of this specification. By re-determining the simulation start time, the initial position of the satellite to be tested appearing on the ground station to be tested can be accurately queried, which lays an accurate data foundation for the subsequent query of visible arcs.

In an optional embodiment, the height angles corresponding to the start point and the end point may be equal or unequal. In addition, the height angle corresponding to the point between the starting point and the ending point may first rise and then decrease, that is, gradually rise from the height angle corresponding to the starting point to the passing vertex, and then decrease from the passing fixed point to the height angle corresponding to the ending point. Among them, the passing vertex is the highest height angle corresponding to the starting point and the ending point.

S110. Perform an interpolation operation on the trajectory position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, to obtain an interpolation point from the starting point to the ending point .

Specifically, the preset simulation time interval set in the embodiments of this specification is generally relatively large, and the preset simulation time interval can be set to be greater than the specified time threshold, for example, greater than 60 seconds. Therefore, the calculated sampling points are relatively sparse, and subsequent steps are required. The interpolation algorithm expands out all desired target points. The embodiment of the present specification obtains multiple interpolation points from the starting point to the ending point by performing interpolation operation using the trajectory position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point. For example, multiple interpolation points can be inserted at equal intervals between the trajectory positions corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, to obtain 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. In order to improve the calculation accuracy, more interpolation points can be inserted between each sampling point according to actual needs. The quantity can be set according to actual needs, which is not specifically limited in the embodiment of this specification.

S112. Set the starting point, the trajectory position corresponding to the satellite to be tested, the interpolation point and the ending point corresponding to each preset simulation time interval between the starting point and the ending point Connect to obtain the simulated motion trajectory of the satellite to be tested.

Specifically, after the interpolation point is obtained, the curve composed of the starting point, the trajectory position of each preset simulation time interval, each interpolation point and the ending point is recorded as the simulated motion trajectory of the satellite to be tested. Each trajectory point in the visible arc is within the visible range of the ground station. After the simulated motion trajectory is determined, it can be analyzed whether the satellite to be tested is to be tested by the ground station or to be tested according to the position, angle, speed, attitude, signal transmission frequency and other information of the satellite to be tested corresponding to each trajectory point in the visible arc. Check whether the satellite corresponding to the ground station has interference problems.

A data processing method for a visible arc segment of a satellite provided by the embodiment of this specification can perform simulation calculation on the satellite to be tested according to the acquired satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested, and the simulation calculation is performed every preset simulation time. The altitude angle of the satellite to be tested relative to the ground station to be tested is calculated at intervals, and the starting point and the ending point that the ground station to be tested can see the satellite to be tested is determined based on the altitude angle. By setting a longer preset simulation time interval, the amount of simulation calculation data can be greatly reduced, and then the interpolation point corresponding to the trajectory position of each satellite to be tested between the starting point and the end point is calculated by interpolation, so as to obtain the satellite to be tested. Simulating the motion trajectory can avoid calculating too many simulation calculations in the arc segment, which leads to low calculation efficiency. The present application only needs to calculate a small number of points and use interpolation operation to calculate all the target points in the visible arc segment, reduce the number of simulation techniques to be collected, greatly reduce the simulation time, and speed up the simulation efficiency.

On the basis of the above-mentioned embodiment, in an embodiment of the present specification, FIG. 2 is a schematic flowchart of a second data processing method for satellite visible arc segments provided by the embodiment of the present specification, as shown in FIG. 2 . The satellite orbit parameters of the test satellite and the position information of the ground station to be tested start from the simulation start time to the simulation end time, and the relative value of the satellite to be tested relative to the to-be-tested satellite is calculated every preset simulation time interval. Test the altitude angle of the ground station, including:

S202. After calculating the current altitude angle corresponding to the current simulation time interval point, compare the size of the current altitude angle and the preset minimum transit angle, if the current altitude angle is smaller than the preset minimum transit angle, then Calculate the altitude angles corresponding to two adjacent simulation time intervals of the current simulation time interval.

S204, compare the current altitude angle and the size of the altitude angles of two adjacent simulation time interval points, if the current altitude angle is greater than the altitude angles of the two adjacent simulation time interval points and all The current altitude angle is less than the preset minimum transit angle, skip the specified length arc, re-determine the simulation start time, and start recalculating the simulation start time every preset simulation time interval based on the re-determined simulation start time. The altitude angle of the satellite to be tested relative to the ground station to be tested.

Specifically, when calculating the altitude angle of the satellite to be tested relative to the ground station to be tested at every preset simulation time interval, each time an altitude angle is calculated, the calculated altitude angle can be compared with the preset minimum transit angle, If the current altitude angle corresponding to the current simulation time interval point is smaller than the preset minimum transit angle, it means that the trajectory position corresponding to the satellite to be tested corresponding to the current simulation time interval point is not within the visible range of the ground station to be tested. At this time, the embodiment of the present specification can calculate the altitude angles corresponding to two adjacent simulation time intervals of the current simulation time interval, that is, the corresponding simulation time points of one preset simulation time interval before or after the current simulation time interval height angle. Comparing the magnitudes of these three altitude angles, if the middle one, that is, the current altitude angle, is greater than the other two altitude angles, it means that the satellite to be tested has passed the top at the current simulation time interval. However, even if the satellite to be tested has passed the top and its altitude angle is still smaller than the preset minimum transit angle, it is impossible for the satellite to be tested to appear within the visible range of the ground station to be tested within a long arc. Segments do not appear near the current simulation time interval point. At this time, the arc of the specified length can be skipped, the simulation start time can be re-determined, and the altitude angle of the satellite to be tested relative to the ground station to be tested can be recalculated every preset simulation time interval based on the re-determined simulation start time, so as to Recalculate visible arcs.

Among them, over-the-top can be understood as the height angle of the ground station looking at the satellite or the 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 current arc segment. The limit value of the ground station facing the satellite, but due to the sparseness of the sampling points, it may not be exactly met. In the embodiment of this specification, three time points are continuously sampled. If the satellite passes over the top when it is close to the second time point, then The altitude angle of the second time point will be larger than the angle of the first and third time points.

It can be understood that the three time points sampled in the embodiment 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 current simulation time interval point are separated by one simulation time interval. The previous simulation time interval point and the next simulation time interval point, then the current simulation time point is the middle time point. In actual use, the current simulation time interval and its first two simulation time intervals, or the current simulation time interval and its next two simulation time intervals can also be taken as three consecutive nodes, depending on the actual situation. Certainly, the embodiments of this specification are not specifically limited.

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 orbit of the satellite to be tested, or directly skip the orbit of the satellite to be tested. The next lap starts the simulation calculation.

The embodiment of this specification repeatedly considers the characteristics of the altitude angle change, and when it is determined that the current altitude angle is less than the preset minimum transit angle, it is determined whether the satellite to be tested is over the top at the current time, and if so, the designated arc can be skipped directly. The trajectory position of the satellite to be tested in the segment is determined, the simulation start time is re-determined, and the calculation of the visible arc segment is restarted. The arcs that are basically impossible to appear in the visible range of the ground station to be tested are avoided, which greatly reduces the amount of simulation calculations, thereby improving the efficiency of data processing.

On the basis of the above embodiment, in the embodiment of this specification, FIG. 3 is a schematic flowchart of a third method for processing data of satellite visible arc segments provided in the embodiment of this specification. As shown in FIG. 3 , the method further includes:

S302, according to the simulation time corresponding to the termination point and the satellite orbit parameters, skip the simulation span period, and determine the simulation start time of the next visible arc segment, from the simulation start time of the next visible arc segment Begins calculation of the next visible arc.

Specifically, the simulation span period is the length of time that the satellite to be tested revolves around the star where the ground station to be tested is located, which is a specified multiple. The time of the star running for one week is T, and the simulation span period can be half of T or one-third of T.

In practical applications, considering that each lap satellite will only transit once, that is, the general satellite to be tested only appears within the visible range of the ground station to be tested once a week, and the change of the satellite altitude angle is to increase first and then change Small trend, the embodiment of this specification fully considers the characteristics of the change of the altitude angle. After a visible arc is determined, the simulation span period can be directly crossed, the simulation start time can be re-determined, and the visible arc of the next circle of satellites can be found to realize the visible arc. Fast search of arc segments to improve data processing efficiency.

In an optional embodiment, FIG. 4 is a schematic flowchart of a fourth method for processing data of satellite visible arc segments provided by the embodiment of the present specification. As shown in FIG. 4 , in step S302, the corresponding The simulation time and the satellite orbit parameters, skip the simulation span period, and determine the simulation start time of the next visible arc segment, which can include:

S3022. Determine the orbit period of the satellite to be tested according to the satellite orbit parameter.

Specifically, the satellite orbit parameters may also include the running speed of the satellite to be tested and the running track of the satellite to be tested, and the orbital period of the satellite to be tested can be determined based on the running speed of the satellite to be tested and the running track of the satellite to be tested, and That is to say, the orbit period is calculated as the time for the satellite to be tested to run for one week.

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

Specifically, the simulation span ratio may be determined according to actual needs or historical experience, and the simulation span ratio in the embodiment of this specification may be one-third of the orbit period, that is, the simulation span period is one-third of T.

S3026. Move 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.

Specifically, the embodiment of this specification considers that the length of the arc segment of the satellite passing through the disturbed ground station each time is greater than 1/3 of the orbital period (one orbital period is considered to rotate 360 degrees around the earth). , we can move back 1/3 orbital circle for the starting point of the next arc. Generally, it is unlikely to be visible again within 1/3 of the orbital period after the end of an arc, and skipping 1/3 of the orbital period can achieve a more efficient search. The simulation start time of the next visible arc can be calculated according to the sum of the simulation time corresponding to the end point and the simulation span period, that is, the simulation start time of the next visible arc is the previous visible arc. The sum of the simulation time corresponding to the end point of the segment and one third of the orbital period T. That is, t2=t1+T/3. Among them, t1 is the simulation time corresponding to the end point of the previous visible arc segment, and t2 is the simulation start time point of the next visible arc segment.

The corresponding time interval is skipped by means of the simulation span period, and the calculation of the altitude angle of the satellite to be tested relative to the ground station to be tested is restarted every preset simulation period at the simulation start time point of the next visible arc segment, The interference of invisible arcs to simulation calculation can be reduced, the data flow of simulation calculation can be reduced, and the efficiency of simulation calculation can be improved.

Fig. 5 is a schematic diagram of the data processing flow of the satellite visible arc segment in a scene example of this specification. As shown in Fig. 5, a simulation time range can be preset, and the simulation calculation of the visible arc segment is performed within the set time range. The altitude angle of the satellite to be tested is calculated in the simulation cycle, and based on the altitude angle, it is judged whether the satellite is transiting, that is, whether the satellite is within the visible range of the ground station to be tested. Specifically, the altitude angle can be compared with the preset minimum transit angle. For details, see The descriptions of the above embodiments are not repeated here. When the first transit time node is found, a transit sign can be added, which means that the satellite enters the visible range of the ground station. , if it exists, it means that the satellite is within the visible range of the ground station to be tested, and continues to judge whether the current node is out of the country based on the altitude angle. If the satellite at the current time node does not have a transit sign, it means that the satellite has not yet appeared within the visible range of the ground station. You can judge whether it is necessary to continue the calculation by judging whether the satellite at the current time node is over the top. For example, the processing process of over-the-top will not be repeated here.

On the basis of the above embodiment, in an embodiment of this specification, the interpolation operation is performed by using the trajectory position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, Obtaining the interpolation point from the starting point to the ending point may include:

The cubic spline interpolation algorithm is used to interpolate the trajectory position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, and obtain the distance from the starting point to the ending point. Multiple interpolation points for points.

Specifically, cubic spline interpolation is referred to as Spline interpolation, which is a process of mathematically obtaining a curve function group by solving a three-bending moment equation group through a smooth curve of a series of shape-value points. This interpolation method is suitable for fitting the curve, which is more suitable for the motion curve of the satellite. The following is the process of the cubic spline interpolation method.

First, the points of each arc segment are extracted to form a set {t _i , pos _i }, where t _i refers to the time difference between the current point and the starting point, in seconds, and pos _i is the coordinate information of the current moment (to be coordinates of the trajectory position of the test satellite).

Construct a cubic curve equation S _i =a _i x+b _i x ² + _ci x ³ +d _i x ⁴ .

Among them, x can be understood as the time difference, and S _i is the longitude coordinate. Since the first derivative of the internal point of the cubic equation should be continuous, it can be obtained for any interval {x _i , x _i+1 }, where, in the first The end point of the i interval and the start point of the i+1th interval are the same point, and their first derivatives should also be equal, that is, S _i '(x _i+1 )=S _i+1 '(x _i+1 ), and the inner second derivative also needs to be continuous, there is S _i ″(x _i+1 )=S _i+1 ″(x _i+1 ).

The above results in an equation as follows:

Wherein: h _i =x _{i +1} -xi , m _i =S _i "(x _i+1 )=2c _i

Using the equations described in the above embodiments, a curve can be constructed to simulate the motion trajectory of the satellite, and then the position and time offset of the satellite are input to simulate the motion trajectory of the satellite. For example: enter the longitude of the satellite 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. . A system of equations can be listed through the input points, and each a _i , b _i , c _i , d _i can be obtained. Next, if you want to get the longitude coordinates of a point in the arc segment, you only need to offset the time offset from the starting point. Enter the shift amount into the equation, such as 15s, and you can get the longitude value of the time point immediately, without the need for complicated calculations.

It can be understood that each visible arc segment is continuous and satisfies the curve characteristics, so for each arc segment, the usual method is to simulate each time slice that needs to be simulated, such as calculating the satellite's Spatial position and angular relationship with respect to the disturbed earth station. Due to the continuous curve characteristics of each arc segment, the embodiment of this specification only needs to perform calculations in steps of 30 seconds or 60 seconds, and after obtaining the spatial position and angular relationship of every 60 seconds, it can be extended through the curve interpolation algorithm. Get satellite position and angle information every 1 second.

In the embodiment of this specification, the cubic spline interpolation method is used to perform operations on each arc segment point in the arc segment calculated by the simulation, thereby reducing the calculation amount of the satellite simulation software, and the interpolation method can directly calculate the corresponding step size to be tested. Satellite arbitrary position information and angle information.

FIG. 6 is a schematic diagram of the principle of a data processing method for a satellite visible arc segment in an embodiment of the present specification. As shown in FIG. 6 , the data processing method for a satellite visible arc segment provided by an embodiment of the present specification can be based on satellite network data. Set a relatively large preset simulation time interval, roughly query the visible arcs of the satellite to be tested within the visible range of the ground station to be tested, and then perform interpolation calculations on the points in the arcs to obtain accurate visible arcs. It can avoid calculating too many points in the arc segment, which leads to low calculation efficiency. It only needs to calculate a small number of points and interpolate all the points in the curve, and any fine time interval calculation can be performed. It requires a large amount of computing resources and time resources to achieve simulation within 1 second, or even at the millisecond level, and the review progress of satellite network data will be very inefficient. After using the interpolation method, the simulation time can be greatly reduced and the simulation efficiency can be accelerated.

On the other hand, FIG. 7 is a schematic diagram of a data processing apparatus for a satellite visible arc section provided by an embodiment of the present specification. As shown in FIG. 7 , an embodiment of the present specification provides a data processing apparatus for a satellite visible arc section. The device includes:

The information acquisition module 701 is configured to perform acquisition of satellite orbit parameters of the satellite to be tested and position information of the ground station to be tested;

The simulation parameter configuration module 702 is configured to set the simulation start time, simulation end time and preset simulation time interval of the satellite to be tested;

The calculation module 703 is configured to execute the simulation start time 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, every preset simulation time. The time interval calculates the altitude 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;

The visible arc segment determination module 704 is configured to determine the starting point of the visible arc segment according to the trajectory position of the satellite to be tested when the first altitude angle is greater than the preset minimum transit angle, and according to the last altitude angle greater than the preset minimum transit angle The trajectory position of the satellite to be tested determines the termination point of the visible arc segment at the time of angle;

The interpolation operation module 705 is configured to perform an interpolation operation using the trajectory position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, and obtain the distance from the starting point to the the interpolation point of the termination point;

The simulated motion trajectory determination module 706 is configured to perform the process of determining the starting point, the trajectory position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, The interpolation point and the termination point are connected to obtain the simulated motion trajectory of the satellite to be tested.

The data processing device for satellite visible arcs provided by the embodiments of this specification has the same concept as the above-mentioned data processing method for satellite visible arcs, has the same technical features, and therefore also has the same technical effects, which will not be described here.

FIG. 8 is a block diagram of an electronic device according to an embodiment of the present specification. The electronic device may be a terminal, and its internal structure diagram may be as shown in FIG. 8 . The electronic device includes a processor, a memory, a network interface, a display screen, and an input device connected by a system bus. Among them, the processor of the electronic device is used to provide computing and control capabilities. The memory of the electronic device includes a non-volatile storage medium and an internal memory. The nonvolatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the execution of the operating system and computer programs in the non-volatile storage medium. The network interface of the electronic device is used to communicate with an external terminal through a network connection. The computer program, when executed by a processor, implements a method for data processing of satellite visible arcs. The display screen of the electronic device may be a liquid crystal display screen or an electronic ink display screen, and the input device of the electronic device may be a touch layer covered on the display screen, or a button, a trackball or a touchpad set on the shell of the electronic device , or an external keyboard, trackpad, or mouse.

Those skilled in the art can understand that the structure shown in FIG. 8 is only a block diagram of a partial structure 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 be Include more or fewer components than shown in the figures, or combine certain components, or have a different arrangement of components.

In an exemplary embodiment, there is also provided an electronic device, comprising: a processor; a memory for storing instructions executable by the processor; wherein the processor is configured to execute the instructions to implement the present disclosure The data processing method of the visible arc segment of the satellite in the example.

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

In an exemplary embodiment, there is also provided a computer program product comprising instructions which, when executed on a computer, cause the computer to perform the method of data processing of a satellite visible arc in an embodiment of the present disclosure.

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 implemented by instructing relevant hardware through a computer program, and 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 above-mentioned method embodiments. Wherein, any reference to memory, storage, database or other medium used in the various embodiments provided in this application may include non-volatile and/or volatile memory. Nonvolatile memory may include read only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memory may include random access memory (RAM) or 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 (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous chain Road (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

It should be understood that the above embodiments are all exemplary and are not intended to include all possible implementations contained in the claims. Various modifications and changes may also be made on the basis of the above embodiments without departing from the scope of the present disclosure. Likewise, various technical features of the above embodiments can also be arbitrarily combined to form additional embodiments of the present invention that may not be explicitly described. Therefore, the above-mentioned embodiments only represent several embodiments of the present invention, and do not limit the protection scope of the patent of the present invention.

Claims (10)

1. A method for processing data of a satellite visible arc segment, the method comprising:

acquiring satellite orbit parameters of a satellite to be tested and position information of a ground station to be tested;

setting simulation starting time, simulation ending time and a preset simulation time interval of the satellite to be tested;

calculating the altitude angle of the satellite to be tested relative to the ground station to be tested and the track position corresponding to the satellite to be tested at intervals of preset simulation time from the simulation starting time to the simulation ending time according to the satellite orbit parameters of the satellite to be tested and the position information of the ground station to be tested;

determining a starting point of a visible arc section according to the track position of the satellite to be tested when the first altitude angle is larger than a preset lowest transit angle, and determining a termination point of the visible arc section according to the track position of the satellite to be tested when the last altitude angle is larger than the preset lowest transit angle;

performing interpolation operation by using the track position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point to obtain an interpolation point from the starting point to the ending point;

and connecting the starting point, the track position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, the interpolation point and the ending point to obtain the simulated motion track of the satellite to be tested.

2. The method for processing data of a satellite visible arc segment according to claim 1, wherein the calculating the altitude angle of the satellite to be tested relative to the ground station to be tested at intervals of the preset simulation time interval 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 comprises:

after calculating a current altitude angle corresponding to a current simulation time interval point, comparing the current altitude angle with the preset lowest transit angle, and if the current altitude angle is smaller than the preset lowest transit angle, calculating altitude angles corresponding to two simulation time interval points adjacent to the current simulation time interval point;

and comparing the current altitude angle with the altitude angles of two adjacent simulation time interval points of the current simulation time interval point, if the current altitude angle is greater than the altitude angles of the two adjacent simulation time interval points, skipping an arc section with a specified length, re-determining the simulation starting time, and re-calculating the altitude angle of the satellite to be tested relative to the ground station to be tested at the preset simulation time interval based on the re-determined simulation starting time.

3. The method for processing data of a satellite visible arc segment according to claim 1 or 2, wherein after determining the starting point and the ending point of the visible arc segment of the satellite to be measured, the method further comprises:

and skipping a simulation span period according to the simulation time corresponding to the termination point and the satellite orbit parameters, determining the simulation starting time of the next visible arc segment, and calculating the next visible arc segment from the simulation starting time of the next visible arc segment.

4. The data processing method of the satellite visible arc segments according to claim 3, wherein the step of skipping a simulation span cycle according to the simulation time corresponding to the termination point and the satellite orbit parameters to determine the simulation start time of the next visible arc segment comprises:

determining the orbit period of the satellite to be tested according to the satellite orbit parameters;

calculating the simulation span period according to the track period and the simulation span proportion;

and pushing the simulation time interval point corresponding to the simulation span period backwards from the simulation time interval point corresponding to the termination point to serve as the simulation starting time of the next visible arc segment.

5. The method of claim 1, further comprising:

and if the altitude angle corresponding to the simulation starting time is larger than the preset lowest transit angle, the simulation starting time is pushed backwards by a specified simulation interval, and the simulation starting time is determined again.

6. The method for processing data of a satellite visible arc segment according to claim 1, wherein the step of performing interpolation operation by using the track position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point to obtain an interpolation point from the starting point to the ending point comprises:

and inserting a plurality of interpolation points at equal intervals between the track positions corresponding to the satellites to be tested and corresponding to each preset simulation time interval between the starting point and the ending point to obtain a plurality of interpolation points between the starting point and the ending point.

7. The method for processing data of a satellite visible arc segment according to claim 1, wherein the obtaining of the interpolation point from the starting point to the ending point by performing interpolation operation using the track position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point comprises:

and carrying out interpolation operation by adopting a cubic spline interpolation algorithm to obtain a plurality of interpolation points from the starting point to the ending point.

8. A data processing apparatus for a satellite visible arc segment, the apparatus comprising:

the information acquisition module is configured to acquire satellite orbit parameters of a satellite to be tested and position information of a ground station to be tested;

the simulation parameter configuration module is configured to set a simulation starting time, a simulation ending time and a preset simulation time interval of the satellite to be tested;

the calculation module is configured to calculate the altitude angle of the satellite to be tested relative to the ground station to be tested and the track position corresponding to the satellite to be tested at intervals of preset simulation time according to the satellite orbit parameter of the satellite to be tested and the position information of the ground station to be tested from the simulation starting time to the simulation ending time;

the visible arc section determining module is configured to determine a starting point of a visible arc section according to the track position of the satellite to be tested when the first altitude angle is larger than a preset lowest transit angle, and determine a termination point of the visible arc section according to the track position of the satellite to be tested when the last altitude angle is larger than the preset lowest transit angle;

the interpolation operation module is configured to perform interpolation operation by using the track position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point to obtain an interpolation point from the starting point to the ending point;

and the simulated motion track determining module is configured to execute connecting the starting point, the track position corresponding to the satellite to be tested corresponding to each preset simulation time interval between the starting point and the ending point, the interpolation point and the ending point to obtain a simulated motion track of the satellite to be tested.

9. A computer readable storage medium, wherein instructions in the computer readable storage medium, when executed by a processor of a data processing apparatus/electronic device of a satellite visible arc, enable the data processing apparatus/electronic device of a satellite visible arc to perform the data processing method of a satellite visible arc according to any one of claims 1 to 7.

10. A computer program product comprising computer programs/instructions, characterized in that said computer programs/instructions, when executed by a processor, implement the data processing method of the satellite visible arc segment of any of claims 1 to 7.

Images