A satellite acquisition method for a carrier monitoring terminal

Abstract

The application provides a satellite acquisition method for a carrier monitoring terminal, comprising the following steps: S1, acquiring all satellite ephemeris information on a target orbit and performing analysis processing to obtain the running orbit of each satellite; S2, acquiring coordinate information of the carrier monitoring terminal and performing coordinate conversion to construct a visible area of the carrier monitoring terminal; S3, calculating the accessible time period of each satellite relative to the carrier monitoring terminal based on the running orbit of each satellite and the visible area of the carrier monitoring terminal, and the accessible time periods of all satellites relative to the carrier monitoring terminal form a visible satellite timetable; S4, the carrier monitoring terminal acquires a target satellite according to the visible satellite timetable. The scheme provided by the application does not need to traverse all satellite ephemeris information of all on-orbit satellites to deduce the current positions of all on-orbit satellites and the satellites appearing above the carrier monitoring terminal when acquiring the satellites, thereby reducing the calculation amount and improving the satellite acquisition efficiency.

Description

Technical Field

[0001] This invention relates to the field of satellite communications, specifically to satellite acquisition technology in the field of satellite communications, and more specifically, to satellite acquisition technology for carrier monitoring terminals, i.e., a satellite acquisition method for carrier monitoring terminals. Background Technology

[0002] A carrier monitoring terminal (CMM) is a test instrument used for satellite network coverage and interference testing. It supports various satellite communication methods, including low-Earth orbit (LEO) broadband, LEO narrowband, and high-Earth orbit (HEO) broadband, and is of great significance to the construction of satellite internet. Specifically, the CMM captures and measures all satellites appearing in its orbit during each sampling period to monitor and analyze satellite signals and assess satellite network coverage and signal quality.

[0003] In the prior art, the carrier monitoring terminal acquires and measures all satellites appearing above it once in each sampling period in the following manner: within a sampling period, it traverses the ephemeris information of all on-orbit satellites to calculate the current position of all on-orbit satellites and the satellites appearing above the carrier monitoring terminal. Then, it sequentially calculates the distance, azimuth angle, and elevation angle of all satellites appearing above the carrier monitoring terminal relative to the carrier monitoring terminal. According to the order from near to far, it controls the antenna of the carrier monitoring terminal to be aligned with the satellites above it, and acquires and measures the satellites in sequence.

[0004] Although the proposed solutions in the existing technology can achieve satellite acquisition and measurement by the carrier monitoring terminal, the existing technology requires the carrier monitoring terminal to traverse the ephemeris information of all on-orbit satellites within a very short sampling period to deduce the current position of all on-orbit satellites and the satellites appearing above the carrier monitoring terminal. This results in the problems of large computational load and slow computation speed in the proposed solutions. Summary of the Invention

[0005] Therefore, the purpose of this invention is to overcome the defects of the prior art and provide a satellite acquisition method for a carrier monitoring terminal and a carrier monitoring terminal.

[0006] The objective of this invention is achieved through the following technical solutions.

[0007] According to a first aspect of the present invention, a satellite acquisition method for a carrier monitoring terminal is provided, the carrier monitoring terminal being used to acquire satellites to measure satellite signals, the method comprising: S1, acquiring ephemeris information of all satellites in a target orbit and parsing it to obtain the orbit of each satellite; S2, acquiring coordinate information of the carrier monitoring terminal and performing coordinate transformation to construct the visible area of ​​the carrier monitoring terminal; S3, calculating the accessible time period of each satellite relative to the carrier monitoring terminal based on the orbit of each satellite and the visible area of ​​the carrier monitoring terminal, the accessible time periods of all satellites relative to the carrier monitoring terminal constituting a visible satellite timetable; S4, the carrier monitoring terminal acquiring the target satellite according to the visible satellite timetable.

[0008] In some embodiments of the present invention, step S1 includes: S11, obtaining ephemeris information of all satellites in the target orbit and parsing it to obtain the orbital six-root number parameters of all satellites; S12, calculating the orbit of each satellite based on the orbital six-root number parameters of all satellites, wherein the orbit of each satellite is calculated in the following manner:

[0009]

[0010]

[0011]

[0012]

[0013] in, , , This indicates the satellite's coordinates on the XOY plane at the current moment. Indicates the radius of the satellite's orbit. This represents the angle between the line connecting the Earth's center to the satellite and the equatorial plane. Indicates the right ascension of the ascending node. Indicates the inclination of the satellite's orbit. This indicates the angle the satellite has rotated within the time difference between the current moment and the observation moment in the ephemeris information. Indicates the angle of approach. This indicates the number of times a satellite orbits the Earth per day. This represents the time difference between the current time and the observed time in the ephemeris information. Indicates the semi-major axis of the satellite's orbit. This represents the distance from geostationary orbit to the Earth's center. Indicates the argument of perigee.

[0014] In some embodiments of the present invention, step S2 includes: S21, obtaining the coordinates of the carrier monitoring terminal in the geocentric geofixed coordinate system and converting them into coordinates in the geocentric inertial coordinate system, wherein the coordinate transformation is performed in the following manner:

[0015]

[0016]

[0017] in, , , This indicates the coordinates of the carrier monitoring terminal in the geocentric-ground-fixed coordinate system at the current moment. , , This indicates the coordinates of the carrier monitoring terminal in the geocentric inertial coordinate system at the current moment. Indicates the angle of Greenwich Pyeongchang. Indicates the current Julian Day;

[0018] S22. Convert the coordinates of the carrier monitoring terminal in the geocentric inertial coordinate system to coordinates in the two-dimensional plane coordinate system, wherein the coordinate transformation is performed in the following manner:

[0019]

[0020] in, , This represents the coordinates of the carrier monitoring terminal in a two-dimensional plane coordinate system at the current moment;

[0021] S23. Based on the coordinates of the carrier monitoring terminal in the two-dimensional plane coordinate system, calculate the representation of the visible area above the carrier monitoring terminal after projection onto the two-dimensional plane:

[0022]

[0023]

[0024] in, , This represents the visible area after the visible area above the carrier monitoring terminal is projected onto a two-dimensional plane. Represents the Earth's radius. This represents the radius of the circle projected onto the Earth's surface from the visible area above the carrier monitoring terminal. Indicates the altitude of the satellite's orbit. This indicates the minimum visible elevation angle of the carrier monitoring terminal.

[0025] In some embodiments of the present invention, step S3 includes: S31, calculating the representation of the orbit of each satellite projected onto a two-dimensional plane in the following manner:

[0026]

[0027] in, , A representation of a satellite's orbit projected onto a two-dimensional plane;

[0028] S32. Based on the visible area representation after projecting the visible area above the carrier monitoring terminal onto a two-dimensional plane and the representation of the orbit of each satellite projected onto a two-dimensional plane, calculate the time period during which each satellite appears in the visible area above the carrier monitoring terminal within one orbital cycle; S33. Determine whether the satellite can communicate with the carrier monitoring terminal during the time period during which each satellite appears in the visible area above the carrier monitoring terminal within one orbital cycle, and filter out satellites that cannot communicate with the carrier monitoring terminal to obtain the accessible time period of each satellite relative to the carrier monitoring terminal.

[0029] In some embodiments of the present invention, step S4 includes: obtaining all satellites that can communicate with the carrier monitoring terminal at the current time based on the visual satellite timetable; selecting the satellite with the smallest distance from the carrier monitoring terminal from all satellites that can communicate with the carrier monitoring terminal at the current time as the target satellite for capture.

[0030] In some embodiments of the present invention, step S4 includes: obtaining all satellites that can communicate with the carrier monitoring terminal at the current time based on the visual satellite timetable, and randomly selecting one of them as the target satellite for capture.

[0031] In some embodiments of the present invention, the target orbit is a near-Earth circular orbit, a mid-Earth circular orbit, or an upper-Earth circular orbit.

[0032] According to a second aspect of the present invention, a carrier monitoring terminal is provided, the carrier monitoring terminal being configured to capture a satellite using the method described in the first aspect of the present invention.

[0033] Compared with the prior art, the advantages of the present invention are: (1) by performing a two-dimensional mapping between the satellite orbit and the visible area above the carrier monitoring terminal to calculate the visible satellite timetable, it is not necessary to traverse the ephemeris information of all on-orbit satellites to deduce the current position of all on-orbit satellites and the satellites appearing above the carrier monitoring terminal when capturing satellites, thus reducing the number of satellites that need to be deduced; (2) by capturing the satellites that the carrier monitoring terminal can access at the current time according to the visible satellite timetable, the efficiency of the carrier monitoring terminal in capturing satellites is improved. Attached Figure Description

[0034] The embodiments of the present invention will be further described below with reference to the accompanying drawings, wherein:

[0035] Figure 1 This is a schematic flowchart of a satellite acquisition method for a carrier monitoring terminal according to an embodiment of the present invention;

[0036] Figure 2 A schematic diagram illustrating an example of a satellite's orbit;

[0037] Figure 3 A schematic diagram illustrating the visible area above a carrier monitoring terminal;

[0038] Figure 4 This is a schematic diagram illustrating the visible area of ​​the carrier monitoring terminal after two-dimensional mapping and the satellite's orbit. Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of this invention clearer, the invention is further described in detail below through specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0040] As described in the background section, although the solutions proposed in the prior art can achieve satellite acquisition and measurement by the carrier monitoring terminal, the prior art solutions suffer from large computational load and slow computation speed because the carrier monitoring terminal needs to traverse the ephemeris information of all on-orbit satellites within a very short sampling period to deduce the current position of all on-orbit satellites and the satellites appearing above the carrier monitoring terminal.

[0041] To address the aforementioned issues, the inventors analyzed existing solutions and discovered that although there are tens of thousands of satellites in orbit, only a small fraction of them appear within the visible area of ​​the carrier monitoring terminal during a given time period. In other words, only a few dozen out of tens of thousands of satellites appear within the visible area of ​​the carrier monitoring terminal during a given time period. By filtering out satellites not within the visible area of ​​the carrier monitoring terminal during that time period and performing calculations only on satellites within the visible area, the computational load can be reduced and the computational speed increased. Based on this, the inventors proposed a scheme for rapidly capturing satellites. In this scheme, the ephemeris information of all satellites in orbit is first obtained to calculate the orbits of all satellites, and the visible area is determined according to the coordinates of the carrier monitoring terminal. Then, based on the orbits of all satellites and the visible area of ​​the carrier monitoring terminal, the visible time period of each satellite relative to the carrier monitoring terminal is calculated to obtain a visible satellite schedule. Finally, the target satellite is captured according to the visible satellite schedule. Thus, when capturing satellites, it is not necessary to traverse the ephemeris information of all satellites in orbit to calculate the current position of all satellites in orbit and the satellites appearing above the carrier monitoring terminal. This reduces the amount of computation and improves the efficiency of satellite capture.

[0042] To better understand the present invention, the present invention will be described in detail below with reference to the accompanying drawings and embodiments.

[0043] In summary, such as Figure 1 As shown, this invention provides a satellite acquisition method for a carrier monitoring terminal, comprising: S1, acquiring ephemeris information of all satellites in the target orbit and parsing it to obtain the orbit of each satellite; S2, acquiring the coordinate information of the carrier monitoring terminal and performing coordinate transformation to construct the visible area of ​​the carrier monitoring terminal; S3, calculating the accessible time period of each satellite relative to the carrier monitoring terminal based on the orbit of each satellite and the visible area of ​​the carrier monitoring terminal, and the accessible time periods of all satellites relative to the carrier monitoring terminal constitute a visible satellite timetable; S4, the carrier monitoring terminal acquires the target satellite according to the visible satellite timetable. To better understand the solution proposed by this invention, steps S1-S4 are described in detail below.

[0044] In step S1, the ephemeris information of all satellites in the target orbit is acquired and parsed to obtain the orbit of each satellite. According to one embodiment of the present invention, the target orbit is a near-Earth circular orbit, a mid-Earth circular orbit, or an upper-Earth circular orbit. It should be noted that, for ease of understanding, the proposed solution will be illustrated using a near-Earth circular orbit as an example in subsequent embodiments. The processing principles for all satellites in mid-Earth circular orbits and upper-Earth circular orbits are consistent with those for near-Earth circular orbits and will not be repeated here.

[0045] According to an embodiment of the present invention, step S1 includes steps S11-S12, and each step is described below.

[0046] In step S11, the ephemeris information of all satellites in the target orbit is obtained and parsed to obtain the orbital root parameters of all satellites. It should be noted that the satellite ephemeris information originates from on-orbit satellite orbital messages published by ground observation agencies in TLE format. The TLE message contains the launch time, observation time, and orbital inclination from the orbital root parameters. Right ascension of ascending node Orbital eccentricity r, perigee argument , and the near point angle and the number of times a satellite orbits the Earth per day Information such as that obtained from parsing the TLE message can determine the following: Figure 2 The image shows the satellite's orbit and position. The image shows the satellite's orbital semi-major axis. (Semi-major axis of the track) The shape of a satellite's orbit can be determined by the number of times it orbits the Earth per day (calculated using Kepler's Third Law) and its orbital eccentricity (r). The orbital inclination angle is also important. Right ascension of ascending node Perigeal argument It can obtain the satellite's orbital position relative to the Earth, based on the mean anomaly angle. It can obtain the relative position of the satellite in orbit at the time of observation.

[0047] In step S12, the orbit of each satellite is calculated based on the orbital six-root parameters of all satellites, wherein the orbit of each satellite is calculated as follows:

[0048]

[0049]

[0050]

[0051]

[0052] in, , , This indicates the satellite's coordinates on the XOY plane at the current moment. Indicates the radius of the satellite's orbit. This represents the angle between the line connecting the Earth's center to the satellite and the equatorial plane. Indicates the right ascension of the ascending node. Indicates the inclination of the satellite's orbit. This indicates the angle the satellite has rotated within the time difference between the current moment and the observation moment in the ephemeris information. Indicates the angle of approach. This indicates the number of times a satellite orbits the Earth per day. This represents the time difference between the current time and the observed time in the ephemeris information. Indicates the semi-major axis of the satellite's orbit. This represents the distance from geostationary orbit to the Earth's center. This represents the perigee argument. It should be noted that since satellites in near-Earth circular orbits are low-Earth orbit satellites, and the orbits of low-Earth orbit satellites are mainly near-circular orbits, the orbits of all satellites in near-Earth circular orbits are considered as circular orbits. In this case, the radius of the satellite's orbit is the semi-major axis of the satellite's orbit.

[0053] To better understand how the satellite's orbit is calculated in this invention, the calculation principle of the satellite's orbit in step S12 will be explained in detail below.

[0054] First, establish the circular coordinate equations on the XOY plane. It is represented as follows:

[0055]

[0056] Then, by rotating around the X-axis, the following rotation matrix is ​​obtained, which is represented as follows:

[0057]

[0058] Then, by rotating around the Z-axis, the following rotation matrix is ​​obtained, which is represented as follows:

[0059]

[0060] Finally, the satellite's orbit is calculated as follows:

[0061]

[0062] In step S2, the visible area of ​​the carrier monitoring terminal is constructed by acquiring the coordinate information of the carrier monitoring terminal and performing coordinate transformation. According to an embodiment of the present invention, step S2 includes steps S21-S23, which are described below.

[0063] In step S21, the coordinates of the carrier monitoring terminal in the geocentric geofixed coordinate system are obtained and converted into coordinates in the geocentric inertial coordinate system. The coordinate transformation is performed in the following manner:

[0064]

[0065]

[0066] in, , , This indicates the coordinates of the carrier monitoring terminal in the geocentric-ground-fixed coordinate system at the current moment. , , This indicates the coordinates of the carrier monitoring terminal in the geocentric inertial coordinate system at the current moment. Indicates the angle of Greenwich Pyeongchang. This indicates the Julian Day at the current moment. It should be noted that the relative speed of the carrier monitoring terminal (CMM) to the ground is smaller than the Earth's rotation speed. Therefore, the relative speed of the CMM can be ignored; that is, when reading the CMM's coordinates, only the Earth's rotation speed needs to be considered. It should also be noted that CMM coordinates are generally identified by latitude and longitude. Since latitude and longitude coordinates belong to the geocentric coordinate system, which differs from the geocentric inertial coordinate system of the satellite's orbit, and because the calculation of satellite coordinates involves a large amount of computation, the CMM's position coordinates are transformed from the geocentric coordinate system to the geocentric inertial coordinate system to reduce computational load, thus unifying the coordinate system for calculations.

[0067] In step S22, the coordinates of the carrier monitoring terminal in the geocentric inertial coordinate system are converted to coordinates in the two-dimensional plane coordinate system, wherein the coordinate transformation is performed in the following manner:

[0068]

[0069] in, , This represents the coordinates of the carrier monitoring terminal in a two-dimensional plane coordinate system at the current moment. It should be noted that the visible area above the carrier monitoring terminal is as follows: Figure 3 The diagram shows a conical region, which is mapped onto the ground as a circular region. When a satellite enters this conical region, it indicates that the satellite is within the visible area above the carrier monitoring terminal. To simplify the calculation process, the coordinates of the carrier monitoring terminal in the geocentric inertial coordinate system can be converted to coordinates in a two-dimensional plane coordinate system, and the visible area above the carrier monitoring terminal after mapping onto the two-dimensional plane can be calculated.

[0070] In step S23, the visible area of ​​the carrier monitoring terminal after projection onto the two-dimensional plane is calculated based on the coordinates of the carrier monitoring terminal in the two-dimensional plane coordinate system:

[0071]

[0072]

[0073] in, , This represents the visible area after the visible area above the carrier monitoring terminal is projected onto a two-dimensional plane. Represents the Earth's radius. This represents the radius of the circle projected onto the Earth's surface from the visible area above the carrier monitoring terminal. Indicates the altitude of the satellite's orbit. This represents the minimum visible elevation angle of the carrier monitoring terminal. The visible area above the carrier monitoring terminal, projected onto a two-dimensional plane, is shown below. Figure 4 As shown, by Figure 4 As can be seen, the visible area above the carrier monitoring terminal, after being projected onto a two-dimensional plane, is a rectangular area. In the figure, 'a' represents half the length of the visible area after being projected onto a two-dimensional plane, and 'b' represents half the width of the visible area after being projected onto a two-dimensional plane.

[0074] In step S3, the accessible time period for each satellite relative to the carrier monitoring terminal is calculated based on the orbit of each satellite and the visible area of ​​the carrier monitoring terminal. The accessible time periods of all satellites relative to the carrier monitoring terminal constitute the visible satellite timetable. According to an embodiment of the present invention, step S3 includes steps S31-S33, which are described below.

[0075] In step S31, the representation of the orbital projection of each satellite onto the two-dimensional plane is calculated as follows:

[0076]

[0077] in, , This represents the satellite's orbit projected onto a two-dimensional plane. The orbital path after projection onto the two-dimensional plane is shown below. Figure 4 As shown, by Figure 4 It can be seen that after the satellite's orbit is projected onto a two-dimensional plane, the satellite's orbit is a smooth curve. When this curve intersects with the visible area above the carrier monitoring terminal after it is projected onto a two-dimensional plane, it indicates that the satellite appears within the visible area above the carrier monitoring terminal.

[0078] In step S32, based on the visible area representation projected onto a two-dimensional plane from the visible area above the carrier monitoring terminal and the representation projected onto a two-dimensional plane from the orbit of each satellite, the time period during which each satellite appears in the visible area above the carrier monitoring terminal within one orbital cycle is calculated. It should be noted that the satellite coordinates... The time period during which the satellite is located in the visible area above the carrier monitoring terminal can be calculated by substituting the visible area into the representation of the visible area after projection onto a two-dimensional plane.

[0079] In step S33, it is determined whether each satellite can communicate with the carrier monitoring terminal during the time period when it appears in the visible area above the carrier monitoring terminal within one orbital cycle. Satellites that cannot communicate with the carrier monitoring terminal are filtered out to obtain the accessible time period for each satellite relative to the carrier monitoring terminal. It should be noted that when the satellite is in the visible area of ​​the carrier monitoring terminal, the elevation angle and distance between the carrier monitoring terminal and the satellite, as well as the angle between the carrier monitoring terminal and the satellite beam, are used to determine whether the terminal can establish a communication connection with the satellite.

[0080] In step S4, the carrier monitoring terminal acquires the target satellite according to the visual satellite schedule. According to one embodiment of the present invention,

[0081] Step S4 includes: obtaining all satellites that can communicate with the carrier monitoring terminal at the current time based on the visual satellite timetable; selecting the satellite with the smallest distance to the carrier monitoring terminal from all satellites that can communicate with the carrier monitoring terminal at the current time as the target satellite for acquisition. According to an embodiment of the present invention, step S4 includes: obtaining all satellites that can communicate with the carrier monitoring terminal at the current time based on the visual satellite timetable, and randomly selecting one satellite from them as the target satellite for acquisition. It should be noted that during the satellite acquisition process, the elevation angle, azimuth angle, and distance of the carrier monitoring terminal antenna are calculated based on the satellite's coordinates and the carrier monitoring terminal's coordinates to assist in correcting the carrier monitoring terminal antenna for satellite acquisition.

[0082] Based on the above embodiments, the present invention also provides a carrier monitoring terminal, which is configured to capture satellites using the method described in the foregoing embodiments.

[0083] The beneficial effects of the present invention are as follows: (1) By performing a two-dimensional mapping between the satellite orbit and the visible area above the carrier monitoring terminal to calculate the visible satellite timetable, it is not necessary to traverse the ephemeris information of all on-orbit satellites to deduce the current position of all on-orbit satellites and the satellites appearing above the carrier monitoring terminal when capturing satellites, thus reducing the number of satellites that need to be deduced; (2) The carrier monitoring terminal can capture satellites that are accessible at the current time according to the visible satellite timetable, thereby improving the efficiency of the carrier monitoring terminal in capturing satellites.

[0084] It should be noted that although the steps are described in a specific order above, it does not mean that the steps must be executed in the above specific order. In fact, some of these steps can be executed concurrently or even in a different order, as long as the required function can be achieved.

[0085] This invention can be a system, method, and / or computer program product. A computer program product may include a computer-readable storage medium having computer-readable program instructions loaded thereon for causing a processor to implement various aspects of the invention.

[0086] Computer-readable storage media can be tangible devices that hold and store instructions for use by an instruction execution device. Computer-readable storage media can include, for example, but not limited to, electrical storage devices, magnetic storage devices, optical storage devices, electromagnetic storage devices, semiconductor storage devices, or any suitable combination thereof. More specific examples (a non-exhaustive list) of computer-readable storage media include: portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), static random access memory (SRAM), portable compact disc read-only memory (CD-ROM), digital multifunction disc (DVD), memory sticks, floppy disks, mechanical encoding devices, such as punch cards or recessed protrusions storing instructions thereon, and any suitable combination thereof.

[0087] The various embodiments of the present invention have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or technical improvements to the embodiments in the market, or to enable others skilled in the art to understand the embodiments disclosed herein.

Claims

1. A satellite acquisition method for a carrier monitoring terminal, the carrier monitoring terminal being used to acquire satellites to measure satellite signals, characterized in that, The method includes: S1. Obtain the ephemeris information of all satellites in the target orbit and parse and process it to obtain the orbit of each satellite. Step S1 includes: S11. Obtain the ephemeris information of all satellites in the target orbit and parse it to obtain the orbital root number parameters of all satellites; S12. Calculate the orbit of each satellite based on the six orbital parameters of all satellites, wherein the orbit of each satellite is calculated in the following manner: in, , , This indicates the satellite's coordinates on the XOY plane at the current moment. Indicates the radius of the satellite's orbit. This represents the angle between the line connecting the Earth's center to the satellite and the equatorial plane. Indicates the right ascension of the ascending node. Indicates the inclination of the satellite's orbit. This indicates the angle the satellite has rotated within the time difference between the current moment and the observation moment in the ephemeris information. Indicates the angle of approach. This indicates the number of times a satellite orbits the Earth per day. This represents the time difference between the current time and the observed time in the ephemeris information. Indicates the semi-major axis of the satellite's orbit. This represents the distance from geostationary orbit to the Earth's center. Indicates the argument of perigee; S2. Obtain the coordinate information of the carrier monitoring terminal and perform coordinate transformation to construct the visible area of ​​the carrier monitoring terminal; S3. Calculate the accessible time period for each satellite relative to the carrier monitoring terminal based on the orbit of each satellite and the visible area of ​​the carrier monitoring terminal. The accessible time periods of all satellites relative to the carrier monitoring terminal constitute a visible satellite timetable. Step S3 includes: S31. Calculate the representation of the orbital trajectory of each satellite projected onto a two-dimensional plane as follows: in, , A representation of a satellite's orbit projected onto a two-dimensional plane; S32. Based on the visible area representation after the visible area above the carrier monitoring terminal is projected onto a two-dimensional plane and the representation of the orbit of each satellite projected onto a two-dimensional plane, calculate the time period during which each satellite appears in the visible area above the carrier monitoring terminal within one orbital cycle. S33. Determine whether each satellite can communicate with the carrier monitoring terminal during the time period when it appears in the visible area above the carrier monitoring terminal within an orbital cycle, and filter out satellites that cannot communicate with the carrier monitoring terminal to obtain the accessible time period of each satellite relative to the carrier monitoring terminal. S4. The carrier monitoring terminal captures the target satellite according to the visual satellite timetable.

2. The method according to claim 1, characterized in that, Step S2 includes: S21. Obtain the coordinates of the carrier monitoring terminal in the geocentric coordinate system and convert them to coordinates in the geocentric inertial coordinate system, wherein the coordinate transformation is performed in the following manner: in, , , This indicates the coordinates of the carrier monitoring terminal in the geocentric-ground-fixed coordinate system at the current moment. , , This indicates the coordinates of the carrier monitoring terminal in the geocentric inertial coordinate system at the current moment. Indicates the angle of Greenwich Pyeongchang. Indicates the current Julian Day; S22. Convert the coordinates of the carrier monitoring terminal in the geocentric inertial coordinate system to coordinates in the two-dimensional plane coordinate system, wherein the coordinate transformation is performed in the following manner: in, , This represents the coordinates of the carrier monitoring terminal in a two-dimensional plane coordinate system at the current moment; S23. Based on the coordinates of the carrier monitoring terminal in the two-dimensional plane coordinate system, calculate the representation of the visible area above the carrier monitoring terminal after projection onto the two-dimensional plane: in, , This represents the visible area after the visible area above the carrier monitoring terminal is projected onto a two-dimensional plane. Represents the Earth's radius. This represents the radius of the circle projected onto the Earth's surface from the visible area above the carrier monitoring terminal. Indicates the altitude of the satellite's orbit. This indicates the minimum visible elevation angle of the carrier monitoring terminal.

3. The method according to claim 2, characterized in that, Step S4 includes: Based on the visual satellite timetable, obtain all satellites that can communicate with the carrier monitoring terminal at the current moment; Select the satellite with the smallest distance from the carrier monitoring terminal from all satellites that can communicate with the carrier monitoring terminal at the current moment as the target satellite for capture.

4. The method according to claim 2, characterized in that, Step S4 includes: Based on the visual satellite timetable, obtain all satellites that can communicate with the carrier monitoring terminal at the current moment, and select one of them as the target satellite for capture.

5. The method according to claim 1, characterized in that, The target orbit is a near-Earth circular orbit, a mid-Earth circular orbit, or an upper-Earth circular orbit.

6. A carrier monitoring terminal, characterized in that, The carrier monitoring terminal is configured to capture satellites using the method described in any one of claims 1-5.

7. A computer-readable storage medium, characterized in that, It contains a computer program that can be executed by a processor to implement the steps of the method according to any one of claims 1-5.

8. An electronic device, characterized in that, include: One or more processors; A storage device for storing one or more programs that, when executed by one or more processors, cause the electronic device to perform the steps of the method as described in any one of claims 1-5.

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