CN114757035A - Data processing method, device, medium and equipment for visible arc segment of satellite - Google Patents
Data processing method, device, medium and equipment for visible arc segment of satellite Download PDFInfo
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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
Technical Field
The invention relates to the field of data processing, in particular to a data processing method, a device, a medium and equipment for a satellite visible arc segment.
Background
At present, with the increasing application of satellites, space frequency resources become more precious, so that detailed examination needs to be performed on reporting data of each satellite to ensure that resources such as used frequency and orbit do not cause interference to the existing satellites. Therefore, software simulation needs to be carried out on the operation data provided by the satellite declaring person, and the motion tracks of all satellites can be simulated through the satellite orbit parameters provided by the satellite operation data; the signal transmitting condition of the satellite to the ground can be simulated through the satellite working frequency and the satellite transmitting wave beam in the data. For the current constellation to be checked, by means of the given working frequency, a GSO satellite or an NGSO satellite with a relatively close working frequency can be searched in the existing satellite network database as a possible interfered object, software simulation is performed according to the orbit parameters and the beam parameters, a ground station of the interfered constellation is designated, slice simulation is performed according to a time interval of 1 second by simulating a period of time, such as one year, the emission condition of useless signals of the constellation to be checked to the interfered constellation in each time slice is counted, and whether interference exists is determined by using a limit value specified by the International Telecommunication Union (ITU). For a one-year simulation time, one-second simulation interval, and for constellations where the number of satellites reaches hundreds or even thousands, there is a lot of calculations to calculate the position of each time slice, requiring large computational resources and latency.
Disclosure of Invention
The method and the device solve the technical problems that in the prior art, satellite simulation data are large in calculation amount, long in calculation period and excessive in resource consumption in the calculation process.
In order to solve the technical problem, an embodiment of the present specification provides a data processing method for a satellite visible arc segment, where the method includes:
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 preset simulation time intervals 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 starting time to the simulation ending time;
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 and 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.
Further, 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 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 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 altitude angles of two simulation time interval points adjacent to the current simulation time interval point, skipping an arc section with a specified length if the current altitude angle is larger than the altitude angles of the two adjacent simulation time interval points, 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.
Further, after determining the starting point and the ending point of the visible arc segment of the satellite to be detected, 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.
Further, the step of skipping a simulation span cycle according to the simulation time corresponding to the termination point and the satellite orbit parameter to determine the simulation start time of the next visible arc segment includes:
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.
Further, the method further comprises:
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 backward by a specified simulation interval, and the simulation starting time is determined again.
Further, the 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 includes:
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 from the starting point to the ending point.
Further, the 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 includes:
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.
In another aspect, an embodiment of the present specification provides a data processing apparatus for a satellite visible arc segment, where the apparatus includes:
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 parameters 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.
In another aspect, the present specification embodiments provide a computer readable storage medium, wherein when the instructions in the computer readable storage medium are executed by a processor of a data processing apparatus/electronic device of a satellite visible arc, the data processing apparatus/electronic device of the satellite visible arc can execute the data processing method of the satellite visible arc as described above.
In yet another aspect, the present specification provides a computer program product including a computer program/instructions, which when executed by a processor, implement the data processing method for the satellite visible arc segment as described above.
According to the data processing method, the device, the medium and the equipment for the satellite visible arc section, the satellite to be tested can be subjected to simulation calculation according to the acquired 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 at intervals of preset simulation time, and the starting point and the ending point of the satellite to be tested which can be seen by the ground station to be tested can be determined based on the altitude angle. The simulation calculation data amount can be greatly reduced by setting a longer preset simulation time interval, and then interpolation points corresponding to the track positions of the satellites to be tested between the starting point and the ending point are calculated by utilizing interpolation operation, so that the simulated motion tracks of the satellites to be tested are obtained, and the low calculation efficiency caused by excessive simulation calculation in an arc section can be avoided. According to the method and the device, only a small number of points need to be calculated, interpolation operation is utilized, all target points in the visible arc section are calculated, the number of simulation technologies needing to be collected is reduced, simulation time is greatly shortened, and simulation efficiency is accelerated.
Drawings
Fig. 1 is a schematic flowchart of a first method for processing data of a satellite visible arc provided in an embodiment of the present disclosure;
fig. 2 is a schematic flowchart of a second method for processing data of a satellite visible arc segment according to an embodiment of the present disclosure;
fig. 3 is a schematic flowchart of a data processing method for a visible arc segment of a third satellite according to an embodiment of the present disclosure;
fig. 4 is a schematic flowchart of a data processing method for a fourth satellite visible arc segment according to an embodiment of the present disclosure;
FIG. 5 is a schematic view of a processing flow of data of an arc segment visible to a satellite in an example scenario of the present specification;
FIG. 6 is a schematic diagram illustrating a data processing method for a satellite visible arc segment according to one embodiment of the present disclosure;
fig. 7 is a schematic diagram of a data processing apparatus for a satellite visible arc segment according to an embodiment of the present disclosure;
fig. 8 is a block diagram of an electronic device provided in an embodiment of the present specification.
Detailed Description
In order to make the technical solution and advantages of the present invention more comprehensible, a detailed description is given below by way of specific examples. Wherein the figures are not necessarily to scale, and certain features may be exaggerated or minimized to more clearly show details of the features; unless defined otherwise, technical and scientific terms used herein have the same meaning as those in the technical field to which this application belongs.
Referring to fig. 1, fig. 1 is a schematic flow chart of a first method for processing data of a satellite visible arc segment provided in an embodiment of the present disclosure, and as shown in fig. 1, the method for processing data of a satellite visible arc segment provided in the present disclosure may include the following steps:
s102, satellite orbit parameters of the satellite to be tested and position information of the ground station to be tested are obtained.
Specifically, the satellite orbit parameters of the satellite to be tested can simulate the motion trajectory of the satellite, and the satellite orbit parameters can include the position, the running speed, the running angle, the running attitude and other parameters of the satellite. The position information of the ground station to be tested can be that a GSO satellite or an NGSO satellite with a relatively close working frequency is searched in an existing satellite network database according to the satellite working frequency of the satellite to be tested and the satellite transmitting beam as a possible disturbed object, and software simulation is carried out according to the satellite orbit parameter and the beam parameter, so that one ground station of a disturbed constellation can be determined, namely the position information of the ground station to be tested is related to the satellite orbit parameter, the satellite working frequency and the satellite transmitting beam of the satellite to be tested.
The satellite to be tested can be a satellite or a spacecraft, can be a satellite or a spacecraft to be used, and can also be a satellite or a spacecraft which is already put into use. The ground stations to be tested may be ground stations already using satellites or spacecraft.
S104, setting the simulation starting time, the simulation ending time and the preset simulation time interval of the satellite to be tested.
In a specific implementation process, a user can define the simulation starting time, the simulation ending time and the preset simulation time interval of the satellite to be tested according to actual needs. Such as: the simulation start time was 9 am at 1 st/4/2022, and the simulation end time was 9 am at 30 st/4/2022. The preset simulation time interval may generally be set to a longer time step, such as: the time interval may be set according to specific use requirements, and the embodiment of the present specification is not specifically limited, and compared with a target time interval required by general simulation, for example, one time of simulation calculation for 1 second, the calculation amount calculated every preset simulation time interval is greatly reduced.
And S106, starting the simulation termination time from the simulation starting 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 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 the preset simulation time.
In a specific implementation process, after the position 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 position information of the ground station to be tested. And calculating the altitude angle of the satellite to be tested relative to the ground station to be tested at preset simulation time intervals from the simulation starting time until the simulation termination time is calculated. Wherein, 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, 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 the 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.
Specifically, the preset lowest transit angle can be understood as the smallest angle at which the ground station to be tested can see the satellite to be tested; the predetermined minimum transit angle may be determined according to satellite orbit parameters (e.g., track position and position information of the ground station to be tested), and generally, the predetermined 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 lowest transit angle, it can be said that the satellite to be tested is within the visual range of the ground station to be tested, and it can also be called as the transit of the satellite to be tested.
In the embodiment of the present specification, 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 by comparing the calculated altitude angle with the preset minimum transit angle. Each calculation point can be used as a sampling point, the height angle corresponding to each sampling point is compared with the preset lowest transit angle, the starting point of the visible arc segment is determined according to the track position of the satellite to be tested when the first transit angle is larger than the preset lowest transit angle, and the ending point of the visible arc segment is determined according to the track position of the satellite to be tested when the last transit angle is larger than the preset lowest transit angle. A transit identifier can be marked at the starting point, an exit identifier can be marked at the ending point, and then the arc section (namely the visible arc section) in the visible range of the ground station can be quickly inquired based on the identifiers.
In the process of judging the situation of the border crossing and the situation of the border departure by calculating the altitude angle, if the judgment result of the current sampling point is the border crossing and the last sampling point is not in the border crossing, the track position of the current sampling point is considered to be the track position of the satellite to be tested when the first track position is larger than the preset lowest border crossing angle. Similarly, if the judgment result of the current sampling point is in-environment and the judgment result of the next sampling point is in-environment, the track position of the current sampling point is considered to be the track position of the satellite to be tested when the last track position is larger than the preset lowest transit angle.
In practical implementation, considering that the starting point of the visible arc segment may be located between the time of the current sampling point and the time of the last sampling point, in order to obtain an accurate entry time, the two time points may be searched to determine the starting point of the visible arc segment. Similarly, considering that the end point of the visible arc may be located between these two points, the exact end point of the visible arc may be further searched (this search is generally performed at a time interval set by the user, such as 1 second), and at this time, it is considered that a visible arc search is ended, and the satellite orbit period is skipped 1/3, and the coarse step search is continued. In other words, since the present application sets a longer preset simulation time interval, the sampling sparsity may result in not necessarily just touching the start point and the end point of the visible arc segment. In an alternative embodiment, to solve the above problem, the algorithm will first find two points before and after the time when the 60 second step (coarse step) is crossed, for example: if the satellite enters the orbit at the time of 3 minutes and 15 seconds, however, because the sampling points are the time points of 1 minute, 2 minutes, 3 minutes and 4 minutes, the starting point of the visible arc segment is between the time points of 3 minutes and 4 minutes, at this time, special processing is carried out between the two points of 3 minutes and 4 minutes, and the time point of 3 minutes and 15 seconds is accurately found through a search algorithm to be used as the starting point. Similarly, the termination point is determined by a similar method. Therefore, as for the arc segment result of the final coarse step sampling, the first point starts from 3 minutes and 15 seconds instead of 3 minutes, and the starting point and the ending point of the visible arc segment are accurately searched, so that the accurate time of 1 second level set by a user is obtained, and the phenomenon of missing points is prevented.
Generally, the altitude angle corresponding to the simulation start time is smaller than a preset lowest transit angle, but if the altitude angle corresponding to the simulation start time is larger than the preset lowest transit angle, the simulation start time is shifted backward by a specified simulation interval, and the simulation start time is determined again.
In a specific implementation process, if the altitude angle corresponding to the simulation start time is greater than the preset lowest 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 start point of the visible arc segment of the satellite to be tested should appear before the simulation start time, and the simulation start time misses the start point of the visible arc segment. Based thereon, the simulation start time may be pushed back by a specified simulation interval, such as 100 seconds, a new simulation start time is determined, and the calculation of the visible arc segment is performed starting from the new simulation start time. The specific value of the specified simulation interval may be set according to actual needs, and embodiments of the present specification are not specifically limited. By re-determining the simulation starting time, the initial position of the satellite to be tested at the ground station to be tested is accurately inquired, and an accurate data base is laid for the inquiry of the subsequent visible arc section.
In an alternative embodiment, the height angles corresponding to the starting point and the ending point may be equal or unequal. In addition, the corresponding height angle between the starting point and the ending point may be raised first and then lowered, that is, the height angle corresponding to the starting point gradually rises to the over-peak point and then is lowered from the over-peak point to the height angle corresponding to the ending point. Wherein, the over-peak is the highest elevation angle between the starting point and the ending point.
S110, performing interpolation operation on 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.
Specifically, the preset simulation time interval set in the embodiments of the present specification is generally relatively large, and the preset simulation time interval may be set to be greater than a specified time threshold, for example: and the time is more than 60 seconds, so the calculated sampling points are sparse, and all the required target points need to be expanded by a subsequent interpolation algorithm. In the embodiment of the specification, interpolation operation is performed by using the track position corresponding to the to-be-tested satellite corresponding to each preset simulation time interval between the starting point and the ending point, so that a plurality of interpolation points from the starting point to the ending point are obtained. Such as: a plurality of interpolation points can be inserted 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 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, a larger number of interpolation points can be inserted between each sampling point according to actual needs, the number of the interpolation points can be set according to actual needs, and the embodiment of the specification is not specifically limited.
S112, 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.
Specifically, after obtaining the interpolation points, a curve formed by the starting point, the trajectory positions 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, and it can be understood that each trajectory point of the satellite to be tested in the visible arc segment is within the visible range of the ground station. After the simulated motion track is determined, whether the to-be-tested satellite interferes with the to-be-tested ground station or the satellite corresponding to the to-be-tested ground station or not can be analyzed according to the information such as the position, the angle, the speed, the attitude, the signal emission frequency and the like of the to-be-tested satellite corresponding to each track point in the visible arc section.
According to the data processing method for the satellite visible arc section, provided by the embodiment of the specification, simulation calculation can be performed on a 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, the altitude angle of the satellite to be tested relative to the ground station to be tested is calculated at intervals of preset simulation time, and the starting point and the ending point of the satellite to be tested, which can be seen by the ground station to be tested, are determined based on the altitude angle. The simulation calculation data amount can be greatly reduced by setting a longer preset simulation time interval, and then interpolation points corresponding to the track positions of the satellites to be tested between the starting point and the ending point are calculated by interpolation operation, so that the simulated motion tracks of the satellites to be tested are obtained, and the low calculation efficiency caused by excessive simulation calculation in an arc section can be avoided. According to the method and the device, only a small number of points need to be calculated, interpolation operation is utilized, all target points in the visible arc section are calculated, the number of simulation technologies needing to be collected is reduced, simulation time is greatly shortened, and simulation efficiency is accelerated.
On the basis of the foregoing embodiment, in an embodiment of this specification, fig. 2 is a schematic flow chart of a second method for processing data of a satellite visible arc segment provided in this specification, and as shown in fig. 2, the calculating an altitude angle of the to-be-tested satellite relative to the to-be-tested ground station every preset simulation time interval according to the satellite orbit parameter of the to-be-tested satellite and the position information of the to-be-tested ground station from the simulation start time to the simulation end time includes:
s202, after calculating the current altitude corresponding to the current simulation time interval point, comparing the current altitude with the preset lowest transit angle, and if the current altitude is smaller than the preset lowest transit angle, calculating the altitude corresponding to two adjacent simulation time interval points of the current simulation time interval point.
S204, comparing the current altitude angle with altitude angles of two simulation time interval points adjacent to the current simulation time interval point, if the current altitude angle is larger than the altitude angles of the two adjacent simulation time interval points and the current altitude angle is smaller than the preset lowest transit angle, skipping arc segments with appointed length, re-determining 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.
Specifically, when the altitude angle of the to-be-tested satellite relative to the to-be-tested ground station is calculated at intervals of preset simulation time, the calculated altitude angle can be compared with the preset lowest transit angle every time when one altitude angle is calculated, and if the current altitude angle corresponding to the current simulation time interval point is smaller than the preset lowest transit angle, it is indicated that the track position corresponding to the to-be-tested satellite corresponding to the current simulation time interval point is not within the visual range of the to-be-tested ground station. At this time, in the embodiments of the present specification, the altitude angles corresponding to two simulation time interval points adjacent to the current simulation time interval point may be calculated, that is, the altitude angles corresponding to the simulation time interval points at one preset simulation time interval before or after the current simulation time interval point are calculated. And comparing the sizes of the three altitude angles, and if the middle altitude angle, namely the current altitude angle is larger than the other two altitude angles, indicating that the satellite to be tested at the current simulation time interval point passes through the top. However, even if the altitude angle of the satellite to be tested is still smaller than the preset minimum transit angle after the satellite to be tested passes through the top, the satellite to be tested cannot be within the visual range of the ground station to be tested in a long arc section, and the visual arc section cannot be near the current simulation time interval point. At this time, the arc segment with the appointed length can be skipped, the simulation starting time is re-determined, and the altitude angle of the satellite to be tested relative to the ground station to be tested is re-calculated every preset simulation time interval based on the re-determined simulation starting time so as to re-calculate the visible arc segment.
The over-vertex can be understood as that the altitude angle of the ground station looking at the satellite or the spacecraft reaches the maximum value, the orbit of the satellite does not necessarily pass right above the ground station, and therefore is not necessarily 90 degrees, the angle is the limit value of the current arc ground station towards the satellite, but due to sparsity of sampling points, the satellite does not necessarily just touch, and by continuously sampling 3 time points, if the satellite passes over the vertex when approaching the 2 nd time point, the altitude angle of the 2 nd time point is larger than the altitude angles of the first time point and the third time point.
It can be understood that the three time points sampled in the embodiment of the present 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 a previous simulation time interval point and a next simulation time interval point of a simulation time interval, and then the current simulation time point is the middle time point. In practical use, the current simulation time interval point and two simulation time interval points before the current simulation time interval point, or the current simulation time interval point and two simulation time interval points after the current simulation time interval point may also be taken as three continuous nodes.
In addition, the designated arc segment can be preset and can be determined according to actual needs, such as: the orbit half of the satellite to be tested can be set to 1/3, or the simulation calculation can be started from the next circle by directly skipping one circle of the orbit of the satellite to be tested.
In the embodiment of the description, the characteristic of altitude angle change is repeatedly considered, when the current altitude angle is determined to be the passing vertex angle smaller than the preset lowest crossing angle, whether the satellite to be tested passes the top at the current time is judged, if yes, the track position of the satellite to be tested in the appointed arc section can be directly skipped, the simulation starting time is determined again, and the visible arc section is calculated again. The arc section which is basically impossible to appear in the visual range of the ground station to be tested is avoided, the simulation calculation amount is greatly reduced, and the data processing efficiency is improved.
On the basis of the foregoing embodiments, in this embodiment of the present specification, fig. 3 is a schematic flowchart of a data processing method for a visible arc segment of a third satellite provided in this embodiment of the present specification, and as shown in fig. 3, the method further includes:
s302, skipping a simulation span cycle 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.
Specifically, the simulation span period is a time length of a specified multiple of one circle of the to-be-tested satellite running around the star where the to-be-tested ground station is located, and can be understood as being capable of skipping an arc section which does not need to be subjected to simulation calculation, for example, if the time of one circle of the to-be-tested satellite running around the star where the to-be-tested ground station is located is T, the simulation span period can be half of T or one third of T.
In practical application, considering that each circle of satellites can only cross a border once, namely, a general satellite to be tested generally only appears in a visual range of a ground station to be tested once when running for a circle, and the change of the altitude angle of the satellite is a trend of increasing and then decreasing.
In an optional embodiment, fig. 4 is a schematic flow chart of a fourth method for processing data of a satellite visible arc segment provided in this specification, and as shown in fig. 4, the step S302 of skipping a simulation span period according to a simulation time corresponding to the termination point and the satellite orbit parameter, and determining a simulation start time of a next visible arc segment may include:
s3022, determining the orbit period of the satellite to be tested according to the satellite orbit parameters.
Specifically, the satellite orbit parameters may further include the operation speed of the satellite to be tested and the operation trajectory of the satellite to be tested, and the orbit period of the satellite to be tested may be determined based on the operation speed of the satellite to be tested and the operation trajectory of the satellite to be tested, that is, the orbit period, which is the time for the satellite to be tested to operate for one week, is calculated.
And S3024, calculating the simulation span period according to the track period and the simulation span proportion.
Specifically, the simulation span ratio may be determined according to actual needs or according to historical experience, and the simulation span ratio in this embodiment may be one third of the track cycle, that is, the simulation span cycle is one third of T.
And S3026, pushing the simulation time interval point corresponding to the simulation span period backwards from the simulation time interval point corresponding to the termination point, and taking the simulation time interval point as the simulation starting time of the next visible arc segment.
Specifically, in the embodiments of the present disclosure, considering that the arc length of each pass of the satellite through the disturbed ground station is greater than 1/3 orbit cycles (one orbit cycle is considered as being rotated by 360 degrees around the earth), after the search for one arc is finished, we can search for the starting point of the next arc by 1/3 orbit cycles. In general, skipping 1/3 track cycles can achieve a more efficient search within 1/3 track cycles after the end of an arc, which is less likely to be visible again. The simulation starting time of the next visible arc segment 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 starting time point of the next visible arc segment is the sum of the simulation time corresponding to the end point of the previous visible arc segment and one third of the track period T. Namely T2T 1+ T/3. Wherein t1 is the simulation time corresponding to the end point of the last visible arc segment, and t2 is the simulation start time point of the next visible arc segment.
And skipping corresponding time intervals in a simulation span period mode, and restarting to calculate the altitude angle of the satellite to be tested relative to the ground station to be tested every other preset simulation period when the simulation starting time point of the next visible arc segment is started, so that the interference of the invisible arc segment on simulation calculation can be reduced, the simulation calculation data flow is reduced, and the simulation calculation efficiency is improved.
Fig. 5 is a schematic view of a processing flow of satellite visible arc data in a scene example in this specification, and as shown in fig. 5, a simulation time range may be preset, simulation calculation of a visible arc is performed within the set time range, an altitude angle of a satellite to be tested is calculated every preset simulation period, whether the satellite passes through is determined based on the altitude angle, that is, whether the satellite is within a visible range of a ground station to be tested, specifically, the altitude angle may be compared with a preset minimum transit angle, and specific details may be referred to the description of the above embodiment, and are not described herein again. When the time node of the first crossing is found, a crossing identifier can be added, namely, the satellite is identified to enter the visible range of the ground station, the satellite entering identifier can also be called as a satellite entering identifier, after the altitude angle is calculated subsequently, whether the satellite has the crossing identifier can be judged firstly, if the satellite exists, the satellite is indicated to be in the visible range of the ground station to be tested, whether the current node exits or not is judged continuously based on the altitude angle, if the satellite exits, the exiting identifier is set, and if the satellite does not exit, the calculation of the next time node is continued. If the current time node satellite does not have the transit identifier, which indicates that the satellite does not exist within the visible range of the ground station, it may be determined whether it is necessary to continue the calculation by determining whether the current time node satellite is over-topped.
On the basis of the foregoing embodiment, in an embodiment of the present specification, the performing interpolation operation by using the track position corresponding to the to-be-tested satellite 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 may include:
and carrying out interpolation operation on the track position corresponding to the satellite to be tested and corresponding to each preset simulation time interval between the starting point and the ending point by adopting a cubic spline interpolation algorithm to obtain a plurality of interpolation points from the starting point to the ending point.
Specifically, cubic Spline interpolation, called Spline interpolation for short, is a process of obtaining a curve function set mathematically by solving a three bending moment equation set through a smooth curve of a series of shape value points. The interpolation method is suitable for fitting a curve, is matched with a motion curve of a satellite, and is a process of a cubic spline interpolation method.
Firstly, extracting points of each arc segment to form a set ti,posiWhere t isiRefers to the time difference of the current point from the starting point, in seconds, posiIs the coordinate information of the current moment (the coordinates of the track position of the satellite to be tested).
Equation S for constructing a cubic curvei＝aix+bix2+cix3+dix4。
Where x can be understood as the time difference, SiFor longitude coordinates, since the first derivative of the points inside the cubic equation should be continuous, we can get the { x } for any one intervali,xi+1Where at the end of the i-th interval and at the start of the i + 1-th interval are the same point, their first derivatives should also be equal, i.e. Si'(xi+1)＝Si+1'(xi+1) And the internal second derivative also needs to be continuous, having Si”(xi+1)＝Si+1”(xi+1)。
The above can be found in an equation as follows:
wherein: h isi＝xi+1-xi，mi＝Si”(xi+1)＝2ci
The equation recorded in the embodiment can be used for constructing a curve to simulate the motion track of the satellite, and then the position and the time offset of the satellite are input to simulate the motion track of the satellite. For example: the longitude of the satellite and the time difference from the start point are input, (110.12,0), (110.23,60), (110.35,120), (110.79,180), (111.23,240), (111.44,300), and so on. Through the input points, an equation set can be listed, and each a is obtainedi，bi，ci，diIf the longitude coordinate of a certain point in the arc segment is to be obtained, the longitude value of the time point can be obtained immediately only by inputting the time offset from the starting point into the equation, for example, 15s, without complicated calculation.
It will be appreciated that each visible arc is continuous and satisfies the curve characteristics, so for each arc, the usual approach is to simulate every time slice that needs to be simulated, such as calculating the spatial position of the satellite and the angular relationship of orientation to the disturbed earth station every second. Due to the continuous curve characteristic of each arc segment, the embodiment of the specification only needs to calculate according to the step length of 30 seconds or 60 seconds, and after the spatial position and the angle relation of every 60 seconds are obtained, the satellite position and the angle information of every 1 second can be obtained by expanding through a curve interpolation algorithm.
In the embodiment of the specification, each arc segment point in the arc segment of the simulation calculation is calculated by a cubic spline interpolation method, so that the calculation amount of satellite simulation software is reduced, and any position information and angle information of the satellite to be tested corresponding to the corresponding step length can be directly calculated by the interpolation method.
Fig. 6 is a schematic diagram illustrating a principle of a data processing method of a satellite visible arc segment in an embodiment of the present specification, and as shown in fig. 6, the data processing method of the satellite visible arc segment provided in the embodiment of the present specification may first roughly query a visible arc segment of a satellite to be tested in a visible range of a ground station to be tested by setting a relatively large preset simulation time interval according to satellite network data, and then perform interpolation calculation on points in the arc segment, thereby obtaining an accurate visible arc segment. The method can avoid low calculation efficiency caused by excessive points calculated in the arc section, only a small number of points need to be calculated and all points in the curve need to be interpolated, any fine time interval calculation can be carried out, and if the requirement on the time interval is within 1 second, even millisecond-level simulation is carried out by the traditional calculation method, a large amount of calculation resources and time resources are needed to be consumed, and the efficiency of the auditing progress of satellite network data is very low. After the interpolation method is used, the simulation time can be greatly reduced, and the simulation efficiency is accelerated.
On the other hand, fig. 7 is a schematic diagram of a data processing apparatus for a satellite visible arc segment according to an embodiment of the present disclosure, and as shown in fig. 7, the data processing apparatus for a satellite visible arc segment according to an embodiment of the present disclosure includes:
an information acquisition module 701 configured to perform acquisition of satellite orbit parameters of a satellite to be tested and position information of a ground station to be tested;
a simulation parameter configuration module 702 configured to set a simulation start time, a simulation end time, and a preset simulation time interval of the satellite to be tested;
a calculating module 703 configured to calculate, from the simulation start time to the simulation end time, an altitude angle of the satellite to be tested relative to the ground station to be tested and a track position corresponding to the satellite to be tested at preset simulation time intervals according to the satellite orbit parameter of the satellite to be tested and the position information of the ground station to be tested;
a visible arc segment determining module 704 configured to determine a starting point of a visible arc segment according to the track position of the satellite to be tested when the first altitude angle is greater than a preset lowest transit angle, and determine an ending point of the visible arc segment according to the track position of the satellite to be tested when the last altitude angle is greater than the preset lowest transit angle;
an interpolation operation module 705 configured to perform an interpolation operation using a 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;
a simulated motion trajectory determination module 706 configured to perform 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, so as to obtain a simulated motion trajectory of the satellite to be tested.
The data processing device of the satellite visible arc segment provided in the embodiment of the present specification has the same concept and the same technical features as those of the data processing method of the satellite visible arc segment, and therefore, has the same technical effects, and will not be described herein in detail.
Fig. 8 is a block diagram of an electronic device provided in an embodiment of the present specification, where the electronic device may be a terminal, and an internal structure diagram of the electronic device may be as shown in fig. 8. The electronic device comprises a processor, a memory, a network interface, a display screen and an input device which are connected through a system bus. Wherein the processor of the electronic device is configured to provide computing and control capabilities. The memory of the electronic equipment comprises a nonvolatile 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 an operating system and computer programs in the non-volatile storage medium. The network interface of the electronic device is used for connecting and communicating with an external terminal through a network. The computer program is executed by a processor to implement a method of data processing of a satellite visible arc segment. The display screen of the electronic equipment can be a liquid crystal display screen or an electronic ink display screen, and the input device of the electronic equipment can be a touch layer covered on the display screen, a key, a track ball or a touch pad arranged on the shell of the electronic equipment, an external keyboard, a touch pad or a mouse and the like.
Those skilled in the art will appreciate that the architecture shown in fig. 8 is merely a block diagram of some of the structures associated with the disclosed aspects and does not constitute a limitation on the electronic devices to which the disclosed aspects apply, as a particular electronic device may include more or less components than those shown, or combine certain components, or have a different arrangement of components.
In an exemplary embodiment, there is also provided an electronic device including: a processor; a memory for storing the processor-executable instructions; wherein the processor is configured to execute the instructions to implement a data processing method of a satellite visible arc segment as in an embodiment of the present disclosure.
In an exemplary embodiment, there is also provided a computer-readable storage medium, in which instructions, when executed by a processor of an electronic device, enable the electronic device to perform a data processing method of a satellite visible arc segment in an embodiment 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, and the like.
In an exemplary embodiment, there is also provided a computer program product containing instructions which, when run on a computer, cause the computer to perform a method of data processing of a satellite visible arc segment in an embodiment of the present disclosure.
It will be understood by those skilled in the art that all or part of the processes of the methods of the embodiments described above may be implemented by hardware instructions of a computer program, which may be stored in a non-volatile computer-readable storage medium, and when executed, the computer program may include the processes of the embodiments of the methods described above. Any reference to memory, storage, database, or other medium used in the embodiments provided herein may include non-volatile and/or volatile memory, among others. Non-volatile memory can include read-only memory (ROM), Programmable ROM (PROM), Electrically Programmable ROM (EPROM), Electrically Erasable Programmable ROM (EEPROM), or flash memory. Volatile memory can include Random Access Memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in a variety of forms such as Static RAM (SRAM), Dynamic RAM (DRAM), Synchronous DRAM (SDRAM), Double Data Rate SDRAM (DDRSDRAM), Enhanced SDRAM (ESDRAM), Synchronous Link DRAM (SLDRAM), Rambus Direct RAM (RDRAM), direct bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).
It should be understood that the above embodiments are exemplary and are not intended to encompass all possible implementations encompassed by 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 features of the above embodiments may be arbitrarily combined to form additional embodiments of the present invention that may not be explicitly described. Therefore, the above examples only represent some embodiments of the present invention, and do not limit the scope 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.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115276771A (en) * | 2022-07-28 | 2022-11-01 | 银河航天(北京)网络技术有限公司 | Method and device for simulating service range of non-stationary orbit satellite gateway station |
| CN116996115A (en) * | 2023-09-26 | 2023-11-03 | 国家卫星海洋应用中心 | Low-orbit satellite receiving time window calculation method, device and equipment |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115276771A (en) * | 2022-07-28 | 2022-11-01 | 银河航天(北京)网络技术有限公司 | Method and device for simulating service range of non-stationary orbit satellite gateway station |
| CN115276771B (en) * | 2022-07-28 | 2024-01-16 | 银河航天(北京)网络技术有限公司 | Non-stationary orbit satellite gateway station service range simulation method and device |
| CN116996115A (en) * | 2023-09-26 | 2023-11-03 | 国家卫星海洋应用中心 | Low-orbit satellite receiving time window calculation method, device and equipment |
| CN116996115B (en) * | 2023-09-26 | 2023-12-22 | 国家卫星海洋应用中心 | Low-orbit satellite receiving time window calculation method, device and equipment |
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