Satellite communication method, system and device and nonvolatile storage medium

Abstract

The invention discloses a satellite communication method, system and device and a nonvolatile storage medium. The method comprises the following steps: determining position information of terminal equipment, and determining a target area to which the terminal equipment belongs according to the position information; coverage information of a satellite communication system for the target area is determined, the satellite communication system comprises at least one constellation composed of a plurality of satellite orbit planes at equal intervals, a preset number of satellites run on each satellite orbit plane, the orbit type of the satellite orbit plane is a regression orbit, and the satellite orbit plane is a medium orbit satellite orbit; and determining a satellite for providing satellite communication service for the terminal equipment according to the coverage information. The technical problems of high construction cost, complex management and low service efficiency of a satellite communication system caused by the fact that a traditional satellite communication method is difficult to balance the contradiction among the coverage range, the number of satellites and the service performance are solved.

Description

Technical Field

[0001] The present application relates to the field of satellite communications, and more specifically, to a satellite communications method, system, device and non-volatile storage medium. Background Art

[0002] In satellite communication technology, building a communication network with global coverage is a crucial goal. Currently, high-orbit satellites have the problem of large link loss. However, in order to achieve global coverage, although low-orbit satellite constellations have small link loss, they require hundreds of satellites. Traditional satellite communication methods are difficult to balance the contradiction between coverage, number of satellites and service performance.

[0003] To address the above-mentioned problems, no effective solution has been proposed yet. Summary of the invention

[0004] The embodiments of the present application provide a satellite communication method, system, device and non-volatile storage medium to at least solve the technical problems of high satellite communication system construction cost, complex management and low service efficiency caused by the difficulty of traditional satellite communication methods in balancing the contradiction between coverage, number of satellites and service performance.

[0005] According to one aspect of an embodiment of the present application, a satellite communication method is provided, including: determining location information of a terminal device, and determining a target area to which the terminal device belongs based on the location information; determining coverage information of a satellite communication system for the target area, wherein the satellite communication system includes at least one constellation composed of a plurality of equally spaced satellite orbital planes, each satellite orbital plane having a preset number of satellites running thereon, the orbital type of the satellite orbital plane being a recurrent orbit, and the satellite orbital plane being a medium-orbit satellite orbit, the coverage information including a coverage time period during which the target area is covered by the satellite communication system, and a satellite identifier corresponding to each coverage time period; and determining a satellite that provides satellite communication services to the terminal device based on the coverage information.

[0006] Optionally, determining the satellite that provides satellite communication services to the terminal device based on the coverage information includes: determining the coverage time period at the target time and the satellite identifier corresponding to the coverage time period; and determining the satellite that provides satellite communication services to the terminal device based on the satellite identifier.

[0007] Optionally, the satellites operating on each satellite orbital plane include first-category satellites and second-category satellites, wherein the operating periods of the first-category satellites operating on each satellite orbital plane of the constellation relative to any position on the ground are the same, and the operating periods of the second-category satellites operating on each satellite orbital plane relative to any position on the ground are the same; in the case where the satellite communication system includes multiple constellations, the ascending node longitude parameters of each constellation are different, and the orbital inclination angles of each constellation are different, and each constellation is used to complement each other's coverage; or, the orbital inclination angles of each constellation are partially the same.

[0008] Optionally, the initial observation azimuth and initial observation elevation angle corresponding to the first type of satellites are the same, and the observation time interval corresponding to any two first type of satellites in an adjacent observation order is a first preset time length; and the initial observation azimuth and initial observation elevation angle corresponding to the second type of satellites are the same, and the observation time interval corresponding to any two second type of satellites in an adjacent observation order is a second preset time length.

[0009] Optionally, when the satellites operating on each satellite orbital plane are a first-category satellite and a second-category satellite, the phase difference between the first-category satellite and the second-category satellite operating on the same satellite orbital plane is 180°.

[0010] Optionally, orbital parameters of the satellite communication system are determined based on coverage requirement information or interference avoidance requirement information, wherein the orbital parameters include at least one of the following: a preset orbital regression period, a preset angle between the orbital plane and the equatorial plane, a preset orbital shape, a preset position of the orbital sub-satellite point trajectory crossing the equator, a preset orientation of the orbital perigee in the orbit, and a preset position of the satellite in the orbit; an orbital adjustment instruction is generated based on the orbital parameters, and a target satellite for receiving the orbital adjustment instruction is determined based on the coverage information; and the orbital adjustment instruction is sent to the target satellite.

[0011] Optionally, generating an orbit adjustment instruction based on orbit parameters includes: determining the orbital semi-major axis information of the satellite orbital plane based on a preset orbital regression period; determining the orbital inclination angle of the satellite orbital plane based on a preset angle; determining the orbital eccentricity of the satellite orbital plane based on a preset orbital shape; determining the longitude parameters of the ascending node of the satellite orbital plane based on a preset position where the orbital sub-satellite point trajectory crosses the equator; determining the perigee argument of the satellite orbital plane based on a preset azimuth; determining the true anomaly angle of the satellite orbital plane based on a preset position of the satellite in orbit; generating an orbit adjustment instruction, wherein the orbit adjustment instruction carries the orbital semi-major axis information, the orbital inclination angle, the orbital eccentricity, the longitude parameters of the ascending node, the perigee argument, and the true anomaly angle.

[0012] According to another aspect of an embodiment of the present application, a satellite communication system is also provided, including a terminal device, a ground base station and a satellite, wherein: the ground base station is used to determine the location information of the terminal device, and determine the target area to which the terminal device belongs based on the location information; determine the coverage information of the satellite communication system relative to the target area; determine the satellite that provides satellite communication services to the terminal device based on the coverage information; the satellite communication system also includes a plurality of equally spaced satellite orbital planes, each of which has a preset number of satellites running on it, the orbital type of the satellite orbital plane is a recurrent orbit, and the satellite orbital plane is a medium-orbit satellite orbit, and the coverage information includes the coverage time period when the target area is covered by the satellite communication system, and the satellite identifier corresponding to each coverage time period.

[0013] According to another aspect of an embodiment of the present application, a satellite communication device is also provided, including: a first processing module, used to determine the location information of a terminal device, and determine the target area to which the terminal device belongs based on the location information; a second processing module, used to determine the coverage information of the satellite communication system for the target area, wherein the satellite communication system includes at least one constellation composed of a plurality of equally spaced satellite orbital planes, each satellite orbital plane has a preset number of satellites running on it, the orbital type of the satellite orbital plane is a regression orbit, and the satellite orbital plane is a medium-orbit satellite orbit, and the coverage information includes the coverage time period during which the target area is covered by the satellite communication system, and the satellite identifier corresponding to each coverage time period; a third processing module, used to determine the satellite that provides satellite communication services to the terminal device based on the coverage information.

[0014] According to another aspect of an embodiment of the present application, a non-volatile storage medium is provided, in which a program is stored, wherein when the program is running, a device where the non-volatile storage medium is located is controlled to execute a satellite communication method.

[0015] According to another aspect of an embodiment of the present application, there is also provided an electronic device, including: a memory and a processor, the processor being configured to run a program stored in the memory, wherein the satellite communication method is executed when the program is run.

[0016] According to another aspect of an embodiment of the present application, a computer program product is also provided, including a computer program, and when the computer program is executed by a processor, a satellite communication method is implemented.

[0017] In an embodiment of the present application, the location information of the terminal device is determined, and the target area to which the terminal device belongs is determined based on the location information; the coverage information of the satellite communication system for the target area is determined, wherein the satellite communication system includes at least one constellation composed of a plurality of equally spaced satellite orbital planes, a preset number of satellites are running on each satellite orbital plane, the orbit type of the satellite orbital plane is a regression orbit, and the satellite orbital plane is a medium-orbit satellite orbit, and the coverage information includes a coverage time period during which the target area is covered by the satellite communication system, and a satellite identifier corresponding to each coverage time period; a method of determining a satellite that provides satellite communication services to the terminal device based on the coverage information is adopted, and the purpose of accurately positioning satellite services and optimizing satellite resource allocation is achieved by determining the location information of the terminal device and matching the coverage strategy of the regression orbit medium-orbit satellite constellation based on the information, thereby achieving the technical effect of significantly reducing the construction and operation and maintenance as a service efficiency of the satellite communication system while ensuring global coverage and service performance, thereby solving the technical problems of high construction cost, complex management and low service efficiency of the satellite communication system caused by the difficulty of traditional satellite communication methods in balancing the contradiction between coverage range, number of satellites and business performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0019] Figure 1 It is a structural schematic diagram of a computer terminal (mobile device) provided according to an embodiment of the present application;

[0020] Figure 2 It is a schematic diagram of a sub-satellite point trajectory of an orbit with an inclination of 55° and a single-day return number of 4.5 times according to an embodiment of the present application;

[0021] Figure 3 is a schematic diagram of a medium orbit constellation with an orbital inclination of 55° according to an embodiment of the present application;

[0022] Figure 4 is a schematic diagram of a sub-satellite point trajectory of an orbit with an inclination angle of 55° according to an embodiment of the present application;

[0023] Figure 5 It is a flowchart of a satellite communication method provided according to an embodiment of the present application;

[0024] Figure 6 It is a schematic diagram of the structure of a satellite communication device provided according to an embodiment of the present invention. DETAILED DESCRIPTION

[0025] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present application.

[0026] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0027] In order to better understand the embodiments of the present application, the technical terms involved in the embodiments of the present application are explained as follows:

[0028] High-orbit satellite: Satellites with an orbit altitude of 36,000 kilometers are generally called high-orbit earth satellites.

[0029] Medium Earth Orbit Satellite: The orbit of a medium earth orbit satellite MEO (Medium Earth Orbit) is generally between about 1,500 and 36,000 kilometers from the ground.

[0030] Low-orbit satellite: An Earth satellite with an orbital altitude less than 1500km and greater than 300km is generally called a low-orbit satellite.

[0031] Satellite constellation: A satellite system composed of multiple satellites deployed according to certain rules is called a satellite constellation.

[0032] Regression orbit: The subsatellite point trajectory overlaps periodically, that is, after a certain period of time, the subsatellite point trajectory returns to the original route. This type of orbit is called a regression orbit, or a revisit orbit or a cyclic orbit. The period of overlap is called a regression period.

[0033] Walker constellation: It is a constellation arrangement when the general satellite orbit is a circular orbit, the orbital planes are evenly distributed, and the satellites in the orbital planes are evenly distributed.

[0034] In related technologies, in order to achieve effective coverage of hot spots on the earth, satellite communications generally use a constellation of multiple satellites to provide communication services. For high-orbit satellites, such as GSO (Geostationary satellite orbit) satellites, because their orbital positions are stationary relative to the earth, the areas provided by GSO services are relatively fixed. Multiple GSO satellites can achieve coverage of major hot spots or densely populated areas around the world. For example, the maritime satellite system uses 5-7 GSO satellites to achieve coverage of major areas of the world. For low-orbit satellites, dozens or even hundreds of thousands of satellites are often required to form a constellation to provide coverage of major areas of the world. For example: The OneWeb system requires more than 720 satellites to provide global Ku-band broadband data services; the Starlink system requires tens of thousands of satellites to provide global broadband data services.

[0035] Due to the geometric characteristics of the Earth's artificial satellite orbit, the higher the orbital altitude, the greater the coverage of the ground by a single satellite, and the fewer satellites are needed to achieve global coverage. The lower the orbital altitude, the smaller the coverage of the ground by a single satellite, and the more satellites are needed to achieve global coverage. However, the higher the orbit, the greater the link loss, and the worse the service performance that can be provided under the same terminal conditions; the lower the orbital altitude, the smaller the link loss, and the better the service performance that can be provided under the same terminal conditions. It can be seen that in order to achieve global coverage, although the link loss of low-orbit satellite constellations is small, hundreds of satellites are required, and although the link loss of high-orbit satellites is large, the number of satellites required is greatly reduced. In order to balance the construction cost of the satellite constellation and the business capabilities that the constellation system can provide, it is necessary to carry out the structural optimization design of the satellite communication constellation, and build a satellite communication system taking into account multiple factors such as the number of satellites, coverage, frequency interference avoidance strategy, and system capacity.

[0036] In order to solve the above problems, relevant solutions are provided in the embodiments of the present application, which are described in detail below.

[0037] According to an embodiment of the present application, a method embodiment of a satellite communication method is provided. It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and although a logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0038] The method embodiments provided in the embodiments of the present application can be executed in a mobile terminal, a computer terminal or a similar computing device. Figure 1 FIG. 1 shows a hardware structure block diagram of a computer terminal (or mobile device) for implementing a satellite communication method. Figure 1As shown, the computer terminal 10 (or mobile device 10) may include one or more (102a, 102b, ..., 102n are used to illustrate) processors 102 (the processor 102 may include but is not limited to a processing device such as a microprocessor MCU or a programmable logic device FPGA), a memory 104 for storing data, and a transmission device 106 for communication functions. In addition, it may also include: a display, an input / output interface (I / O interface), a universal serial bus (USB) port (which may be included as one of the ports of the BUS bus), a network interface, a power supply and / or a camera. It can be understood by those skilled in the art that Figure 1 The structure shown is only for illustration and does not limit the structure of the above electronic device. Figure 1 More or fewer components as shown, or with Figure 1 Different configurations are shown.

[0039] It should be noted that the one or more processors 102 and / or other data processing circuits described above may generally be referred to herein as "data processing circuits". The data processing circuits may be embodied in whole or in part as software, hardware, firmware, or any other combination thereof. In addition, the data processing circuit may be a single independent processing module, or may be incorporated in whole or in part into any of the other components in the computer terminal 10 (or mobile device). As described in the embodiments of the present application, the data processing circuit acts as a processor control (e.g., selection of a variable resistor terminal path connected to an interface).

[0040] The memory 104 can be used to store software programs and modules of application software, such as the program instructions / data storage device corresponding to the satellite communication method in the embodiment of the present application. The processor 102 executes various functional applications and data processing by running the software programs and modules stored in the memory 104, that is, realizing the above-mentioned satellite communication method. The memory 104 may include a high-speed random access memory, and may also include a non-volatile memory, such as one or more magnetic storage devices, flash memory, or other non-volatile solid-state memory. In some examples, the memory 104 may further include a memory remotely arranged relative to the processor 102, and these remote memories may be connected to the computer terminal 10 via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0041] The transmission device 106 is used to receive or send data via a network. The specific example of the above network may include a wireless network provided by a communication provider of the computer terminal 10. In one example, the transmission device 106 includes a network adapter (Network Interface Controller, NIC), which can be connected to other network devices through a base station so as to communicate with the Internet. In one example, the transmission device 106 can be a radio frequency (RF) module, which is used to communicate with the Internet wirelessly.

[0042] The display may be, for example, a touch screen liquid crystal display (LCD) that enables a user to interact with a user interface of the computer terminal 10 (or mobile device).

[0043] An embodiment of the present application provides a satellite communication system, including a terminal device, a ground base station and a satellite, wherein: the ground base station is used to determine the location information of the terminal device, and determine the target area to which the terminal device belongs based on the location information; determine the coverage information of the satellite communication system relative to the target area; determine the satellite that provides satellite communication services to the terminal device based on the coverage information; the satellite communication system also includes a plurality of equally spaced satellite orbital planes, each of which has a preset number of satellites running on it, the orbit type of the satellite orbital plane is a recurrent orbit, and the satellite orbital plane is a medium-orbit satellite orbit, and the coverage information includes the coverage time period when the target area is covered by the satellite communication system, and the satellite identifier corresponding to each coverage time period.

[0044] Specifically, the orbital period of an artificial earth satellite is related to the orbital altitude of the satellite, that is, related to the semi-major axis of the satellite orbit, as shown in the following formula.

[0045]

[0046] Among them, a represents the semi-major axis of the orbit, G is the gravitational constant, and M is the mass of the earth. Assuming that the earth takes 23 hours, 56 minutes and 4 seconds to rotate once, the satellite orbit parameters under different regression periods are calculated based on this period, mainly including: the number of orbit regressions within a single earth rotation period and the corresponding orbit semi-major axis and orbit period parameters, as shown in the table below.

[0047]

[0048] The Van Allen radiation belts are located at altitudes of 1500km-5000km and 13000km-20000km from the Earth's surface, and are divided into inner and outer belts. The orbits with a return number greater than or equal to 12.5 and less than 4.5 (not included) in a single Earth rotation period are within the inner belt, and the orbital altitudes with a return number equal to 2.5 in the table above are within the outer belt.

[0049] According to the above analysis, the satellite orbit altitude with a daily return number of 4.5 belongs to the medium-orbit satellite orbit, which is between the inner and outer belts of the Van Allen radiation belt. The space radiation environment is relatively good and is suitable for the orbit of a communication satellite. Figure 2 An orbital sub-satellite point trajectory with an inclination of 55° and a daily return frequency of 4.5 is shown.

[0050] Optionally, the medium-orbit satellite mobile communication constellation structure is realized based on the above orbital altitude:

[0051] 1. The semi-major axis of the fixed satellite orbit is 15459.11km (±20km) and the eccentricity is 0;

[0052] 2. According to the satellite orbit coverage requirements or interference avoidance requirements, determine the longitude of the ascending node of the satellite orbit, so as to determine the position where the sub-satellite point trajectory of the satellite orbit crosses the equator;

[0053] 3. Based on the above orbits, the Walker constellation is constructed, with the delta constellation configuration: N=12, P=6, F=4.

[0054] The medium-orbit constellation has 6 orbital planes (i.e. satellite orbital planes), each orbital plane has 2 stars (i.e. a preset number of satellites), the phase difference between the 2 stars is 180°, and there are a total of 12 stars. Each star has the same sub-satellite point motion trajectory, and each star orbits the earth 4.5 times in a single day.

[0055] 4. The preferred value of satellite orbit inclination: 30°-60°.

[0056] Figure 3 A mid-orbit constellation with an orbital inclination of 55° is shown. Figure 3 As shown, the satellite numbers and positions in the constellation are as follows:

[0057] Orbital plane 1: 1-1 star true anomaly 0°, 1-2 star true anomaly 180°;

[0058] Orbital plane 2: 2-1 true anomaly 90°, 2-2 true anomaly 270°;

[0059] Orbital plane 3: 3-1 has a true anomaly angle of 180°, 3-2 has a true anomaly angle of 360°;

[0060] Orbital plane 4: 4-1 true anomaly 270°, 4-2 true anomaly 90°;

[0061] Orbital plane 5: 5-1 true anomaly 0°, 5-2 true anomaly 180°;

[0062] Orbital plane 6: 6-1 true anomaly 90°, 6-2 true anomaly 270°;

[0063] The longitude intervals of the ascending nodes in the orbital planes are 60°.

[0064] The subsatellite point trajectory of this constellation is fixed and returns in a 2-day cycle. The trajectory is as follows Figure 4 shown.

[0065] The satellite communication constellation designed with regression orbit has obvious regression and repetitive characteristics in its sub-satellite point trajectory on the earth's surface, that is, the relative position of the satellite orbit and the ground signal gateway or tracking and control station has repetitive characteristics. This characteristic can simplify the on-orbit management of the satellite constellation by the ground station.

[0066] Taking the above medium-orbit satellite communication constellation with a daily return frequency of 4.5 as an example, Walker Delta (12 / 6 / 4), with an orbital inclination of 55°, 6 orbital planes are evenly spaced, 2 satellites in each orbital plane, and a total of 12 satellites belong to the medium-orbit satellite orbit. The ground station at any location on the earth has periodic visibility of the satellites of this constellation.

[0067] The ground station starts observing satellites 1-1, 2-1, 3-1, 4-1, 5-1 and 6-1 at the same azimuth and elevation angles, with a periodic interval of 4 hours;

[0068] The ground station starts observing satellites 1-2, 2-2, 3-2, 4-2, 5-2 and 6-2 at the same azimuth and elevation angles, with a periodic interval of 4 hours.

[0069] By utilizing the above characteristics and arranging daily observation tables for ground stations, it is possible to control the ground stations to periodically and automatically implement daily observation and control of satellite constellations, thereby improving the efficiency and reliability of constellation management.

[0070] By utilizing the characteristics of the recurrent orbit, the satellite can repeatedly visit any area on the ground in a certain period. In terms of satellite mobile communications, by utilizing this characteristic of the satellite orbit, the ground service area can periodically obtain satellite communication services. Take the above medium-orbit satellite communication constellation with a single-day recurrent frequency of 4.5 as an example, Walker Delta (12 / 6 / 4), with an orbital inclination of 55°.

[0071] Satellites 1-1, 2-1, 3-1, 4-1, 5-1 and 6-1 have the same service period for any location on the ground, and the service interval between different satellites for any location area is 4 hours.

[0072] The service periods of satellites 1-2, 2-2, 3-2, 4-2, 5-2 and 6-2 for any location on the ground are the same, and the service interval between different satellites for any location area is 4 hours.

[0073] In the above operating environment, the embodiment of the present application provides a satellite communication method, such as Figure 5 As shown, the method comprises the following steps:

[0074] Step S502, determining the location information of the terminal device, and determining the target area to which the terminal device belongs based on the location information.

[0075] Optionally, by utilizing the characteristics of the regression orbit, the satellite can repeatedly visit any area on the ground in a certain period. In terms of satellite mobile communications, by utilizing this characteristic of the satellite orbit, the ground service area can periodically obtain the communication service of the satellite. The ground base station obtains the location information of the terminal device and determines the ground service area (i.e., the target area) where the terminal device is located.

[0076] Step S504, determining the coverage information of the satellite communication system for the target area, wherein the satellite communication system includes at least one constellation composed of a plurality of equally spaced satellite orbital planes, each satellite orbital plane has a preset number of satellites running on it, the orbital type of the satellite orbital plane is a regression orbit, and the satellite orbital plane is a medium-orbit satellite orbit, and the coverage information includes the coverage time period of the target area covered by the satellite communication system, and the satellite identifiers corresponding to each coverage time period.

[0077] Optionally, the satellite communication system determines the coverage information of the target area based on the characteristics of the regression orbit satellite constellation, especially taking the medium-orbit satellite communication constellation with an inclination of 55° and a single-day regression number of 4.5 as an example, the Walker Delta (12 / 6 / 4) configuration is applied, where N=12 represents the total number of satellites, P=6 represents the number of satellite orbit planes, and F=4 represents the phase difference of satellites in adjacent orbital planes. These parameters jointly determine the structure and operation mode of the satellite constellation. The characteristics of the regression orbit ensure that the satellite can repeatedly visit a specific area on the ground with a certain period, thereby providing periodic and regular communication services for the ground service area.

[0078] In order to determine the coverage information of the satellite communication system for the target area, including the coverage time period and the corresponding service satellite identification, we first need to understand the movement patterns of satellites in different orbital planes. The Walker Delta constellation design ensures that satellites on the same orbital plane have the same service period. For example, 1-1, 2-1, 3-1, 4-1, 5-1 and 6-1 satellites constitute the first type of satellites. For any location on the ground, these satellites have the same service period, and the service interval between different satellites is 4 hours. This means that once the service time of any satellite for that location is determined, the coverage time period of the remaining satellites can be calculated, forming a continuous and periodic communication access mode.

[0079] Similarly, the second category of satellites, namely 1-2, 2-2, 3-2, 4-2, 5-2 and 6-2 satellites, operate in different orbital planes, but also have the same service period, and the service interval between different satellites is also 4 hours. This design makes full use of the characteristics of the regression orbit, allowing the satellite constellation to achieve coverage of major global areas with a minimum number of satellites, while reducing the risk of frequency interference, because the satellites in each orbital plane are evenly distributed, avoiding the concentrated access of multiple satellites to the same ground area at the same time, thereby improving the overall performance and availability of the communication system.

[0080] When determining coverage information, the ground base station will track the real-time position and motion status of the satellite, and combine the satellite orbit parameters (such as orbit semi-major axis, inclination, eccentricity, ascending node longitude, perigee argument and true anomaly) to predict when the satellite will enter the visible range of the target area, and record the satellite identification serving the area during this time period. For each target area, in this way, a detailed satellite communication service schedule can be constructed to ensure that ground users can find satellites providing services at any time, thereby achieving continuous and seamless communication connections. The determination of satellite identification and coverage time period further reflects the advantages of this technical solution in improving the flexibility and efficiency of satellite communication systems, as well as its contribution to optimizing resource scheduling and improving service quality.

[0081] In the technical solution provided in step S504, the satellites operating on each satellite orbital plane include first-category satellites and second-category satellites, wherein the operating periods of the first-category satellites operating on each satellite orbital plane of the constellation relative to any position on the ground are the same, and the operating periods of the second-category satellites operating on each satellite orbital plane relative to any position on the ground are the same; in the case where the satellite communication system includes multiple constellations, the longitude parameters of the ascending nodes of each constellation are different, and the orbital inclination angles of each constellation are different, and each constellation is used to complement each other's coverage; or, the orbital inclination angles of each constellation are partially the same.

[0082] Optionally, the initial observation azimuth and initial observation elevation angle corresponding to the first type of satellites are the same, and the observation time interval corresponding to any two first type of satellites in an adjacent observation order is a first preset time length; and the initial observation azimuth and initial observation elevation angle corresponding to the second type of satellites are the same, and the observation time interval corresponding to any two second type of satellites in an adjacent observation order is a second preset time length.

[0083] Optionally, taking the above-mentioned medium-orbit satellite communication constellation with a single-day return number of 4.5 as an example, Walker Delta (12 / 6 / 4), orbital inclination 55°, 6 orbital planes are evenly spaced, 2 satellites per orbital plane, and a total of 12 satellite orbital heights belong to the medium-orbit satellite orbit. The ground base station at any location on the earth has periodic visibility of the satellites of this constellation.

[0084] The ground base station starts observing the azimuth and elevation angles of satellites 1-1, 2-1, 3-1, 4-1, 5-1 and 6-1 (i.e., the first type of satellites) at the same interval of 4 hours (i.e., the first preset duration);

[0085] The ground base station starts observing satellites 1-2, 2-2, 3-2, 4-2, 5-2 and 6-2 (i.e., second type of satellites) at the same azimuth and elevation angles, with a periodic interval of 4 hours (i.e., the second preset duration).

[0086] Optionally, when the satellites operating on each satellite orbital plane are a first-category satellite and a second-category satellite, the phase difference between the first-category satellite and the second-category satellite operating on the same satellite orbital plane is 180°.

[0087] Optionally, in the case where a satellite communication system includes multiple constellations, the ascending node longitude parameters of each constellation are different, and the orbital inclination angles of each constellation are different, and each constellation is used to complement each other's coverage; or, the orbital inclination angles of each constellation are partially the same. When building a global satellite mobile communication network, a single constellation may not be able to perfectly cover all geographical areas, especially in polar and high-latitude regions. In order to solve this problem, the satellite communication system supports multiple constellations, each with different orbital parameters, to achieve seamless coverage around the world. In specific implementation, the satellite communication system first determines that the ascending node longitude parameters of each constellation are different, which means that the positions where the satellite orbits cross the equator will be staggered, thereby avoiding duplication of coverage near the equator and ensuring efficient use of resources. For example, the ascending node longitude of constellation A can be set to 0°, while the ascending node longitude of constellation B is set to 60°, and so on, to ensure that the trajectory of the satellites of each constellation above the equator is evenly distributed without blind spots.

[0088] In addition, the orbital inclination angles of each constellation must also be different. The purpose of this strategy is to expand coverage, especially to high-latitude areas. Different orbital inclination angles mean that the angles between the orbital plane of the satellite constellation and the equatorial plane are different, so that the sub-satellite point tracks of the satellite constellations will cover different latitude areas, complement each other, and jointly build a global coverage network. For example, the orbital inclination angle of constellation A can be set to 55° to ensure good mid-latitude coverage; the orbital inclination angle of constellation B is set to 65°, focusing on covering high-latitude areas; and the orbital inclination angle of constellation C may be set to 45° to enhance coverage of low-latitude areas, or there are also some constellations with the same orbital inclination angle to improve the overall redundancy of the system.

[0089] By integrating multiple constellations with different ascending node longitudes and orbital inclination angles in the satellite communication system, the system can achieve complementary coverage of all parts of the world, especially in specific geographical environments where enhanced coverage is needed, such as at sea, in polar regions or in remote mountainous areas. Through the collaborative work of multiple constellations, it can be ensured that users in these areas can also enjoy stable and high-quality satellite communication services. In addition, the complementary coverage of different constellations can also improve the overall redundancy of the system, enhance the anti-interference ability and reliability of the network, and even if the satellites of a certain constellation fail, the satellites of other constellations can still maintain the continuity and stability of the communication network.

[0090] Step S506: Determine the satellite that provides satellite communication service for the terminal device according to the coverage information.

[0091] In the technical solution provided in step S506, determining the satellite that provides satellite communication services to the terminal device based on the coverage information includes: determining the coverage time period at the target time, and the satellite identifier corresponding to the coverage time period; determining the satellite that provides satellite communication services to the terminal device based on the satellite identifier.

[0092] Optionally, the ground base station searches for the satellite identifier at the corresponding moment according to the real-time time, selects the service satellite and notifies the terminal device to ensure that it always maintains a communication connection with the correct satellite to achieve seamless service.

[0093] Optionally, the method also includes determining orbital parameters of the satellite communication system based on coverage requirement information or interference avoidance requirement information, wherein the orbital parameters include at least one of the following: a preset orbital regression period, a preset angle between the orbital plane and the equatorial plane, a preset orbital shape, a preset position of the orbital sub-satellite point trajectory crossing the equator, a preset orientation of the orbital perigee in the orbit, and a preset position of the satellite in the orbit; generating an orbital adjustment instruction based on the orbital parameters, and determining a target satellite to receive the orbital adjustment instruction based on the coverage information; and sending the orbital adjustment instruction to the target satellite.

[0094] Optionally, for satellite communication constellations designed using regression orbits, the sub-satellite point trajectory has obvious regression and repetitive characteristics on the earth's surface, that is, the relative position of the satellite orbit and the ground gateway station or tracking and control station has repetitive characteristics. This characteristic can be used to simplify the on-orbit management of satellite constellations by ground stations. By arranging daily observation tables for ground stations, the ground stations can be controlled to periodically and automatically implement daily observation and control of satellite constellations, thereby improving the efficiency and reliability of constellation management.

[0095] Optionally, the ground base station determines the target satellite to receive the orbit adjustment instruction based on the coverage information or the interference avoidance requirement information. By analyzing the real-time coverage of the satellite constellation, the control center can identify the satellite currently responsible for the coverage of a specific area and the satellite that is about to enter the coverage of the area. First, the orbit parameter adjustment strategy is determined based on the demand analysis. For example, the determination of the preset orbit return period is intended to ensure that the satellite can return to the area where enhanced coverage or interference avoidance is required at a specific period by adjusting the semi-major axis of the orbit, thereby optimizing the continuity of service and the management of frequency resources. Based on this, the system sends an orbit adjustment instruction to the target satellite to instruct it to adjust according to the new orbit parameters. This process not only ensures that the ground station's observation and communication operations of the satellite are carried out according to the daily observation table, but also optimizes the satellite orbit in real time to cope with changes in coverage requirements and challenges of frequency interference, thereby improving the automation level, efficiency and reliability of constellation management.

[0096] Optionally, the orbital semi-major axis information of the satellite orbital plane is determined according to a preset orbital regression period; the orbital inclination angle of the satellite orbital plane is determined according to a preset angle; the orbital eccentricity of the satellite orbital plane is determined according to a preset orbital shape; the longitude parameters of the ascending node of the satellite orbital plane are determined according to a preset position where the orbital sub-satellite point trajectory crosses the equator; the argument of perigee of the satellite orbital plane is determined according to a preset azimuth; the true anomaly angle of the satellite orbital plane is determined according to a preset position of the satellite in orbit; and an orbital adjustment instruction is generated, wherein the orbital adjustment instruction carries the orbital semi-major axis information, the orbital inclination angle, the orbital eccentricity, the longitude parameters of the ascending node, the argument of perigee, and the true anomaly angle.

[0097] Optionally, the ground base station determines the orbital semi-major axis information of the satellite orbital plane according to the preset orbital regression period target. The periodic characteristics of the regression orbit determine the frequency of the satellite's repeated visits to a specific area on the ground, and the orbital semi-major axis is directly related to the orbital period. By calculating and adjusting the semi-major axis, it is possible to ensure that the satellite returns to the required area with the desired period. The layout of the satellite orbital plane is optimized according to the preset angle target between the orbital plane and the equatorial plane, that is, the orbital inclination. The setting of the orbital inclination can avoid excessive concentration of satellite orbits on the equator, reduce frequency interference, and ensure that the satellite can cover all latitude areas. The orbital eccentricity of the satellite orbital plane is determined according to the needs of the preset orbital shape. The orbital eccentricity determines whether the orbit is circular or elliptical, which is crucial to the signal transmission performance of the satellite. Assuming that the system requirement is a circular orbit to simplify operation and improve signal stability, the eccentricity will be set to zero. Conversely, if the requirement is an elliptical orbit to optimize coverage of a specific area, the eccentricity will be adjusted to a non-zero value. According to the preset position of the sub-satellite point track crossing the equator, the ascending node longitude parameter is adjusted to control the satellite's coverage track on the earth's surface. The ascending node longitude determines the position where the satellite's sub-satellite point track first crosses the equator. The precise setting of this parameter can ensure the best relative position of the satellite track and the ground gateway or hot spot area, thereby improving communication efficiency and quality. According to the preset azimuth, the perigee argument of the satellite orbit plane is determined. The perigee argument refers to the angular distance between the satellite orbit perigee and the ascending node. Adjustment of this parameter helps to optimize the link loss of signal transmission and can improve overall communication performance. Based on the preset position of the satellite in orbit, the true anomaly angle is set to accurately control the specific position of each satellite in orbit. The true anomaly angle is the position of the satellite in orbit relative to the perigee. By setting the appropriate true anomaly angle, the layout of the satellite constellation can be ensured to be uniform, conflicts between satellites can be avoided, and periodic coverage of the ground area can be achieved.

[0098] After all orbital parameters are determined, the ground base station generates an orbit adjustment command based on the new orbital parameters. This command contains all the necessary information for satellite orbit adjustment, including the new value of the orbit semi-major axis, the adjustment angle of the orbit inclination, the change in orbit eccentricity, the set value of the longitude of the ascending node, and the specific adjustment parameters of the perigee angle and true anomaly angle. The ground base station sends these commands to the target satellite to guide it to make orbit adjustments to optimize coverage and reduce frequency interference.

[0099] Optionally, a Warker constellation is constructed based on the above-mentioned regression orbit, and the delta configuration parameters are N / P / F, where N represents the total number of satellites, P represents the number of orbital planes, and F represents the phase difference of satellites in adjacent orbital planes, that is, the angle difference between corresponding satellites in adjacent orbital planes.

[0100] Through the above steps, a satellite constellation realization method based on a regression orbit can be realized. The regression characteristics of the satellite orbit are used to make the sub-satellite point trajectory of the satellite on the ground relatively fixed, which is convenient for the satellite to cover a specific area on the ground, and also convenient for the frequency interference strategy design with other satellite communication systems; at the same time, the constellation configuration is optimized, and global coverage is achieved with as few satellites as possible, reducing the cost of constellation construction and the difficulty of maintenance. By determining the location information of the terminal equipment and matching the coverage strategy of the regression orbit medium-orbit satellite constellation based on the information, the purpose of accurately positioning satellite services and optimizing satellite resource allocation is achieved, thereby achieving the technical effect of significantly reducing the construction and operation and maintenance efficiency of the satellite communication system while ensuring global coverage and service performance, thereby solving the technical problems of high construction cost, complex management and low service efficiency of the satellite communication system caused by the difficulty of traditional satellite communication methods in balancing the contradiction between coverage, number of satellites and business performance.

[0101] The present application embodiment provides a satellite communication device, Figure 6 is a schematic diagram of the structure of the device, such as Figure 6 As shown, the device includes: a first processing module 60, used to determine the location information of the terminal device, and determine the target area to which the terminal device belongs based on the location information; a second processing module 62, used to determine the coverage information of the satellite communication system for the target area, wherein the satellite communication system includes at least one constellation composed of a plurality of equally spaced satellite orbital planes, each satellite orbital plane has a preset number of satellites running, the orbital type of the satellite orbital plane is a regression orbit, and the satellite orbital plane is a medium-orbit satellite orbit, and the coverage information includes the coverage time period in which the target area is covered by the satellite communication system, and the satellite identifier corresponding to each coverage time period; a third processing module 64, used to determine the satellite that provides satellite communication services to the terminal device based on the coverage information.

[0102] In some embodiments of the present application, the third processing module 64 determines the satellite that provides satellite communication services to the terminal device based on the coverage information, including: determining the coverage time period at the target time, and the satellite identifier corresponding to the coverage time period; determining the satellite that provides satellite communication services to the terminal device based on the satellite identifier.

[0103] In some embodiments of the present application, the satellites operating on each satellite orbital plane include a first type of satellite and a second type of satellite, wherein the operating periods of the first type of satellites operating on each satellite orbital plane of the constellation relative to any position on the ground are the same, and the operating periods of the second type of satellites operating on each satellite orbital plane relative to any position on the ground are the same; in the case where a satellite communication system includes multiple constellations, the ascending node longitude parameters of each constellation are different, and the orbital inclination angles of each constellation are different, and each constellation is used to complement each other's coverage; or, the orbital inclination angles of each constellation are partially the same.

[0104] In some embodiments of the present application, the initial observation azimuth and the initial observation elevation angle corresponding to the first type of satellite are the same, and the observation time interval corresponding to any two first type of satellites in an adjacent observation order is a first preset time length; and the initial observation azimuth and the initial observation elevation angle corresponding to the second type of satellite are the same, and the observation time interval corresponding to any two second type of satellites in an adjacent observation order is a second preset time length.

[0105] In some embodiments of the present application, when the satellites operating on each satellite orbital plane are a first-category satellite and a second-category satellite, the phase difference between the first-category satellite and the second-category satellite operating on the same satellite orbital plane is 180°.

[0106] In some embodiments of the present application, orbital parameters of a satellite communication system are determined based on coverage requirement information or interference avoidance requirement information, wherein the orbital parameters include at least one of the following: a preset orbital regression period, a preset angle between the orbital plane and the equatorial plane, a preset orbital shape, a preset position of the orbital sub-satellite point trajectory crossing the equator, a preset orientation of the orbital perigee in the orbit, and a preset position of the satellite in the orbit; an orbital adjustment instruction is generated based on the orbital parameters, and a target satellite for receiving the orbital adjustment instruction is determined based on the coverage information; and the orbital adjustment instruction is sent to the target satellite.

[0107] In some embodiments of the present application, generating an orbit adjustment instruction based on orbit parameters includes: determining the orbital semi-major axis information of the satellite orbital plane based on a preset orbital regression period; determining the orbital inclination angle of the satellite orbital plane based on a preset angle; determining the orbital eccentricity of the satellite orbital plane based on a preset orbital shape; determining the longitude parameters of the ascending node of the satellite orbital plane based on a preset position where the orbital sub-satellite point trajectory crosses the equator; determining the perigee argument of the satellite orbital plane based on a preset azimuth; determining the true anomaly angle of the satellite orbital plane based on a preset position of the satellite in orbit; generating an orbit adjustment instruction, wherein the orbit adjustment instruction carries the orbital semi-major axis information, the orbital inclination angle, the orbital eccentricity, the longitude parameters of the ascending node, the perigee argument, and the true anomaly angle.

[0108] It should be noted that the various modules in the above-mentioned satellite communication device can be program modules (for example, a set of program instructions for implementing a certain specific function) or hardware modules. For the latter, it can be expressed in the following forms, but is not limited to this: the expression form of each of the above-mentioned modules is a processor, or the functions of each of the above-mentioned modules are implemented by a processor.

[0109] An embodiment of the present application provides a non-volatile storage medium, in which a program is stored, wherein when the program is running, the device where the non-volatile storage medium is located is controlled to execute the following satellite communication method: determine the location information of a terminal device, and determine the target area to which the terminal device belongs based on the location information; determine the coverage information of the satellite communication system for the target area, wherein the satellite communication system includes at least one constellation composed of a plurality of equally spaced satellite orbital planes, each satellite orbital plane has a preset number of satellites running on it, the orbital type of the satellite orbital plane is a recurrent orbit, and the satellite orbital plane is a medium-orbit satellite orbit, and the coverage information includes the coverage time period in which the target area is covered by the satellite communication system, and the satellite identifier corresponding to each coverage time period; determine the satellite that provides satellite communication services to the terminal device based on the coverage information.

[0110] An embodiment of the present application provides an electronic device, including: a memory and a processor, the processor being used to run a program stored in the memory, wherein the following satellite communication method is executed when the program is run: determining location information of a terminal device, and determining a target area to which the terminal device belongs based on the location information; determining coverage information of a satellite communication system for the target area, wherein the satellite communication system includes at least one constellation composed of a plurality of equally spaced satellite orbital planes, each satellite orbital plane having a preset number of satellites running on it, the orbital type of the satellite orbital plane being a recurrent orbit, and the satellite orbital plane being a medium-orbit satellite orbit, the coverage information including a coverage time period during which the target area is covered by the satellite communication system, and satellite identifiers corresponding to each coverage time period; and determining a satellite that provides satellite communication services to the terminal device based on the coverage information.

[0111] An embodiment of the present application provides a computer program product, including a computer program, which implements the following satellite communication method when executed by a processor: determining location information of a terminal device, and determining a target area to which the terminal device belongs based on the location information; determining coverage information of a satellite communication system for the target area, wherein the satellite communication system includes at least one constellation composed of a plurality of equally spaced satellite orbital planes, each satellite orbital plane has a preset number of satellites running on it, the orbital type of the satellite orbital plane is a recurrent orbit, and the satellite orbital plane is a medium-orbit satellite orbit, the coverage information includes a coverage time period during which the target area is covered by the satellite communication system, and satellite identifiers corresponding to each coverage time period; and determining a satellite that provides satellite communication services for the terminal device based on the coverage information.

[0112] In the above embodiments of the present application, the description of each embodiment has its own emphasis. For parts that are not described in detail in a certain embodiment, please refer to the relevant description of other embodiments.

[0113] In the several embodiments provided in this application, it should be understood that the disclosed technical content can be implemented in other ways. Among them, the device embodiments described above are only schematic. For example, the division of the units can be a logical function division. There may be other division methods in actual implementation. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of units or modules, which can be electrical or other forms.

[0114] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple units. Some or all of the units may be selected according to actual needs to achieve the purpose of the present embodiment.

[0115] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit. The above-mentioned integrated unit may be implemented in the form of hardware or in the form of software functional units.

[0116] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present application, or the part that contributes to the relevant technology or all or part of the technical solution, can be embodied in the form of a software product, which is stored in a storage medium and includes several instructions for a computer device (which can be a personal computer, a server or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present application. The aforementioned storage medium includes: U disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), mobile hard disk, disk or optical disk, etc. Various media that can store program codes.

[0117] The above is only a preferred implementation of the present application. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present application. These improvements and modifications should also be regarded as the scope of protection of the present application.

Claims

1. A satellite communication method, characterized in that: include: Determine the location information of the terminal device, and determine the target area to which the terminal device belongs based on the location information; Determining coverage information of a satellite communication system for the target area, wherein the satellite communication system includes at least one constellation consisting of a plurality of equally spaced satellite orbital planes, a preset number of satellites are running on each satellite orbital plane, the orbital type of the satellite orbital plane is a regression orbit, and the satellite orbital plane is a medium-orbit satellite orbit, and the coverage information includes a coverage time period during which the target area is covered by the satellite communication system, and satellite identifiers corresponding to each coverage time period; A satellite that provides satellite communication services for the terminal device is determined based on the coverage information.

2. The satellite communication method according to claim 1, characterized in that: The satellite that provides satellite communication services for the terminal device according to the coverage information includes: Determine the coverage time period of the target time and the satellite identifier corresponding to the coverage time period; A satellite that provides satellite communication services for the terminal device is determined based on the satellite identifier.

3. The satellite communication method according to claim 1, characterized in that: The satellites operating on each of the satellite orbital planes include first-category satellites and second-category satellites, wherein: The operation periods of the first-category satellites operating on each of the satellite orbital planes of the constellation relative to any position on the ground are the same, and the operation periods of the second-category satellites operating on each of the satellite orbital planes relative to any position on the ground are the same; In the case where the satellite communication system includes multiple constellations, the ascending node longitude parameters of each constellation are different, and the orbital inclination angles of each constellation are different, and each constellation is used to complement each other's coverage; or, the orbital inclination angles of each constellation are partially the same.

4. The satellite communication method according to claim 3, characterized in that: The initial observation azimuth angle and the initial observation elevation angle corresponding to the first type of satellites are the same, and the observation time interval corresponding to any two first type of satellites adjacent in observation order is a first preset time length; Furthermore, the initial observation azimuth angle and the initial observation elevation angle corresponding to the second-type satellites are the same, and the observation time interval corresponding to any two second-type satellites adjacent in the observation sequence is the second preset time length.

5. The satellite communication method according to claim 3, characterized in that: When the satellites operating on each of the satellite orbital planes are a first-category satellite and a second-category satellite, the phase difference between the first-category satellite and the second-category satellite operating on the same satellite orbital plane is 180°.

6. The satellite communication method according to claim 1, characterized in that: The method further comprises: Determining the orbital parameters of the satellite communication system according to the coverage requirement information or the interference avoidance requirement information, wherein the orbital parameters include at least one of the following: a preset orbital regression period, a preset angle between the orbital plane and the equatorial plane, a preset orbital shape, a preset position of the orbital sub-satellite point trajectory crossing the equator, a preset position of the orbital perigee in the orbit, and a preset position of the satellite in the orbit; generating an orbit adjustment instruction according to the orbit parameter, and determining a target satellite to receive the orbit adjustment instruction according to the coverage information; The orbit adjustment instruction is sent to the target satellite.

7. The satellite communication method according to claim 6, characterized in that: Generating a track adjustment instruction according to the track parameters includes: Determining orbital semi-major axis information of the satellite orbital plane according to the preset orbital regression period; Determining the orbital inclination angle of the satellite orbital plane according to the preset angle; Determining the orbital eccentricity of the satellite orbital plane according to the preset orbital shape; Determining the longitude parameter of the ascending node of the satellite orbit plane according to the preset position where the sub-satellite point trajectory crosses the equator; Determining the perigee argument of the satellite orbital plane according to the preset azimuth; Determining the true anomaly of the satellite orbital plane according to a preset position of the satellite in the orbit; Generate the orbit adjustment instruction, wherein the orbit adjustment instruction carries the orbit semi-major axis information, the orbit inclination angle, the orbit eccentricity, the ascending node longitude parameter, the perigee argument, and the true anomaly angle.

8. A satellite communication system, characterized in that: Including terminal equipment, ground base stations and satellites, including: The ground base station is used to determine the location information of the terminal device, and determine the target area to which the terminal device belongs based on the location information; determine the coverage information of the satellite communication system relative to the target area; and determine the satellite that provides satellite communication services for the terminal device based on the coverage information; The satellite communication system also includes at least one constellation composed of a plurality of equally spaced satellite orbital planes, a preset number of satellites are operating on each satellite orbital plane, the orbital type of the satellite orbital plane is a regression orbit, and the satellite orbital plane is a medium-orbit satellite orbit, and the coverage information includes the coverage time period during which the target area is covered by the satellite communication system, and the satellite identifiers corresponding to each coverage time period.

9. A satellite communication device, characterized in that: include: A first processing module, used to determine the location information of the terminal device, and determine the target area to which the terminal device belongs according to the location information; A second processing module is used to determine coverage information of the satellite communication system for the target area, wherein the satellite communication system includes a plurality of equally spaced satellite orbital planes, each satellite orbital plane has a preset number of satellites running on it, the orbital type of the satellite orbital plane is a regression orbit, and the satellite orbital plane is a medium-orbit satellite orbit, and the coverage information includes a coverage time period during which the target area is covered by the satellite communication system, and a satellite identifier corresponding to each coverage time period; The third processing module is used to determine the satellite that provides satellite communication services for the terminal device according to the coverage information.

10. A non-volatile storage medium, characterized in that: The non-volatile storage medium stores a program, wherein when the program is executed, the device where the non-volatile storage medium is located is controlled to execute the satellite communication method according to any one of claims 1 to 7.

11. An electronic device, characterized in that: include: A memory and a processor, wherein the processor is used to run a program stored in the memory, wherein the program executes the satellite communication method according to any one of claims 1 to 7 when running.

12. A computer program product, characterized in that The invention comprises a computer program which, when executed by a processor, implements the satellite communication method according to any one of claims 1 to 7.

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