CN115983035A - Satellite visibility simulation method and device - Google Patents

Satellite visibility simulation method and device Download PDF

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Publication number
CN115983035A
CN115983035A CN202310074241.XA CN202310074241A CN115983035A CN 115983035 A CN115983035 A CN 115983035A CN 202310074241 A CN202310074241 A CN 202310074241A CN 115983035 A CN115983035 A CN 115983035A
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simulation
time point
satellite
current
visibility
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张鹏
花国良
张世杰
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Galaxy Aerospace Beijing Network Technology Co ltd
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Galaxy Aerospace Beijing Network Technology Co ltd
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Abstract

The application provides a satellite visibility simulation method and a satellite visibility simulation device, wherein the satellite visibility simulation method comprises the following steps: generating a simulation time point set according to the preset simulation duration and the preset simulation stepping; grouping ground stations to be simulated and satellites to be simulated based on a set grouping strategy, and constructing at least two simulation object groups, wherein the at least two simulation object groups perform visibility simulation in parallel, and each simulation object group comprises at least one ground station to be simulated and at least one satellite to be simulated; and selecting a target satellite and a target ground station from the target simulation object group, performing visibility simulation on the target satellite and the target ground station based on the simulation time point set, and determining a visibility simulation result of the target satellite for the target ground station. Therefore, the grouping strategy can be customized, the ground station to be simulated and the satellite to be simulated are grouped, parallelization processing is adopted, computer resources are utilized to the maximum extent, and the visibility simulation efficiency is greatly improved.

Description

Satellite visibility simulation method and device
Technical Field
The application relates to the technical field of non-stationary orbit satellite communication, in particular to a satellite visibility simulation method. The application also relates to a satellite visibility simulation apparatus, a computing device, and a computer-readable storage medium.
Background
With the development of satellite communication technology, satellite communication gains attention from all countries in the world in the field of communication due to the characteristics of wide coverage, strong mobility, large transmission capacity, flexible networking mode, no geographic condition limitation and the like. In recent years, various large companies have been planned to deploy non-geostationary orbit satellite (NGSO) communication systems to provide high-speed broadband internet services, and in the future, in a scenario where the non-geostationary orbit satellite communication system and a geostationary orbit satellite (GSO) communication system coexist at the same frequency, because the satellite scale of the non-geostationary orbit satellite communication system is huge, the global coverage is continuous and a user terminal is ubiquitous, harmful interference is easily caused to the geostationary orbit satellite communication system.
Therefore, how to efficiently analyze the interference between the non-geostationary orbit satellite communication system and the geostationary orbit satellite communication system is also a current difficult problem, and the rapid calculation of the visibility of the satellites in the non-geostationary orbit satellite communication system to the ground station is the basis for interference simulation. In the prior art, the visibility of the satellites to the ground station is often simulated one by one through a relatively universal software tool, the simulation efficiency is greatly reduced along with the increase of the calculation amount such as the constellation scale, and otherwise the simulation precision needs to be sacrificed.
Disclosure of Invention
In view of this, the present application provides a satellite visibility simulation method. The application also relates to a satellite visibility simulation device, a computing device and a computer readable storage medium, which are used for solving the technical defects in the prior art.
According to a first aspect of embodiments of the present application, a satellite visibility simulation method is provided, including:
generating a simulation time point set according to the preset simulation duration and the preset simulation stepping;
grouping ground stations to be simulated and satellites to be simulated based on a set grouping strategy to construct at least two simulation object groups, wherein the at least two simulation object groups perform visibility simulation in parallel, and each simulation object group comprises at least one ground station to be simulated and at least one satellite to be simulated;
selecting a target satellite and a target ground station from a target simulation object group, performing visibility simulation on the target satellite and the target ground station based on the simulation time point set, and determining a visibility simulation result of the target satellite for the target ground station, wherein the target simulation object group is any one of at least two constructed simulation objects, the target satellite is any one of the target simulation object group, and the target ground station is any one of the target simulation object group.
According to a second aspect of embodiments of the present application, there is provided a satellite visibility simulation apparatus including:
the generation module is configured to generate a simulation time point set according to a preset simulation duration and a preset simulation step;
the system comprises a grouping module, a simulation module and a simulation module, wherein the grouping module is configured to group a ground station to be simulated and a satellite to be simulated based on a set grouping strategy and construct at least two simulation object groups, the at least two simulation object groups perform visibility simulation in parallel, and each simulation object group comprises at least one ground station to be simulated and at least one satellite to be simulated;
the simulation module is configured to select a target satellite and a target ground station from a target simulation object group, perform visibility simulation on the target satellite and the target ground station based on the simulation time point set, and determine a visibility simulation result of the target satellite for the target ground station, where the target simulation object group is any one of at least two constructed simulation objects, the target satellite is any one of the target simulation object groups, and the target ground station is any one of the target simulation object groups.
According to a third aspect of embodiments herein, there is provided a computing device comprising:
a memory and a processor;
the memory is configured to store computer-executable instructions and the processor is configured to execute the computer-executable instructions to implement the steps of the satellite visibility simulation method of any one of the above.
According to a fourth aspect of embodiments herein, there is provided a computer-readable storage medium storing computer-executable instructions that, when executed by a processor, implement the steps of the satellite visibility simulation method of any one of the above.
According to the satellite visibility simulation method, a simulation time point set is generated according to preset simulation duration and preset simulation steps; grouping ground stations to be simulated and satellites to be simulated based on a set grouping strategy to construct at least two simulation object groups, wherein the at least two simulation object groups perform visibility simulation in parallel, and each simulation object group comprises at least one ground station to be simulated and at least one satellite to be simulated; selecting a target satellite and a target ground station from a target simulation object group, performing visibility simulation on the target satellite and the target ground station based on the simulation time point set, and determining a visibility simulation result of the target satellite for the target ground station, wherein the target simulation object group is any one of at least two constructed simulation objects, the target satellite is any one of the target simulation object group, and the target ground station is any one of the target simulation object group. Under the condition, a grouping strategy can be customized, the ground station to be simulated and the satellite to be simulated are grouped, at least two simulation object groups are constructed, visibility simulation is performed on each at least two simulation object groups in parallel, parallelization processing is adopted, computer resources are utilized to the maximum extent, visibility simulation is performed quickly, and the efficiency of visibility simulation is improved greatly while the simulation precision is not reduced.
Drawings
Fig. 1 is a flowchart of a satellite visibility simulation method according to an embodiment of the present application;
fig. 2a is a communication diagram of a satellite communication system according to an embodiment of the present application;
FIG. 2b is a schematic diagram of a parallel simulation computation flow provided by an embodiment of the present application;
FIG. 3 is a process flow diagram of a method for simulating visibility of a target satellite and a target ground station according to an embodiment of the present application;
fig. 4 is a schematic structural diagram of a satellite visibility simulation apparatus according to an embodiment of the present application;
fig. 5 is a block diagram of a computing device according to an embodiment of the present application.
Detailed Description
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application. This application is capable of implementation in many different ways than those herein set forth and of similar import by those skilled in the art without departing from the spirit and scope of this application, and thus this application is not limited to the specific implementations disclosed below.
The terminology used in the one or more embodiments of the present application is for the purpose of describing particular embodiments only and is not intended to be limiting of the one or more embodiments of the present application. As used in one or more embodiments of the present application and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and/or" as used in one or more embodiments of the present application refers to and encompasses any and all possible combinations of one or more of the associated listed items.
It will be understood that, although the terms first, second, etc. may be used herein in one or more embodiments of the present application to describe various information, these information should not be limited by these terms. These terms are only used to distinguish one type of information from another. For example, a first aspect may be termed a second aspect, and, similarly, a second aspect may be termed a first aspect, without departing from the scope of one or more embodiments of the present application. The word "if" as used herein may be interpreted as "at" ... "or" when ...or" in response to a determination ", depending on the context.
First, the noun terms to which one or more embodiments of the present application relate are explained.
A stationary orbit satellite: geostationary orbital satellite, a GSO satellite, means that the orbital plane coincides with the equatorial plane, the orbital period of the satellite is equal to the rotation period of the earth in the inertial space, and the direction of the satellite is consistent with the rotation period, and the position of the satellite relative to the ground is kept unchanged.
Non-geostationary orbit satellite: non-geostationary satellite, NGSO means satellites other than GSO satellites, which are most different from GSO satellites in their dynamics with respect to ground position.
It should be noted that, in recent years, a dispute plan of each large company deploys the NGSO communication system to provide high-speed broadband internet service, and in a future scenario where the NGSO communication system and the GSO communication system coexist at the same frequency, because the NGSO communication system has a huge satellite scale, is continuously covered globally and has no user terminal, harmful interference is easily caused to GSO communication. How to efficiently analyze the interference between the large-scale NGSO communication system and the GSO communication system is also a current difficult problem, and the rapid calculation of the visibility relationship between the large-scale NGSO constellation and the ground station or the visibility relationship between the massive ground stations and the NGSO constellation is the basis of interference simulation analysis.
The current relatively universal software tool STK (SystemToolkit) has the problems of complex operation and overlong simulation time when calculating a large-scale NGSO communication system. In addition, when the conventional software calculates the tracking arc sections (and tracking analysis visibility) of the ground station and the low-orbit satellite, a point-by-point calculation method and a cutting method according to the elevation angle constraint are adopted, so that the calculation efficiency is low.
As can be seen from the above, in the above scheme, the simulation task needs to adopt an operation mode fixedly provided by the simulation software, and needs to completely model each factor of the simulation scene, which is high in complexity and insufficient in flexibility; in addition, the simulation process is not controllable, and the problems of setting errors, accidental quitting and the like of a simulation scene are not easy to position; moreover, the simulation scale is limited, and when the software is used for simulation, the simulation efficiency is greatly reduced along with the increase of the calculation amount such as the constellation scale, and otherwise, the simulation precision needs to be sacrificed.
The method and the device can solve the problem that the track forecast and visibility calculation of the current general software is slow in interference simulation analysis of the NGSO communication system and the GSO communication system. In the concrete implementation, the calculation time can be compressed by adopting a parallel calculation method in the links of track forecasting and visibility calculation; moreover, the visibility characteristics (namely transit characteristics) of the satellite to the ground station are fully considered, a calculation method for tracking the visibility is innovated, and a large-span searching method is adopted, so that the efficiency of the calculation of the visibility of the single station to the satellite is improved. That is, aiming at the problem that the interference simulation analysis time of the NGSO communication system to the GSO communication system is long, a parallel simulation strategy is adopted, a visibility calculation algorithm is optimized, and the simulation calculation efficiency is improved.
In the present application, a satellite visibility simulation method is provided, and the present application relates to a satellite visibility simulation apparatus, a computing device, and a computer-readable storage medium, which are described in detail in the following embodiments one by one.
Fig. 1 shows a flowchart of a satellite visibility simulation method according to an embodiment of the present application, which specifically includes the following steps 102 to 106:
step 102: and generating a simulation time point set according to the preset simulation duration and the preset simulation stepping.
Specifically, the simulation uses a project model to translate uncertainty specific to a particular level into their impact on the targets, which is expressed at the level of the simulation project as a whole, using a computer model and a particular level of risk estimation. Project models in embodiments of the present application may include satellites and ground stations to simulate satellite visibility to ground stations.
It should be noted that, in the simulation, a simulation duration and a simulation step are usually set. Specifically, the simulation duration may be determined according to actual requirements, for example, the preset simulation duration may be a duration of one week of orbital motion of the non-stationary orbiting satellite in the satellite, or the simulation duration may be a duration of one week of revolution of the earth, or may be other durations, such as 30 days, 365 days, and the like, which is not limited in this application. The simulation duration is different from the real time, and is only one representation of the time in the computer simulation.
In addition, the simulation stepping can also be determined according to actual requirements, and the preset simulation stepping specifically refers to the length of one simulation time in each simulation, and the smaller the simulation stepping is, the higher the simulation precision is, the more the sampling step is, and the longer the time required for completing one simulation is. For example, the preset simulation step may be 1 second, 1 minute, 1 hour, or other time duration, which is not limited in this application.
In practical application, the simulation time point specifically refers to a time point which needs to be subjected to simulation calculation in simulation, and after the preset simulation time length and the preset simulation step are determined, the simulation time point set can be determined according to the preset simulation time length and the preset simulation step. Specifically, the preset simulation time length may be divided according to the preset simulation step, that is, the preset simulation time length is divided according to the preset simulation step from the start point of the preset simulation time length to generate at least two simulation time points, and the generated simulation time points are combined into the simulation time point set.
For example, if the preset simulation duration is 24h (from 0 point to 23 point), and the simulation step is 1h, the generated simulation time points are divided, namely 0 point, 1 point, 2 points, ..., 23 points, and the like, and 24 time points exist in the simulation time point set; or the preset simulation duration is 1440 minutes, the preset simulation stepping is 1 minute, and then 1 minute, 2 minutes, 3 minutes, 8230, 1440 minutes and the like are generated by division, and 1440 time points exist in the simulation time point set.
Step 104: and grouping the ground station to be simulated and the satellite to be simulated based on a set grouping strategy to construct at least two simulation object groups, wherein the at least two simulation object groups perform visibility simulation in parallel, and each simulation object group comprises at least one ground station to be simulated and at least one satellite to be simulated.
The satellite communication system is a system that transmits radio signals by using a satellite as a relay station to realize user information transmission such as ground and space. For a satellite communication system, regardless of an inter-satellite link, an uplink and a downlink are required to be formed by a gateway station, a user terminal and a satellite to complete communication, referring to fig. 2a, fig. 2a shows a communication schematic diagram of a satellite communication system provided by an embodiment of the present application, as shown in fig. 2a, a user terminal completes communication through a satellite and a gateway station, a link in which a gateway station transmits data to a satellite, a link in which a user terminal transmits data to a satellite is called an uplink, a link in which a satellite transmits data to a gateway station, and a link in which a satellite transmits data to a user terminal is called a downlink. The gateway station sends data to the satellite, the satellite forwards the data to the user terminal, the user terminal sends feedback data to the satellite after completing corresponding processing, and the satellite sends the feedback data to the gateway station, so that one-time communication among the gateway station, the satellite and the user terminal is completed.
The satellite is a communication satellite, and is a space part of a satellite communication system, so that any ground, sea and air communication stations in a visible region can simultaneously communicate with each other. In a satellite communication system, a gateway station is an essential part, and a user who wants to use a satellite needs to connect a user terminal to the satellite and a device for transferring data of the satellite to a ground public network, and the device is the gateway station. The range of visibility of a gateway station, like a base station in an existing communication network, can be up to thousands of kilometers. The gateway station is a data center node of the satellite communication system, is responsible for distributing and collecting satellite communication service data, can complete the exchange of internal data of the satellite communication system and the data routing to an external network, has network management and operation control functions, and is responsible for completing the whole network resource scheduling, system equipment management and user service management.
It should be noted that, in the embodiment of the present application, a ground station refers to a component of a satellite communication system, that is, a ground device arranged on the earth and used for implementing satellite communication, and a ground device used for inputting programs and data to a computer or receiving a processing result output by the computer via a communication facility, for example, the ground station may mainly include a gateway station, a user terminal performing communication through a satellite, a measurement and control station, and the like, the user terminal may include a fixed terminal, a mobile terminal, and the fixed terminal includes a Very Small Aperture Terminal (VSAT) used in a private network, a terminal installed on a roof and used for receiving satellite broadcast signals, and the like; compared with a fixed terminal, the mobile terminal has certain flexibility, such as a news collection vehicle, a mobile ship and the like; mobile terminals are often referred to as hand-held terminals, such as satellite phones.
As can be seen from the above, in the embodiment of the present application, ground devices such as the gateway station, the user terminal, and the measurement and control station, which are disposed on the earth, are collectively referred to as the ground station, and in the embodiment of the present application, the ground station is used for satellite visibility simulation, that is, the satellite visibility simulation method provided in the embodiment of the present application can be used to perform visibility simulation on the ground devices such as the gateway station, the user terminal, and the measurement and control station, which are disposed on the earth.
In particular, the satellite subjected to visibility simulation may refer to a non-geostationary orbit satellite, i.e., an NGSO satellite. Generally, satellites with orbit heights lower than 35789km and a period of rotation around the earth smaller than 24h are collectively called non-stationary orbit satellites, in an actual NGSO satellite system, most of circular orbits are adopted, and the NGSO satellites are characterized by low orbit heights, small link propagation loss and small transmission delay, so that the NGSO satellites are increasingly applied at present.
In practical application, when the visibility of the to-be-simulated satellite to the to-be-simulated ground station is analyzed, the to-be-simulated ground station and the to-be-simulated satellite can be grouped based on a set grouping strategy, at least two simulation object groups are constructed, the visibility simulation is performed on the at least two simulation object groups in parallel, and the parallel strategy is adopted, so that the simulation effect is improved. The set grouping policy may refer to a preset grouping rule, and the set grouping policy may be classified based on a link type of a victim link, or the set grouping policy may also be classified based on attributes of individual satellites in the same satellite constellation.
Because the interference simulation analysis of the GSO communication system by the NGSO communication system is an essential task for low-orbit communication constellation demonstration, construction and operation links, the system simulation analysis of the large constellation can adopt process level parallel processing in the embodiment of the application. The satellites can be processed in batches from the process level, as the satellites do not need to consider interactions. As an example, considering the CPU processing capacity of 8 cores, the satellites may be divided into 8 groups for processing, and for a constellation of 10000 satellites, the number of satellites required to be processed in each group is 1250. (if there are more server cores, 16/32 cores may be considered, roughly only 630/320 satellites per group).
Therefore, compared with the traditional serial simulation method, in the embodiment of the application, the ground station to be simulated and the satellite to be simulated are grouped, and the software background realizes process-level parallel simulation processing in a multi-thread calling calculation program mode, so that the parallelization design and algorithm optimization are performed on time-consuming tasks such as orbit calculation, visibility calculation and the like, the resources of a computer system are fully utilized, and the simulation capability of the system can be improved after the subsequent resources are improved.
In an optional implementation manner of this embodiment, different grouping manners may be adopted for different link types, that is, a grouping policy is set to classify the link type based on the disturbed link, and at this time, based on the set grouping policy, the ground station to be simulated and the satellite to be simulated are grouped to construct at least two simulation object groups, where a specific implementation process may be as follows:
aiming at uplink interference, a first ground station and each satellite to be simulated form a simulation object group, wherein the first ground station is any ground station to be simulated, one simulation object group comprises one ground station to be simulated and each satellite to be simulated, and the number of the simulation object groups is the number of the ground stations to be simulated;
and aiming at downlink interference, respectively forming simulation object groups with the first ground station and each satellite to be simulated into a corresponding number, wherein one simulation object group comprises one ground station to be simulated and one satellite to be simulated, and the number of the simulation object groups is the product of the number of the satellites to be simulated and the number of the ground stations to be simulated.
It should be noted that, when analyzing the downlink interference of NGSO to GSO satellite, because the interfered ground station is unique, it can be grouped according to the satellite, and parallel computation is performed, and from orbit prediction and visible line analysis, each thread is responsible for data processing of one satellite (Sat 1, sat2, sat3, ..., satN); when the uplink interference of the NGSO network to the GSO satellite is analyzed, the visibility calculation of a large number of ground stations to the NGSO satellite is faced, different tracking strategies need to be considered for comparison and output, ephemeris is merged after parallel calculation, the ground stations can be used as analysis objects for parallel calculation, namely each thread is responsible for the tracking visibility analysis and calculation output of one ground station (Sta 1, sta2, sta3, ... staN), and each ground station traverses each satellite.
In practical application, for uplink interference, the first ground station and each satellite to be simulated may form a simulation object group, each ground station to be simulated may be used as the first ground station, and form a simulation object group with each satellite to be simulated, that is, one ground station to be simulated and each satellite to be simulated form a simulation object group, where the number of the simulation object groups is the number of the ground stations to be simulated. For downlink interference, the first ground station and each satellite to be simulated may form a simulation object group with a corresponding number, that is, one ground station to be simulated and one satellite to be simulated form a simulation object group, each ground station to be simulated may be used as the first ground station, and form a simulation object group with each satellite to be simulated, respectively, where the number of the simulation object group is a product of the number of the satellites to be simulated and the number of the ground stations to be simulated.
For example, fig. 2b is a schematic diagram of a parallel simulation computation flow provided in an embodiment of the present application, and as shown in fig. 2b, the scenario configuration parameters are loaded, where the scenario configuration parameters include the number of NGSO orbits, the number of satellites included in each orbit, ground station parameters, and the like. For uplink interference, the ground station 1 and the satellites 1-N form a simulation object group; the ground station 2 and the satellites 1-N form a simulation object group; 823060, 8230; the ground station N and the satellites 1-N form a simulation object group. And performing visibility simulation on each simulation object group in parallel through a corresponding thread, outputting a visibility simulation result, performing visibility analysis on the visibility simulation result of each simulation object group in parallel according to a set analysis strategy, determining relevant parameters of a visible area of a satellite corresponding to the ground station in each simulation object group, and performing visibility analysis on each simulation object group in parallel.
For downlink interference, the ground station 1 and the satellite 1 form a simulation object group; the ground station 1 and the satellite 2 form a simulation object group; 823060, 8230; the ground station 1 and the satellite N form a simulation object group; 823060, 8230; the ground station N and the satellite 1 form a simulation object group; the ground station N and the satellite 2 form a simulation object group; 823060, 8230; the ground station N and the satellite N form a simulation object group. And performing visibility simulation on each simulation object group in parallel through the corresponding thread, and outputting a visibility simulation result of each simulation object group.
In addition, in actual implementation, the grouping policy may be set to be a grouping rule other than the grouping based on the link type of the disturbed link, for example, the grouping may be performed based on the satellite and may be performed according to information such as the satellite controller, the orbit type, the frequency characteristic, and the like; grouping can also be based on ground stations, grouping by serving satellites, distribution areas, and the like. In addition, various attributes of the objects in the group can be defined in batch through grouping, object management is facilitated, and simulation efficiency is improved.
In the embodiment of the application, the ground station to be simulated and the satellite to be simulated can be subjected to custom grouping, and the software background realizes process-level parallel simulation processing by adopting a multi-thread calling calculation program mode, so that the relatively time-consuming tasks such as track calculation, visibility calculation and the like are subjected to parallelization design and algorithm optimization, the resources of a computer system are fully utilized, the simulation capability of the system can be improved after the subsequent resources are improved, and the requirement on the upgrading potential of the system is met.
Step 106: and selecting a target satellite and a target ground station from the target simulation object group, performing visibility simulation on the target satellite and the target ground station based on the simulation time point set, and determining a visibility simulation result of the target satellite for the target ground station.
The target simulation object group is any one of the at least two constructed simulation objects, namely, each constructed simulation object group can be used as a target simulation object group for subsequent visibility simulation; the target satellite is any one simulation object in the target simulation object group, and the target ground station is any one ground station in the target simulation object group.
It should be noted that, for each simulation object group, visibility simulation may be performed on a target ground station and a target satellite therein, that is, a single station performs visibility simulation on a single satellite, after the visibility simulation of the target ground station and the target satellite is completed, other satellites and the target ground station may be selected to perform visibility simulation until the simulation of each satellite in the target simulation object group on the target ground station is completed, if there is no other ground station, the visibility simulation of the target simulation object group is completed, and if there is another ground station, another ground station is selected as the target ground station, and the above procedure is continued to perform visibility simulation.
In an optional implementation manner of this embodiment, visibility simulation may be performed in combination with the current visibility identifier and the current simulation time point, that is, visibility simulation is performed on the target satellite and the target ground station based on the simulation time point set, and a visibility simulation result of the target satellite for the target ground station is determined, which may specifically be implemented as follows:
selecting a current simulation time point from the simulation time point set, and determining a first satellite elevation angle of the target satellite and the target ground station aiming at the current simulation time point under the condition that an end mark does not exist at the current simulation time point;
and acquiring a current visibility identifier, performing visibility simulation based on the first satellite elevation angle and the current visibility identifier, updating the current simulation time point, and returning to execute the operation step of determining the target satellite and the first satellite elevation angle of the target ground station aiming at the current simulation time point until the current simulation time point has an end identifier.
It should be noted that the ending identifier is used to indicate that the current simulation time point is the last simulation time point in the set of simulation time points, that is, the simulation of the round is ended when the preset simulation duration is reached. Secondly, when the sight line is above the local horizontal plane of the earth, in the vertical plane where the sight line is located, the angle formed by the sight line and the horizontal plane is called an elevation angle, the satellite elevation angle is the angle formed by the connecting line between the ground station and the satellite and the horizontal plane, and the first satellite elevation angle is the angle formed by the connecting line between the position of the target satellite and the target ground station and the horizontal line at the current simulation time point. In addition, the visibility flag refers to whether the target satellite is in the visible area of the target ground station (i.e. the arc segment of the satellite visible by the target ground station in the satellite motion orbit), and the current visibility flag is a flag used for marking during the visibility simulation based on the last simulation time point for performing the visibility simulation, and is used for indicating whether the target satellite is in the visible area of the target ground station at the last simulation time point.
In practical applications, a minimum simulation time point (i.e., a first simulation time point) may be initially selected from the set of simulation time points as a current simulation time point, the current simulation time point has no end identifier, for the current simulation time point, a first satellite elevation angle of a target satellite and a target ground station may be determined, and a current visibility identifier may be obtained, where the first satellite elevation angle may indicate whether the target satellite is in a visible area of the target ground station at the current simulation time point, and the current visibility identifier may indicate whether the target satellite is in a visible area of the target ground station at a previous simulation time point for performing visibility simulation, so that visibility simulation may be performed based on the first satellite elevation angle and the current visibility identifier, and the current simulation time point may be updated, and whether the updated current simulation time point has an end identifier, and if the updated current simulation time point does not have an end identifier, the first satellite elevation angles of the target satellite and the target ground station may be determined continuously for the current simulation time point, and simulation may be continued until the current simulation time point has an end identifier at the current simulation time point.
In the embodiment of the application, when the current visibility identifier indicates the last simulation time point for performing visibility simulation, whether the target satellite is in the visible area of the target ground station or not can be determined, and based on the elevation angle of the first satellite, whether the target satellite is in the visible area of the target ground station or not can be determined when the current simulation time point is, so that the change of the area where the target satellite is located from the last simulation time point for performing visibility simulation to the current simulation time point can be determined by combining the elevation angle of the first satellite and the current visibility identifier, thereby determining the relevant parameters of the target satellite entering the visible area and leaving the visible area, and realizing the visibility simulation.
In an optional implementation manner of this embodiment, before determining, for the current simulation time point, a first satellite elevation angle of the target satellite and the target ground station, the method further includes:
determining whether the current simulation time point is the last simulation time point in the simulation time point set;
and if the current simulation time point is the last simulation time point, setting an ending mark for the current simulation time point.
In practical application, under the condition that the end mark does not exist at the current simulation time point, whether the current simulation time point is the last simulation time point in the simulation time point set or not can be further determined, if the current simulation time point is the last simulation time point, the operation step of determining the first satellite elevation angles of the target satellite and the target ground station when the current simulation time point is calculated is shown, the simulation of the round is finished, so that the end mark can be set for the current simulation time point, then the operation step of determining the first satellite elevation angles of the target satellite and the target ground station aiming at the current simulation time point is executed, the visibility simulation calculation is carried out on the last simulation time point in the simulation time point set, after the calculation is finished, the current simulation time point is the last simulation time point in the simulation time point set, so that the current simulation time point is the same before and after the current simulation time point is updated, and the simulation can be finished at this time because the end mark exists at the current simulation time point. If the current simulation time point is not the last simulation time point, the operation step of determining the elevation angle of the target satellite and the first satellite of the target ground station aiming at the current simulation time point can be directly executed, and the visibility simulation is carried out on the current simulation time point.
It should be noted that the simulation is controlled to be ended by adding the end identifier to the last simulation time point in the simulation time point set, the simulation time point does not need to be monitored in real time, and the operation is simple.
In an optional implementation manner of this embodiment, performing visibility simulation based on the first satellite elevation angle and the current visibility flag, and updating the current simulation time point may specifically be as follows:
under the condition that the current visibility mark is visible, determining whether the current simulation time point leaves a visible area or not based on the first satellite elevation angle to obtain a first determination result, performing visibility simulation according to the first determination result, and updating the current simulation time point;
and under the condition that the current visibility mark is invisible, determining whether the current simulation time point enters a visible area or not based on the first satellite elevation angle, obtaining a second determination result, performing visibility simulation according to the second determination result, and updating the current simulation time point.
It should be noted that, when the current visibility flag is visible and a previous simulation time point for performing visibility simulation is described, the target satellite is located in a visible area of the target ground station, at this time, whether the target satellite leaves the visible area of the target ground station at the current simulation time point may be determined based on the first satellite elevation angle, so as to obtain a first determination result, where the first determination result may indicate whether the target satellite moves from the visible area to a non-visible area from the previous simulation time point for performing visibility simulation to the current simulation time point, so that visibility simulation may be performed according to the first determination result, and the current simulation time point is updated, so as to determine related parameters of the target satellite leaving the visible area of the target ground station.
In practical application, when determining whether the current simulation time point leaves the visible region based on the first satellite elevation angle, it may be determined whether the first satellite elevation angle is lower than the lowest tracking elevation angle, and if so, it indicates that the current simulation time point leaves the visible region; if not, the indication is that the visible area is not left.
In addition, under the condition that the current visibility flag is invisible, when the previous simulation time point for performing visibility simulation is described, the target satellite is not located in the visible area of the target ground station, at this time, whether the target satellite enters the visible area of the target ground station at the current simulation time point can be determined based on the elevation angle of the first satellite, a second determination result is obtained, and the second determination result can indicate whether the target satellite moves from the invisible area to the visible area from the previous simulation time point for performing visibility simulation to the current simulation time point, so that visibility simulation can be performed according to the second determination result, and the current simulation time point is updated, so as to determine relevant parameters of the target satellite entering the visible area of the target ground station.
In practical application, when determining whether the current simulation time point enters the visible region based on the first satellite elevation angle, determining whether the first satellite elevation angle is higher than the lowest tracking elevation angle, and if so, indicating that the current simulation time point enters the visible region; if not, it indicates that the visible region is not entered.
In the embodiment of the application, the change of the region where the target satellite is located from the last simulation time point for performing visibility simulation to the current simulation time point can be determined by combining the elevation angle of the first satellite and the current visibility identifier, so that the relevant parameters of the target satellite entering the visible region and leaving the visible region are determined, and the visibility simulation is realized.
It should be noted that, when performing visibility simulation for a target satellite and a target ground station, visibility simulation may be performed in combination with the first satellite elevation angle and the current visibility flag, and simulation calculation may not be performed for each simulation time point in the simulation time point set, but when the first satellite elevation angle and the current visibility flag satisfy a set condition, a set number of simulation time points after the current simulation time in the simulation time point set are skipped, and visibility simulation is continued for the simulation time points after the set number of simulation time points.
In an optional implementation manner of this embodiment, performing visibility simulation according to the first determination result, and updating the current simulation time point may specifically be implemented as follows:
if the first determination result is that the current simulation time point leaves the visible region, determining the time of leaving the visible region based on the current simulation time point, updating the current visibility mark to be invisible, and selecting the next simulation time point from the set of simulation time points to update the current simulation time point based on the set simulation time span;
and if the first determination result is that the satellite does not leave the visible area, performing visibility simulation based on satellite elevation angles corresponding to a plurality of simulation time points with continuous set values, and updating the current simulation time point.
In practical application, if the first determination result is that the target satellite leaves the visible region, it indicates that the target satellite moves from the visible region to the non-visible region from the last simulation time point for performing the visibility simulation to the current simulation time point, that is, the target satellite has left the visible region of the target ground station at the current simulation time point, and the time of leaving the visible region is between the last simulation time point for performing the visibility simulation and the current simulation time point. Since the current simulation time point leaves the visible area and a certain time is still available until the current simulation time point enters the visible area next time, the set condition is met at the moment, the visibility simulation calculation is not needed to be carried out on the simulation time points one by one, at the moment, the next simulation time point is selected from the simulation time point set to update the current simulation time point directly on the basis of the set simulation time span, namely, the set simulation time span is skipped after the current simulation time point in the simulation time point set, and the later simulation time point is used as the updated current simulation time point.
The simulation time span is set as the number of preset simulation time points needing to be skipped, namely, the visibility simulation can be not performed by skipping a plurality of simulation time points at a time. Considering that the satellite only enters the visible area of the target ground station once in each circle, and the change of the elevation angle of the first satellite is changed from large to small, the change characteristic of the elevation angle of the first satellite can be fully considered, and the large-span visible area rapid search, such as 1/3 orbit period, is realized on the LEO orbit, wherein the LEO orbit refers to a low orbit, namely a satellite operation orbit for satellite visibility analysis in the embodiment of the application; that is, the set simulation time span may be set to 1/3 of the orbit period, considering that the time difference between the target satellite entering the visible area of the target ground station twice may be greater than 1/3 of the orbit period.
In specific implementation, when the time of leaving the visible region is determined based on the current simulation time point, that is, the time of leaving the visible region is determined, interpolation may be performed by using the simulation time point that is subjected to the visibility simulation one time above the current simulation time point until the time corresponding to the lowest tracking elevation angle is determined as the time of leaving the visible region.
In addition, if the first determination result is that the satellite does not leave the visible region, it indicates that the target satellite is still located in the visible region from the last simulation time point for performing visibility simulation to the current simulation time point, and at this time, the visibility simulation may be performed based on satellite elevation angles corresponding to consecutive simulation time points in the simulation time point set, and the current simulation time point may be updated, that is, the visibility simulation calculation is performed one by one after the current simulation time point in the simulation time point set.
In the embodiment of the application, a large-span visible area searching method can be adopted to quickly calculate the relevant parameters of the visible area of the target satellite away from the target ground station, a calculation method with a relatively thick time span is adopted, interpolation is subsequently carried out for approximation, and the time of leaving the visible area is determined.
In an optional implementation manner of this embodiment, performing visibility simulation according to the second determination result, and updating the current simulation time point may specifically be implemented as follows:
if the second determination result is that the current simulation time point enters the visible area, determining the time for entering the visible area based on the current simulation time point, updating the current visibility mark to be visible, and selecting the next simulation time point of the current simulation time point from the simulation time point set to update the current simulation time point;
and if the second determination result is that the satellite does not enter the visible region, performing visibility simulation based on satellite elevation angles corresponding to a plurality of simulation time points with continuous set values, and updating the current simulation time point.
In practical application, if the second determination result is that the satellite enters the visible region, it indicates that the target satellite moves from the previous simulation time point for performing visibility simulation to the current simulation time point, the target satellite enters the visible region from the invisible region, that is, the target satellite already enters the visible region of the target ground station at the current simulation time point, and the time for entering the visible region is between the previous simulation time point for performing visibility simulation and the current simulation time point.
If the second determination result is that the satellite does not enter the visible region, it indicates that the target satellite is still located in the invisible region from the last simulation time point for performing the visibility simulation to the current simulation time point, and at this time, the visibility simulation may be performed based on satellite elevation angles corresponding to a set number of continuous simulation time points in the simulation time point set, and the current simulation time point is updated, that is, the visibility simulation calculation is performed one by one after the current simulation time point in the simulation time point set.
In specific implementation, when the time of entering the visible region is determined based on the current simulation time point, interpolation may be performed by using the simulation time point for performing visibility simulation upward from the current simulation time point until the time corresponding to the lowest tracking elevation is determined as the time of entering the visible region.
In the embodiment of the application, a large-span visible area searching method can be adopted to quickly calculate the relevant parameters of the target satellite entering the visible area of the target ground station, a calculation method with a relatively thick time span is adopted, interpolation is subsequently carried out for approximation, and the time of entering the visible area is determined.
In an optional implementation manner of this embodiment, the visibility simulation is performed based on satellite elevation angles corresponding to the simulation time points with the continuously set values, and the current simulation time point is updated, which may be specifically implemented as follows:
determining whether the current simulation time point is over-top or not based on continuous set numerical value simulation time points;
if the current simulation time point is not over the top, acquiring a next simulation time point of the current simulation time point from the simulation time point set and updating the current simulation time point;
and if the current simulation time point is over the top, performing visibility simulation based on the first satellite elevation angle, the current visibility mark and the lowest tracking elevation angle, and updating the current simulation time point.
It should be noted that, based on a number of simulation time points that are continuously set, it may be determined whether the current simulation time point is over-top, that is, whether the elevation angle of the first satellite of the target satellite and the target ground station at the current simulation time point is maximum. During specific implementation, the set value can be 3, the elevation angles of the target satellite and the second satellite of the target ground station at the time of obtaining the simulation time point before the current simulation time point are obtained, the elevation angles of the target satellite and the third satellite of the target ground station at the time of obtaining the simulation time point after the current simulation time point are calculated, if the elevation angle of the first satellite is larger than the elevation angle of the second satellite and larger than the elevation angle of the third satellite, the elevation angle of the first satellite of the target satellite and the target ground station at the current simulation time point is the largest, and the current simulation time point is over the top; if the first satellite elevation angle is not greater than the second satellite elevation angle or the third satellite elevation angle, the first satellite elevation angles of the target satellite and the target ground station at the current simulation time point are not the maximum, and the current simulation time point does not exceed the top.
In practical application, if the current simulation time point is not over the top, acquiring a next simulation time point of the current simulation time point from the simulation time point set as an updated current simulation time point, and continuing to perform visibility simulation on the next simulation time point; if the current simulation time point is over the top, the current simulation time point is indicated, the first satellite elevation angle between the target satellite and the target ground station is the maximum, and at this time, whether the maximum first satellite elevation angle is located in the visible area or not can be further judged based on the first satellite elevation angle, the current visibility identifier and the lowest tracking elevation angle, so that visibility simulation is carried out, and the current simulation time point is updated.
In the embodiment of the application, whether the current simulation time point is over-top or not can be determined based on the continuous set numerical simulation time points, if not, the next simulation time point is continuously obtained, and the visibility simulation is continuously carried out; if the satellite elevation angle exceeds the top, whether the maximum first satellite elevation angle is located in the visible area is further judged based on the first satellite elevation angle, the current visibility mark and the lowest tracking elevation angle, and the situation that the current satellite elevation angle is maximum but not located in the visible area of the target ground station is avoided, so that misjudgment is avoided, and the accuracy of visibility simulation is improved.
In an optional implementation manner of this embodiment, performing visibility simulation based on the first satellite elevation angle, the current visibility flag, and the lowest tracking elevation angle, and updating the current simulation time point may specifically be as follows:
determining whether the first satellite elevation angle exceeds a lowest tracking elevation angle;
if the lowest tracking elevation angle is not exceeded, selecting a next simulation time point from the set of simulation time points to update the current simulation time point based on a set simulation time span;
and if the lowest tracking elevation angle is exceeded, performing visibility simulation based on the first satellite elevation angle and the current visibility identification, and updating the current simulation time point.
It should be noted that, it may be determined whether the first satellite elevation angle exceeds the lowest tracking elevation angle, and if the first satellite elevation angle does not exceed the lowest tracking elevation angle, it is determined that the current satellite elevation angle is the largest, but is not located in the visible region of the target ground station, and a certain time is required to be left from the visible region, so that it may be determined that the set condition is satisfied at this time, and based on the set simulation time span, a next simulation time point is selected from the set of simulation time points to update the current simulation time point, that is, the set simulation time span is skipped after the current simulation time point in the set of simulation time points, and the next simulation time point is taken as the updated current simulation time point. If the current satellite elevation angle exceeds the lowest tracking elevation angle, the current satellite elevation angle is the largest and is located in the visible area of the target ground station, at this time, whether the satellite elevation angle leaves the visible area or not can be further determined based on the first satellite elevation angle and the current visibility mark, visibility simulation is carried out, and the current simulation time point is updated. Therefore, the condition that the current satellite has the largest elevation angle but is not positioned in the visible area of the target ground station is avoided, so that misjudgment is avoided, and the accuracy of the visibility simulation is improved.
In an optional implementation manner of this embodiment, the visibility simulation is performed based on the first satellite elevation angle and the current visibility flag, and the current simulation time point is updated, where a specific implementation process may be as follows:
under the condition that the current visibility mark is invisible, calculating the time for entering a visible area based on the current simulation time point, setting the current visibility mark to be visible, and acquiring the next simulation time point of the current simulation time point from the simulation time point set to update the current simulation time point;
and under the condition that the current visibility mark is visible, judging whether the current simulation time point is positioned in a visible area, carrying out visibility simulation based on a judgment result, and updating the current simulation time point.
It should be noted that, when the current visibility flag is invisible and a previous simulation time point for performing visibility simulation is described, the target satellite is not located in the visible area of the target ground station, and when the current simulation time point is described, the target satellite is already located in the visible area of the target ground station and the satellite elevation angle is the maximum, at this time, the time for entering the visible area may be calculated based on the current simulation time point, the current visibility flag is set to be visible, then, the next simulation time point of the current simulation time point is obtained from the simulation time point set as the updated current simulation time point, and the visibility simulation for the next simulation time point is continued.
Under the condition that the current visibility mark is visible, when the last simulation time point for performing visibility simulation is described, the target satellite is located in the visible area of the target ground station, and when the current simulation time point is described, the target satellite is still located in the visible area of the target ground station and the satellite elevation angle is the largest, so that whether the current simulation time point is located in the visible area can be further judged, whether the target satellite leaves the visible area of the target ground station or not is determined based on the judgment result when the current simulation time point is determined, visibility simulation is performed, and the current simulation time point is updated.
In an optional implementation manner of this embodiment, the performing visibility simulation based on the determination result, and updating the current simulation time point may specifically be implemented as follows:
if the simulation time point is not located in the visible area, calculating the time of leaving the visible area based on the current simulation time point, setting the current visibility mark as invisible, and acquiring the next simulation time point of the current simulation time point from the simulation time point set to update the current simulation time point;
and if the current simulation time point is located in the visible area, acquiring the next simulation time point of the current simulation time point from the simulation time point set and updating the current simulation time point.
In practical application, if the simulation time point is not located in the visible region, it is indicated that from the last simulation time point for performing visibility simulation to the current simulation time point, the target satellite moves from the visible region to the non-visible region, that is, the target satellite has left the visible region of the target ground station at the current simulation time point, the time of leaving the visible region is between the last simulation time point for performing visibility simulation and the current simulation time point, at this time, the time of leaving the visible region may be determined based on the current simulation time point, and the current visibility flag is updated to be invisible, so as to indicate that the target satellite leaves the visible region of the target ground station, and the next simulation time point of the current simulation time point is obtained from the simulation time point set as the updated current simulation time point, so as to continue to perform visibility simulation on the next simulation time point.
In addition, if the current simulation time point is located in the visible region, it indicates that the target satellite is still located in the visible region from the last simulation time point for performing the visibility simulation to the current simulation time point, and at this time, the next simulation time point of the current simulation time point may be directly obtained from the simulation time point set as the updated current simulation time point, and the visibility simulation is continuously performed on the next simulation time point.
It should be noted that, in the visibility simulation process, after the time of entering the visible region and the time of leaving the visible region are obtained through calculation, relevant parameters of the visible region, such as the relative distance between the satellite and the ground station, the distance change rate, the azimuth angle, the pitch angle and the like, can be determined based on the time of entering the visible region and the time of leaving the visible region, and based on the parameters and in combination with the link attenuation, interference evaluation can be performed on various satellite communication systems and link-level indexes, so that interference simulation of the NGSO on the GSO is realized.
In practical implementation, because the geometric relationship different from the relative stationarity of the GSO satellite is different from the problem that the visibility analysis of the NGSO satellite has a large quantity and high dynamic, in order to improve the visibility simulation efficiency, the orbit prediction and the visibility analysis are rapidly carried out by adopting a parallel computing method; and when the visible areas of the ground station and the low-orbit satellite are calculated, the visibility is calculated in a large-span quick searching mode, and compared with a calculation method for calculating the cut traditional visible areas point by point, the calculation efficiency is improved by more than 2 times.
In addition, the grouping strategy and the visibility simulation strategy of each simulation time point can be customized in the embodiment of the application, the simulation task does not need to adopt a fixed flow mode, and each factor of a simulation scene does not need to be completely modeled, so that the complexity of visibility simulation is reduced, and the flexibility is improved; and the simulation file of each simulation time point can be stored, the visibility simulation process is controllable, and the specific problems can be quickly positioned when the problems of setting errors, accidental quitting and the like of the simulation scene occur.
According to the satellite visibility simulation method, a simulation time point set is generated according to a preset simulation time length and a preset simulation step; grouping ground stations to be simulated and satellites to be simulated based on a set grouping strategy to construct at least two simulation object groups, wherein the at least two simulation object groups are subjected to visibility simulation in parallel, and each simulation object group comprises at least one ground station to be simulated and at least one satellite to be simulated; selecting a target satellite and a target ground station from a target simulation object group, performing visibility simulation on the target satellite and the target ground station based on the simulation time point set, and determining a visibility simulation result of the target satellite for the target ground station, wherein the target simulation object group is any one of at least two constructed simulation objects, the target satellite is any one of the target simulation object group, and the target ground station is any one of the target simulation object group. Under the condition, a grouping strategy can be customized, the ground station to be simulated and the satellite to be simulated are grouped, at least two simulation object groups are constructed, visibility simulation is performed on each at least two simulation object groups in parallel, parallelization processing is adopted, computer resources are utilized to the maximum extent, visibility simulation is performed quickly, and the efficiency of visibility simulation is improved greatly while the simulation precision is not reduced.
Fig. 3 shows a processing flow chart of a visibility simulation method for a target satellite and a target ground station according to an embodiment of the present application, which specifically includes:
step 1: and generating a simulation time point set according to the preset simulation duration and the preset simulation step.
And 2, step: and selecting a first simulation time point from the simulation time point set as a current simulation time point.
And step 3: and (4) determining whether the current simulation time point has an ending mark, if so, ending the simulation, and if not, executing the step (4).
And 4, step 4: determining whether the current simulation time point is the last simulation time point in the simulation time point set, if so, setting an ending identifier for the current simulation time point, and executing the step 5; if not, directly executing the step 5.
And 5: at a current simulation time point, a first satellite elevation angle of the target satellite and the target ground station is determined.
Step 6: acquiring a current visibility mark, and executing the step 7 if the current visibility mark is visible; if the current visibility flag is not visible, go to step 8.
And 7: determining whether the current simulation time point leaves the visible area or not, if so, calculating the time of leaving the visible area based on the current simulation time point, setting the current visibility identifier as invisible, skipping a set number of simulation time points after the current simulation time point in the simulation time point set, determining the next simulation time point, taking the next simulation time point as the current simulation time point to update the current simulation time point, and returning to the step 3; if the current simulation time point does not leave the visible area, step 9 is executed.
And step 8: determining whether the current simulation time point enters a visible area or not, if so, calculating the time for entering the visible area based on the current simulation time point, setting the current visibility identifier to be visible, acquiring the next simulation time point of the current simulation time point from the simulation time point set, taking the next simulation time point as the current simulation time point, namely updating the current simulation time point based on the next simulation time point, and returning to the step 3; if the current simulation time point does not enter the visible area, step 9 is executed.
And step 9: determining a second satellite elevation angle of a simulation time point before the current simulation time point and a third satellite elevation angle of a simulation time point after the current simulation time point, based on the first satellite elevation angle, the second satellite elevation angle and the third satellite elevation angle, namely, storing continuous 3 satellite elevation angles, determining whether the current simulation time point is over-vertex based on the continuous 3 satellite elevation angles, if not, acquiring a next simulation time point of the current simulation time point from a simulation time point set, taking the next simulation time point as the current simulation time point, namely, updating the current simulation time point based on the next simulation time point, and returning to the step 3; if so, go to step 10.
Step 10: determining whether the elevation angle of the first satellite of the current simulation time point exceeds the lowest tracking elevation angle, if not, skipping a set number of simulation time points behind the current simulation time point in the simulation time point set, determining the next simulation time point, taking the next simulation time point as the current simulation time point to update the current simulation time point, and returning to the step 3; if the lowest tracking elevation angle is exceeded, step 11 is performed.
Step 11: determining whether the current visibility flag is invisible, if the current visibility flag is invisible, executing step 12; if the current visibility flag is visible, step 13 is executed.
Step 12: calculating the inbound time based on the current simulation time point, setting the current visibility identifier to be visible, acquiring the next simulation time point of the current simulation time point from the simulation time point set, taking the next simulation time point as the current simulation time point, namely updating the current simulation time point based on the next simulation time point, and returning to the step 3.
Step 13: if the current visibility mark is visible, determining whether the current simulation time point leaves the visible area, if so, calculating the time of leaving the visible area based on the current simulation time point, setting the current visibility mark as invisible, acquiring the next simulation time point of the current simulation time point from the simulation time point set, taking the next simulation time point as the current simulation time point, namely updating the current simulation time point based on the next simulation time point, and returning to the step 3; and if the current simulation time point does not leave the visible area, directly acquiring the next simulation time point of the current simulation time point from the simulation time point set, taking the next simulation time point as the current simulation time point, namely updating the current simulation time point based on the next simulation time point, and returning to the step 3.
According to the satellite visibility simulation method, a simulation time point set is generated according to preset simulation duration and preset simulation steps; grouping ground stations to be simulated and satellites to be simulated based on a set grouping strategy to construct at least two simulation object groups, wherein the at least two simulation object groups perform visibility simulation in parallel, and each simulation object group comprises at least one ground station to be simulated and at least one satellite to be simulated; selecting a target satellite and a target ground station from a target simulation object group, performing visibility simulation on the target satellite and the target ground station based on the simulation time point set, and determining a visibility simulation result of the target satellite for the target ground station, wherein the target simulation object group is any one of at least two constructed simulation objects, the target satellite is any one of the target simulation object group, and the target ground station is any one of the target simulation object group. Under the condition, a grouping strategy can be customized, the ground station to be simulated and the satellite to be simulated are grouped, at least two simulation object groups are constructed, visibility simulation is performed on each at least two simulation object groups in parallel, parallelization processing is adopted, computer resources are utilized to the maximum extent, visibility simulation is performed quickly, and the efficiency of visibility simulation is improved greatly while the simulation precision is not reduced. And when the visible areas of the ground station and the NGSO satellite are calculated, the visibility is calculated in a large-span quick searching mode, and the simulation efficiency is greatly improved.
Corresponding to the above method embodiment, the present application further provides an embodiment of a satellite visibility simulation apparatus, and fig. 4 shows a schematic structural diagram of the satellite visibility simulation apparatus provided in an embodiment of the present application. As shown in fig. 4, the apparatus includes:
a generating module 402 configured to generate a set of simulation time points according to a preset simulation duration and a preset simulation step;
a grouping module 404 configured to group the ground station to be simulated and the satellite to be simulated based on a set grouping policy, and construct at least two simulation object groups, wherein the at least two simulation object groups perform visibility simulation in parallel, and each simulation object group includes at least one ground station to be simulated and at least one satellite to be simulated;
a simulation module 406 configured to select a target satellite and a target ground station from a target simulation object group, perform visibility simulation on the target satellite and the target ground station based on the set of simulation time points, and determine a visibility simulation result of the target satellite for the target ground station, where the target simulation object group is any one of at least two constructed simulation objects, the target satellite is any one of the target simulation objects, and the target ground station is any one of the target simulation objects.
Optionally, the grouping policy is set to be classified based on a link type of a disturbed link; a grouping module 404 further configured to:
aiming at uplink interference, a first ground station and each satellite to be simulated form a simulation object group, wherein the first ground station is any ground station to be simulated, one simulation object group comprises one ground station to be simulated and each satellite to be simulated, and the number of the simulation object groups is the number of the ground stations to be simulated;
and aiming at downlink interference, respectively forming simulation object groups with corresponding numbers by the first ground station and each satellite to be simulated, wherein one simulation object group comprises one ground station to be simulated and one satellite to be simulated, and the number of the simulation object groups is the product of the number of the satellites to be simulated and the number of the ground stations to be simulated.
Optionally, the simulation module 406 is further configured to:
selecting a current simulation time point from the simulation time point set, and determining a first satellite elevation angle of the target satellite and the target ground station aiming at the current simulation time point under the condition that an end mark does not exist at the current simulation time point;
and acquiring a current visibility identifier, performing visibility simulation based on the first satellite elevation angle and the current visibility identifier, updating the current simulation time point, and returning to execute the operation step of determining the target satellite and the first satellite elevation angle of the target ground station aiming at the current simulation time point until the current simulation time point has an end identifier.
Optionally, the simulation module 406 is further configured to:
under the condition that the current visibility mark is visible, determining whether the current simulation time point leaves a visible area or not based on the first satellite elevation angle to obtain a first determination result, performing visibility simulation according to the first determination result, and updating the current simulation time point;
and under the condition that the current visibility mark is invisible, determining whether the current simulation time point enters a visible area or not based on the first satellite elevation angle, obtaining a second determination result, performing visibility simulation according to the second determination result, and updating the current simulation time point.
Optionally, the simulation module 406 is further configured to:
if the first determination result is that the current simulation time point leaves the visible region, determining the time of leaving the visible region based on the current simulation time point, updating the current visibility mark to be invisible, and selecting the next simulation time point from the set of simulation time points to update the current simulation time point based on the set simulation time span;
and if the first determination result is that the satellite does not leave the visible area, performing visibility simulation based on satellite elevation angles corresponding to a plurality of simulation time points with continuous set values, and updating the current simulation time point.
Optionally, the simulation module 406 is further configured to:
if the second determination result is that the current simulation time point enters the visible area, determining the time for entering the visible area based on the current simulation time point, updating the current visibility mark to be visible, and selecting the next simulation time point of the current simulation time point from the simulation time point set to update the current simulation time point;
and if the second determination result is that the satellite does not enter the visible area, performing visibility simulation based on satellite elevation angles corresponding to the simulation time points with continuous set values, and updating the current simulation time point.
Optionally, the simulation module 406 is further configured to:
the performing visibility simulation based on satellite elevation angles corresponding to the simulation time points with continuous set values and updating the current simulation time point comprises:
determining whether the current simulation time point is over-top or not based on continuous simulation time points with set numerical values;
if the current simulation time point is not over-top, acquiring a next simulation time point of the current simulation time point from the simulation time point set to update the current simulation time point;
and if the current simulation time point is over the top, performing visibility simulation based on the first satellite elevation angle, the current visibility mark and the lowest tracking elevation angle, and updating the current simulation time point.
Optionally, the simulation module 406 is further configured to:
the performing visibility simulation based on the first satellite elevation, the current visibility flag, and a lowest tracking elevation, and updating the current simulation time point comprises:
determining whether the first satellite elevation angle exceeds a lowest tracking elevation angle;
if the lowest tracking elevation angle is not exceeded, selecting a next simulation time point from the set of simulation time points to update the current simulation time point based on a set simulation time span;
and if the lowest tracking elevation angle is exceeded, performing visibility simulation based on the first satellite elevation angle and the current visibility identification, and updating the current simulation time point.
Optionally, the simulation module 406 is further configured to:
under the condition that the current visibility identification is invisible, calculating time for entering a visible region based on the current simulation time point, setting the current visibility identification to be visible, and acquiring the next simulation time point of the current simulation time point from the simulation time point set to update the current simulation time point;
and under the condition that the current visibility mark is visible, judging whether the current simulation time point is positioned in a visible area, carrying out visibility simulation based on a judgment result, and updating the current simulation time point.
Optionally, the simulation module 406 is further configured to:
the performing visibility simulation based on the determination result and updating the current simulation time point includes:
if the simulation time point is not located in the visible area, calculating the time of leaving the visible area based on the current simulation time point, setting the current visibility mark as invisible, and acquiring the next simulation time point of the current simulation time point from the simulation time point set to update the current simulation time point;
and if the current simulation time point is located in the visible area, acquiring the next simulation time point of the current simulation time point from the simulation time point set and updating the current simulation time point.
Optionally, the simulation module 406 is further configured to:
determining whether the current simulation time point is the last simulation time point in the simulation time point set;
and if the current simulation time point is the last simulation time point, setting an ending mark for the current simulation time point.
The satellite visibility simulation device provided by the application generates a simulation time point set according to a preset simulation duration and a preset simulation step; grouping ground stations to be simulated and satellites to be simulated based on a set grouping strategy to construct at least two simulation object groups, wherein the at least two simulation object groups are subjected to visibility simulation in parallel, and each simulation object group comprises at least one ground station to be simulated and at least one satellite to be simulated; selecting a target satellite and a target ground station from a target simulation object group, performing visibility simulation on the target satellite and the target ground station based on the simulation time point set, and determining a visibility simulation result of the target satellite for the target ground station, wherein the target simulation object group is any one of at least two constructed simulation objects, the target satellite is any one of the target simulation object groups, and the target ground station is any one of the target simulation object groups. Under the condition, a grouping strategy can be customized, the ground station to be simulated and the satellite to be simulated are grouped, at least two simulation object groups are constructed, visibility simulation is performed on each at least two simulation object groups in parallel, parallelization processing is adopted, computer resources are utilized to the maximum extent, visibility simulation is performed quickly, and the efficiency of visibility simulation is improved greatly while the simulation precision is not reduced.
The foregoing is a schematic diagram of a satellite visibility simulation apparatus according to this embodiment. It should be noted that the technical solution of the satellite visibility simulation apparatus and the technical solution of the satellite visibility simulation method described above belong to the same concept, and details that are not described in detail in the technical solution of the satellite visibility simulation apparatus can be referred to the description of the technical solution of the satellite visibility simulation method described above.
Fig. 5 shows a block diagram of a computing device according to an embodiment of the present application. The components of the computing device 500 include, but are not limited to, a memory 510 and a processor 520. Processor 520 is coupled to memory 510 via bus 530, and database 550 is used to store data.
Computing device 500 also includes access device 540, access device 540 enabling computing device 500 to communicate via one or more networks 540. Examples of such networks include a Public Switched Telephone Network (PSTN), a Local Area Network (LAN), a Wide Area Network (WAN), a Personal Area Network (PAN), or a combination of communication networks such as the internet. The Access device 540 may include one or more of any type of network interface (e.g., a Network Interface Controller (NIC)) whether wired or wireless, such as an IEEE802.11 Wireless Local Area Network (WLAN) wireless interface, a worldwide interoperability for microwave Access (Wi-MAX) interface, an ethernet interface, a Universal Serial Bus (USB) interface, a cellular network interface, a bluetooth interface, a Near Field Communication (NFC) interface, and so forth.
In one embodiment of the application, the above-described components of computing device 500 and other components not shown in FIG. 5 may also be connected to each other, such as by a bus. It should be understood that the block diagram of the computing device architecture shown in FIG. 5 is for purposes of example only and is not limiting as to the scope of the present application. Those skilled in the art may add or replace other components as desired.
Computing device 500 may be any type of stationary or mobile computing device, including a mobile computer or mobile computing device (e.g., tablet computer, personal digital assistant, laptop computer, notebook computer, netbook, etc.) or other type of mobile device, or a stationary computing device such as a desktop computer or PC. Computing device 500 may also be a mobile or stationary server.
Wherein the processor 520 is configured to execute the following computer-executable instructions to implement the steps of the satellite visibility simulation method of any of the above.
The foregoing is a schematic diagram of a computing device of the present embodiment. It should be noted that the technical solution of the computing device and the technical solution of the satellite visibility simulation method belong to the same concept, and for details that are not described in detail in the technical solution of the computing device, reference may be made to the description of the technical solution of the satellite visibility simulation method.
An embodiment of the present application also provides a computer readable storage medium storing computer instructions, which when executed by a processor, are used for implementing the steps of the satellite visibility simulation method of any one of the above.
The above is an illustrative scheme of a computer-readable storage medium of the present embodiment. It should be noted that the technical solution of the storage medium belongs to the same concept as the technical solution of the satellite visibility simulation method, and details that are not described in detail in the technical solution of the storage medium can be referred to the description of the technical solution of the satellite visibility simulation method.
The foregoing description has been directed to specific embodiments of this application. Other embodiments are within the scope of the following claims. In some cases, the actions or steps recited in the claims may be performed in a different order than in the embodiments and still achieve desirable results. In addition, the processes depicted in the accompanying figures do not necessarily require the particular order shown, or sequential order, to achieve desirable results. In some embodiments, multitasking and parallel processing may also be possible or may be advantageous.
The computer instructions comprise computer program code, which may be in the form of source code, object code, an executable file or some intermediate form, etc. The computer readable medium may include: any entity or device capable of carrying computer program code, recording medium, usb disk, removable hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM), random Access Memory (RAM), electrical carrier wave signals, telecommunications signals, software distribution medium, and the like.
It should be noted that, for the sake of simplicity, the above-mentioned method embodiments are described as a series of acts or combinations, but those skilled in the art should understand that the present application is not limited by the described order of acts, as some steps may be performed in other orders or simultaneously according to the present application. Further, those skilled in the art will appreciate that the embodiments described in this specification are presently considered to be preferred embodiments and that acts and modules are not required in the present application.
In the above embodiments, the descriptions of the respective embodiments have respective emphasis, and for parts that are not described in detail in a certain embodiment, reference may be made to related descriptions of other embodiments.
The preferred embodiments of the present application disclosed above are intended only to aid in the explanation of the application. Alternative embodiments are not exhaustive or limit the invention to the precise embodiments disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the application and its practical applications, to thereby enable others skilled in the art to best understand and utilize the application. The application is limited only by the claims and their full scope and equivalents.

Claims (10)

1. A satellite visibility simulation method, the method comprising:
generating a simulation time point set according to the preset simulation duration and the preset simulation stepping;
grouping ground stations to be simulated and satellites to be simulated based on a set grouping strategy to construct at least two simulation object groups, wherein the at least two simulation object groups perform visibility simulation in parallel, and each simulation object group comprises at least one ground station to be simulated and at least one satellite to be simulated;
selecting a target satellite and a target ground station from a target simulation object group, performing visibility simulation on the target satellite and the target ground station based on the simulation time point set, and determining a visibility simulation result of the target satellite for the target ground station, wherein the target simulation object group is any one of at least two constructed simulation objects, the target satellite is any one of the target simulation object group, and the target ground station is any one of the target simulation object group.
2. The satellite visibility simulation method according to claim 1, wherein the set grouping policy is classified based on a link type of a disturbed link; the method comprises the following steps of grouping a ground station to be simulated and a satellite to be simulated based on a set grouping strategy, and constructing at least two simulation object groups, wherein the steps comprise:
aiming at uplink interference, a first ground station and each satellite to be simulated form a simulation object group, wherein the first ground station is any ground station to be simulated, one simulation object group comprises one ground station to be simulated and each satellite to be simulated, and the number of the simulation object groups is the number of the ground stations to be simulated;
and aiming at downlink interference, respectively forming simulation object groups with corresponding numbers by the first ground station and each satellite to be simulated, wherein one simulation object group comprises one ground station to be simulated and one satellite to be simulated, and the number of the simulation object groups is the product of the number of the satellites to be simulated and the number of the ground stations to be simulated.
3. The satellite visibility simulation method according to claim 1, wherein the performing the visibility simulation on the target satellite and the target ground station based on the set of simulation time points to determine the visibility simulation result of the target satellite for the target ground station comprises:
selecting a current simulation time point from the simulation time point set, and determining a first satellite elevation angle of the target satellite and the target ground station aiming at the current simulation time point under the condition that an end mark does not exist in the current simulation time point;
and acquiring a current visibility identifier, performing visibility simulation based on the first satellite elevation angle and the current visibility identifier, updating the current simulation time point, and returning to execute the operation step of determining the target satellite and the first satellite elevation angle of the target ground station aiming at the current simulation time point until the current simulation time point has an end identifier.
4. The satellite visibility simulation method according to claim 3, wherein the performing the visibility simulation based on the first satellite elevation angle and the current visibility flag and updating the current simulation time point comprises:
under the condition that the current visibility mark is visible, determining whether the current simulation time point leaves a visible area or not based on the first satellite elevation angle, obtaining a first determination result, performing visibility simulation according to the first determination result, and updating the current simulation time point;
under the condition that the current visibility mark is invisible, determining whether the current simulation time point enters a visible area or not based on the first satellite elevation angle, obtaining a second determination result, performing visibility simulation according to the second determination result, and updating the current simulation time point;
wherein, the performing visibility simulation according to the first determination result and updating the current simulation time point includes:
if the first determination result is that the current simulation time point leaves the visible region, determining the time of leaving the visible region based on the current simulation time point, updating the current visibility mark to be invisible, and selecting the next simulation time point from the set of simulation time points to update the current simulation time point based on the set simulation time span;
if the first determination result is that the satellite does not leave the visible area, performing visibility simulation based on satellite elevation angles corresponding to a plurality of simulation time points with continuous set values, and updating the current simulation time point;
wherein, the performing visibility simulation according to the second determination result and updating the current simulation time point includes:
if the second determination result is that the current simulation time point enters the visible area, determining the time for entering the visible area based on the current simulation time point, updating the current visibility identification to be visible, and selecting the next simulation time point of the current simulation time point from the simulation time point set to update the current simulation time point;
and if the second determination result is that the satellite does not enter the visible area, performing visibility simulation based on satellite elevation angles corresponding to the simulation time points with continuous set values, and updating the current simulation time point.
5. The satellite visibility simulation method according to claim 4, wherein the performing visibility simulation based on satellite elevation angles corresponding to a set number of successive simulation time points and updating the current simulation time point includes:
determining whether the current simulation time point is over-top or not based on continuous set numerical value simulation time points;
if the current simulation time point is not over-top, acquiring a next simulation time point of the current simulation time point from the simulation time point set to update the current simulation time point;
if the current simulation time point is over the top, performing visibility simulation based on the first satellite elevation, the current visibility mark and the lowest tracking elevation, and updating the current simulation time point; wherein the content of the first and second substances,
the performing visibility simulation based on the first satellite elevation, the current visibility flag, and a lowest tracking elevation, and updating the current simulation time point comprises:
determining whether the first satellite elevation angle exceeds a lowest tracking elevation angle;
if the lowest tracking elevation angle is not exceeded, selecting a next simulation time point from the set of simulation time points to update the current simulation time point based on a set simulation time span;
if the lowest tracking elevation angle is exceeded, performing visibility simulation based on the first satellite elevation angle and the current visibility identification, and updating the current simulation time point; wherein the content of the first and second substances,
the performing visibility simulation based on the first satellite elevation angle and the current visibility flag, and updating the current simulation time point includes:
under the condition that the current visibility mark is invisible, calculating the time for entering a visible area based on the current simulation time point, setting the current visibility mark to be visible, and acquiring the next simulation time point of the current simulation time point from the simulation time point set to update the current simulation time point;
and under the condition that the current visibility mark is visible, judging whether the current simulation time point is positioned in a visible area, carrying out visibility simulation based on a judgment result, and updating the current simulation time point.
6. The satellite visibility simulation method according to claim 5, wherein the performing the visibility simulation based on the determination result and updating the current simulation time point includes:
if the simulation time point is not located in the visible area, calculating the time of leaving the visible area based on the current simulation time point, setting the current visibility mark as invisible, and acquiring the next simulation time point of the current simulation time point from the simulation time point set to update the current simulation time point;
and if the current simulation time point is located in the visible area, acquiring the next simulation time point of the current simulation time point from the simulation time point set and updating the current simulation time point.
7. The satellite visibility simulation method of claim 3, wherein the determining a first satellite elevation angle for the target satellite and the target ground station for the current simulation time point is preceded by:
determining whether the current simulation time point is the last simulation time point in the simulation time point set;
and if the current simulation time point is the last simulation time point, setting an ending mark for the current simulation time point.
8. A satellite visibility simulation apparatus, the apparatus comprising:
the generation module is configured to generate a simulation time point set according to a preset simulation duration and a preset simulation step;
the system comprises a grouping module, a simulation module and a simulation module, wherein the grouping module is configured to group a ground station to be simulated and a satellite to be simulated based on a set grouping strategy and construct at least two simulation object groups, the at least two simulation object groups perform visibility simulation in parallel, and each simulation object group comprises at least one ground station to be simulated and at least one satellite to be simulated;
the simulation module is configured to select a target satellite and a target ground station from a target simulation object group, perform visibility simulation on the target satellite and the target ground station based on the simulation time point set, and determine a visibility simulation result of the target satellite for the target ground station, where the target simulation object group is any one of at least two constructed simulation objects, the target satellite is any one of the target simulation object groups, and the target ground station is any one of the target simulation object groups.
9. A computing device, comprising:
a memory and a processor;
the memory is configured to store computer-executable instructions, and the processor is configured to execute the computer-executable instructions to implement the steps of the satellite visibility simulation method of any of the preceding claims 1-7.
10. A computer readable storage medium storing computer instructions which, when executed by a processor, carry out the steps of the satellite visibility simulation method of any one of the preceding claims 1 to 7.
CN202310074241.XA 2023-01-13 2023-01-13 Satellite visibility simulation method and device Pending CN115983035A (en)

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Application Number Priority Date Filing Date Title
CN202310074241.XA CN115983035A (en) 2023-01-13 2023-01-13 Satellite visibility simulation method and device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310074241.XA CN115983035A (en) 2023-01-13 2023-01-13 Satellite visibility simulation method and device

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