Inter-satellite switching method and system for low-orbit satellites

Abstract

The invention relates to the technical field of low-earth-orbit satellite communication, and discloses a low-earth-orbit satellite inter-satellite switching method and system, which can realize an inter-satellite soft switching function of a terminal without interruption of services during inter-satellite switching. The method comprises the following steps: determining a tracked source satellite, wherein a main lobe beam coverage range maximally covers an orbit where the source satellite is located in a terminal view field; a tracked target satellite is determined, when a source satellite tracked by the terminal is switched to the target satellite, mechanical servo rotation enables the source satellite and the target satellite to be always located in the coverage range of a main lobe beam during inter-satellite switching, and the coverage range of the main lobe beam crosses the orbit of the source satellite and the orbit of the target satellite; the orbit inclination angle of the source satellite and the target satellite is larger than 75 degrees. The terminal establishes connection with a source satellite and a target satellite and completes switching, and mechanical servo rotation enables a main lobe beam coverage range to maximally cover an orbit where the target satellite is located in a terminal view field.

Description

Technical Field

[0001] The present application relates to the field of low-orbit satellite communication technology, and in particular to a low-orbit satellite inter-satellite switching method and system. Background Art

[0002] This section is intended to provide a background or context to the embodiments of the present application as recited in the claims. The description herein is not admitted to be prior art as disclosed by virtue of its inclusion in this section.

[0003] Today, the construction of large-scale low-orbit broadband satellite communication systems is becoming increasingly mature. Its advantages of low latency, large bandwidth, and wide coverage can make up for the lack of coverage of existing broadband mobile communication systems in oceans, deserts, and sparsely populated areas. The construction of a communication network system that integrates the sky and the earth has become an inevitable trend in the future.

[0004] However, the user terminals of low-orbit broadband satellite communication systems on the market are expensive, mainly because they use a large number of two-dimensional phased array antenna elements and high related chip costs, which objectively leads to the low-orbit satellite communication terminals not being popularized.

[0005] In order to successfully commercialize the low-orbit broadband satellite communication system and bring low-orbit satellite communication terminals into thousands of households, one of the important issues that need to be resolved is the terminal cost control issue. Another important issue that needs to be resolved is that it is difficult for the terminal to support the inter-satellite soft switching function, and the service will be temporarily interrupted when an inter-satellite switching occurs. Summary of the invention

[0006] The purpose of the present application is to provide a low-orbit satellite inter-satellite switching method and system, which can realize the inter-satellite soft switching function of the terminal, and the service will not be interrupted during the inter-satellite switching.

[0007] The present application discloses a low-orbit satellite inter-satellite switching method, comprising:

[0008] Determine the source satellite to be tracked, and the main lobe beam coverage range maximizes the coverage of the orbit where the source satellite is located within the terminal field of view;

[0009] Determine a target satellite to be tracked, when the source satellite tracked by the terminal switches to the target satellite, the mechanical servo rotates so that the source satellite and the target satellite are always located within the coverage of the main lobe beam during inter-satellite switching, the coverage of the main lobe beam spans the orbit of the source satellite and the orbit of the target satellite, and the orbital inclinations of the source satellite and the target satellite are greater than 75°;

[0010] The terminal establishes connection with the source satellite and the target satellite and completes switching, and the mechanical servo rotation maximizes the coverage of the main lobe beam to cover the orbit where the target satellite is located within the terminal's field of view.

[0011] In a preferred example, it also includes: the mechanical servo rotates from east to west in a direction perpendicular to the satellite orbit to compensate for orbit drift.

[0012] In a preferred example, it also includes: cooperating with the one-dimensional phased array antenna to adjust the beam direction so that the source satellite is always located at the center of the antenna main lobe of the terminal, and the main lobe beam coverage always covers the orbit where the source satellite is located.

[0013] In a preferred example, it also includes: calculating the one-dimensional phased array antenna index of the terminal according to the link budget in each service scenario.

[0014] In a preferred example, it also includes: determining the target satellite to be tracked and the algorithm and parameters for switching between the target satellites based on the indicator.

[0015] In a preferred example, when the current service satellite is not the last satellite on a certain orbital plane that meets the continuous service duration requirement, and the satellite will leave the field of view of the terminal in x seconds, it is set as the source satellite;

[0016] Setting an adjacent satellite on the orbit of the source satellite that enters the terminal field of view after the source satellite as the target satellite;

[0017] Starting from x seconds before the source satellite leaves the terminal's field of view, the beam direction is changed through a one-dimensional phased array antenna to establish connections with the source satellite and the target satellite in a time-division manner until the switching process is completed.

[0018] In a preferred example, when the current service satellite is the last satellite on a certain orbital plane that meets the continuous service duration requirement, and the satellite will leave the terminal field of view in x seconds, it is set as the source satellite;

[0019] The satellite that last enters the terminal's field of view on an orbit adjacent to the orbit where the source satellite is located is set as the target satellite;

[0020] Starting from x seconds before the source satellite leaves the terminal's field of view, the one-dimensional phased array antenna is connected to the source satellite and the target satellite in a time-division manner by rotating the mechanical servo until the switching process is completed.

[0021] In a preferred embodiment, the scanning range of the terminal beam along the long axis direction of the antenna field of view reaches 80°-180°;

[0022] The mechanical servo rotates in the direction along which the satellite moves, and the rotation angle range in this direction reaches 20-180°.

[0023] The present application also discloses a low-orbit satellite inter-satellite switching system, comprising:

[0024] a memory for storing computer executable instructions; and,

[0025] A processor, coupled to the memory, is configured to implement the steps in the method described above when executing the computer executable instructions.

[0026] The present application also discloses a computer-readable storage medium, in which computer-executable instructions are stored. When the computer-executable instructions are executed by a processor, the steps in the method described above are implemented.

[0027] In the implementation manner of the present application, the one-dimensional phased array antenna of the terminal is used in conjunction with the two-dimensional mechanical servo. During inter-satellite switching, the source satellite and the target satellite are always in the main lobe beam coverage range by rotating the mechanical servo, realizing a two-dimensional airspace scanning similar to that of a two-dimensional phased array antenna that combines electronic scanning with mechanical scanning. The field of view direction of the one-dimensional phased array antenna is rotated in a timely manner to realize functions such as satellite tracking, intra-orbit inter-satellite switching, and inter-orbit inter-satellite switching. Therefore, by adopting the implementation manner of the present application, the service will not be interrupted during inter-satellite switching.

[0028] Furthermore, by using one-dimensional phased array antennas, the number of array elements and phase shifters is significantly reduced compared to two-dimensional phased array antennas, and the cost of antenna array surface is significantly reduced. By using one-dimensional electronically scanned terminals in conjunction with constellations at lower orbital altitudes and designing appropriate beam scanning algorithms that combine mechanical and electronic scanning, the use of one-dimensional phased array antennas can reduce terminal costs while ensuring that service availability and continuity are not affected.

[0029] Each technical feature disclosed in the above invention content, each technical feature disclosed in each implementation mode and example below, and each technical feature disclosed in the accompanying drawings can be freely combined with each other to form various new technical solutions (these technical solutions should be deemed to have been recorded in this specification), unless such combination of technical features is technically infeasible. For example, in one example, feature A+B+C is disclosed, and in another example, feature A+B+D+E is disclosed, and features C and D are equivalent technical means that play the same role. Technically, only one of them can be used, and it is impossible to use them at the same time. Feature E can be combined with feature C technically. Then, the solution of A+B+C+D should not be deemed to have been recorded because it is technically infeasible, while the solution of A+B+C+E should be deemed to have been recorded. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 is a flowchart of a low-orbit satellite inter-satellite switching method according to an embodiment of the present application;

[0031] Figure 2 is a flowchart of a low-orbit satellite inter-satellite switching method according to an embodiment of the present application;

[0032] Figure 3 is a flowchart of a low-orbit satellite inter-satellite switching method according to an embodiment of the present application;

[0033] Figures 4 to 9 It is a schematic diagram of a satellite-to-ground communication scenario corresponding to a low-orbit satellite inter-satellite switching method according to an embodiment of the present application;

[0034] Fig.10 It is a corresponding array design diagram of a low-orbit satellite inter-satellite switching method according to an embodiment of the present application;

[0035] Fig.11 The antenna pattern of the one-dimensional phased array antenna corresponding to the low-orbit satellite inter-satellite switching method according to one embodiment of the present application when the main lobe points to the normal direction of the array surface;

[0036] Fig.12 The antenna pattern of the one-dimensional phased array antenna corresponding to the low-orbit satellite inter-satellite switching method according to one embodiment of the present application when the main lobe points to an off-axis angle of 47°; DETAILED DESCRIPTION

[0037] In the following description, many technical details are provided to help readers better understand the present application. However, those skilled in the art can understand that the technical solution claimed in the present application can be implemented even without these technical details and various changes and modifications based on the following embodiments.

[0038] Description of some concepts:

[0039] Main lobe: It is the largest radiation beam on the antenna pattern. The pattern usually has two or more lobes, of which the lobe with the strongest radiation intensity is called the main lobe, and the remaining lobes are called secondary lobes or side lobes. The side lobes in the opposite direction of the main lobe are called back lobes.

[0040] Phased array antenna: A phased array antenna is an antenna that changes the shape of the radiation pattern by controlling the feeding phase of the radiating elements in the array antenna. Controlling the phase can change the direction of the maximum value of the antenna radiation pattern to achieve the purpose of beam scanning. In special cases, the sidelobe level, the minimum position and the shape of the entire radiation pattern can also be controlled, such as obtaining a cosecant square radiation pattern and adaptively controlling the radiation pattern. When the antenna is rotated mechanically, the inertia is large and the speed is slow. The phased array antenna overcomes this shortcoming and has a high beam scanning speed. Its feeding phase is generally controlled by an electronic computer, and the phase changes quickly (milliseconds), that is, the maximum value direction of the antenna radiation pattern or other parameters change rapidly. This is the biggest feature of the phased array antenna.

[0041] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below in conjunction with the accompanying drawings.

[0042] The first embodiment of the present application relates to a low-orbit satellite inter-satellite handover method, the process of which is as follows: Figure 1 As shown, the method comprises the following steps:

[0043] In step 101, the source satellite to be tracked is determined, and the main lobe beam coverage maximizes the coverage of the orbit where the source satellite is located within the terminal field of view;

[0044] In step 102, a target satellite to be tracked is determined. When the source satellite tracked by the terminal is switched to the target satellite, the mechanical servo is rotated so that the source satellite and the target satellite are always located within the coverage of the main lobe beam during inter-satellite switching. The coverage of the main lobe beam spans the orbit of the source satellite and the orbit of the target satellite. The orbital inclinations of the source satellite and the target satellite are greater than 75°.

[0045] In step 103, the terminal establishes connection with the source satellite and the target satellite and completes the switching, and the mechanical servo rotates to maximize the coverage of the main lobe beam to cover the orbit of the target satellite within the terminal's field of view.

[0046] In an optional embodiment, it may also include: the mechanical servo rotates from east to west in a direction perpendicular to the satellite orbit to compensate for orbit drift.

[0047] In an optional embodiment, it may also include: cooperating with the one-dimensional phased array antenna to adjust the beam direction so that the source satellite is always located at the center of the terminal's antenna main lobe, and the main lobe beam coverage always covers the orbit where the source satellite is located.

[0048] In an optional embodiment, the method may further include: calculating a one-dimensional phased array antenna indicator of the terminal according to a link budget in each service scenario.

[0049] In an optional embodiment, the method may further include: determining the target satellite to be tracked and the algorithm and parameters for switching between target satellites according to the indicator.

[0050] In an optional embodiment, in step 201, when the current service satellite is not the last satellite on a certain orbital plane that meets the continuous service duration requirement and the satellite will leave the field of view of the terminal in x seconds, it is set as the source satellite;

[0051] In step 202, an adjacent satellite on the orbit of the source satellite that enters the terminal field of view after the source satellite is set as a target satellite;

[0052] In step 203, starting from x seconds before the source satellite leaves the terminal's field of view, the beam pointing is changed by the one-dimensional phased array antenna, and connections are established with the source satellite and the target satellite in a time-division manner until the switching process is completed. Optionally, x seconds is calculated according to the switching strategy and process of different devices, and the corresponding time is different for different devices. In this embodiment, 10 seconds is preferred.

[0053] In an optional embodiment, in step 301, when the current service satellite is the last satellite on a certain orbital plane that meets the continuous service duration requirement and the satellite will leave the terminal field of view in x seconds, it is set as the source satellite;

[0054] In step 302, the satellite that last enters the terminal's field of view on the adjacent orbit of the orbit where the source satellite is located is set as the target satellite;

[0055] In step 303, starting from x seconds before the source satellite leaves the terminal's field of view, the one-dimensional phased array antenna is connected to the source satellite and the target satellite in a time-division manner by rotating the mechanical servo until the switching process is completed. Optionally, x seconds is calculated based on the switching strategy and process of different devices, and the corresponding time is different for different devices. In this embodiment, 10 seconds is preferred.

[0056] In an optional embodiment, the scanning range of the terminal's beam along the long axis direction of the antenna's field of view reaches 80°-180°, and the mechanical servo rotates in the direction of the satellite's movement, and the rotation angle range in this direction reaches 20-180°. Preferably, the scanning range of the terminal's beam along the long axis direction of the antenna's field of view reaches at least 88°. Preferably, the mechanical servo rotates in the direction of the satellite's movement, and the rotation angle range in this direction reaches at least 22°. Optionally, the scanning range of the terminal's beam along the long axis direction of the antenna's field of view and the rotation angle range of the mechanical servo rotating in the direction of the satellite's movement are adjusted accordingly according to the switching strategies and processes of different devices. Different devices have different corresponding scanning ranges and rotation angle ranges.

[0057] In order to better understand the technical solution of the present application, a specific example is provided below for illustration. The details listed in the example are mainly for ease of understanding and are not intended to limit the scope of protection of the present application.

[0058] According to a certain low-orbit satellite constellation design and terminal position, the satellite moves on a high-inclination orbit that is close to a polar orbit (orbital inclination > 75°); the terminal is set at 121°E, 31°N, and the antenna array axis is perpendicular to the ground section. Determine the airspace range that the terminal antenna field of view should cover in a non-switching scenario. This range is to ensure that the terminal can stably track the source satellite, and in an intra-orbit inter-satellite soft switching scenario, to ensure that the terminal antenna field of view can simultaneously cover the same orbital arc segment where the source satellite and the target satellite are located.

[0059] Since the maximum off-axis angle of the satellite payload is 53°, in order to maximize the satellite's service time, the satellite should enter the terminal's electronic scanning range at the same time as the terminal enters the satellite payload's field of view. Figure 4 As shown in the figure, at a certain moment, there are 5 satellites in the field of view of the satellite, belonging to 2 different orbital planes. Optionally, when the satellite enters and leaves the field of view of the terminal antenna, it moves roughly from north to south. The main lobe of the terminal's one-dimensional phased array antenna always stares at the satellite, and the beam scans an angle range of about 93° along the direction of satellite movement.

[0060] Due to the rotation of the earth, the position of the satellite orbital plane and the terminal keeps changing. Figures 4 to 7 The relative change shown. According to the orbital drift speed of the constellation, the rotation direction and angular velocity of the mechanical servo are calculated to track the orbit, compensate for the orbital drift, and overlap the orbital moment with the antenna field of view. Optionally, the mechanical servo rotates from east to west in a direction almost perpendicular to the satellite orbit at an angular velocity of about 0.027° / second to compensate for the orbital drift. At the same time, in conjunction with the beam direction adjustment of the one-dimensional phased array antenna, the source satellite is always located at the center of the main lobe of the terminal antenna, and the narrow elliptical field of view of the antenna always covers the orbital plane where the service satellite is located.

[0061] Due to the rotation of the earth, when all satellites on a certain orbital plane cannot be visible to the terminal, in order to ensure service continuity, the following operations are required: Figures 7 and 8 The cross-orbit inter-satellite switching shown, that is, switching from a source satellite to a target satellite on another orbital plane, simultaneously establishes connections with the source satellite and the target satellite within a certain period of time when the switching occurs, and disconnects the connection with the source satellite after the switching is completed.

[0062] According to the constellation design, terminal position and intersatellite soft switching process, determine the scanning angle range of the terminal antenna field of view in the long axis direction and the rotation angle range of the mechanical servo in the cross-orbit intersatellite soft switching scenario to ensure that the source satellite and the target satellite appear in the narrow elliptical field of view of the terminal antenna at the same time. In order to make the source satellite and the target satellite simultaneously located at both ends of the terminal's field of view, the terminal's beam scanning range along the long axis direction of the antenna field of view should be at least about 88°. At the same time, the mechanical servo can rotate at a certain angular velocity in the direction of the satellite's movement, and the rotation angle range in this direction should be at least 22° to ensure that the source satellite and the target satellite will not leave the terminal antenna field of view before the switching is completed.

[0063] According to the constellation design and the terminal position, the rotation angle range of the mechanical servo after the inter-orbital handover is completed is determined, so that the antenna field of view rotates from the position spanning the orbit of the source satellite and the orbit of the target satellite to the position covering the orbit of the target satellite. Figures 8 to 9 shown.

[0064] According to the constellation design, network element performance indicators, communication environment factors and system performance requirements, determine the communication link budget required for the above-mentioned business scenarios, especially when the terminal antenna beam angle reaches the scanning range limit, and calculate the gain, transmission power and other indicators that the terminal's one-dimensional phased array antenna should achieve based on this. When using the DVB (Digital Video Broadcasting) communication system and requiring the link availability to reach more than 90%, the terminal's equivalent radiated power EIRP (Effective Isotropic Radiated Power) in the direction of the maximum beam off-axis angle should reach 23.9dBW, and the antenna gain G should reach 28.6dBi. Combined with the terminal's requirements for EIRP and G, according to the mission requirements, design as follows Fig.10 The 40×2 phased array antenna shown in the figure has an operating wavelength of 2.73 cm and a half-wavelength spacing between adjacent antennas. The antenna can only change the beam direction along the long side of the array. Each array element is an isotropic array element, and the gain of a single array element is 4dBi. The antenna radiation pattern of the antenna when the main lobe beam is pointing to the normal direction of the array face and the off-axis angle is 47° is as follows: Fig.11 and Fig.12 shown.

[0065] Based on the performance indicators of the terminal antenna, constellation design, terminal position and inter-satellite soft switching process, the strategy and specific parameters for the terminal to continuously track the service satellite and perform cross-orbit inter-satellite switching are determined, including the beam tracking strategy combined with mechanical scanning, the selection of switching time, the selection of switching target satellites, and the corresponding electronic scanning and mechanical scanning algorithms.

[0066] Optionally, according to the constellation design and mission requirements, the inter-satellite switching strategy within the orbital plane is designed as follows: when the current service satellite is not the last satellite on a certain orbital plane that meets the continuous service time requirement, and the satellite will leave the terminal's field of view in 10 seconds, it will be set as the switching source satellite. The adjacent satellite on the orbit where the source satellite is located and that enters the terminal's field of view after the source satellite is set as the switching target satellite. Starting 10 seconds before the source satellite leaves the terminal's field of view, the beam pointing is changed through the one-dimensional phased array antenna, and connections are established with the source satellite and the target satellite in a time-division manner until the soft switching process is completed. During this process, the mechanical servo rotates accordingly to ensure that the field of view of the one-dimensional phased array antenna always covers the orbital plane. At this point, the inter-satellite switching within the orbital plane is completed. The overall process is as follows Figures 4 to 6 shown.

[0067] Optionally, according to the constellation design and mission requirements, the inter-orbital switching strategy is designed as follows: when the current service satellite is the last satellite on a certain orbital plane that meets the continuous service time requirements, and the satellite will leave the terminal's field of view in 10 seconds, it is set as the switching source satellite. The satellite that last enters the terminal's field of view on the adjacent orbit of the orbit where the source satellite is located is set as the switching target satellite. Starting 10 seconds before the source satellite leaves the terminal's field of view, the one-dimensional phased array antenna can establish connections with the source satellite and the target satellite in time by rotating the mechanical servo until the soft switching process ends. During this process, the mechanical servo rotates accordingly to ensure that the source satellite and the target satellite never leave the field of view of the one-dimensional phased array antenna. After the soft switching process ends, the terminal rotates the mechanical servo so that the narrow field of view of the one-dimensional phased array antenna covers the orbital plane where the target satellite is located. At this point, the inter-orbital switching is completed. The overall process is as follows Figures 7 to 9 shown.

[0068] A second embodiment of the present application relates to a low-orbit satellite inter-satellite switching system, which includes a memory for storing computer-executable instructions; and a processor coupled to the memory for implementing any step in the above method when executing the computer-executable instructions.

[0069] The first implementation manner is a method implementation manner corresponding to the present implementation manner. The technical details in the first implementation manner can be applied to the present implementation manner, and the technical details in the present implementation manner can also be applied to the first implementation manner.

[0070] Accordingly, the embodiments of the present application also provide a computer-readable storage medium, in which computer executable instructions are stored, and when the computer executable instructions are executed by the processor, the various method embodiments of the present application are implemented. Computer-readable storage media include permanent and non-permanent, removable and non-removable media, and information storage can be implemented by any method or technology. Information can be a computer-readable instruction, a data structure, a module of a program, or other data. Examples of computer storage media include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technology, read-only compact disk read-only memory (CD-ROM), digital versatile disk (DVD) or other optical storage, magnetic cassettes, disk storage or other magnetic storage devices or any other non-transmission media that can be used to store information that can be accessed by a computing device. As defined herein, computer-readable storage media does not include temporary computer-readable media (transitory media), such as modulated data signals and carriers.

[0071] It should be noted that, in the present application, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply that there is any such actual relationship or order between these entities or operations. Moreover, the term "include", "comprise" or any other variant thereof is intended to cover non-exclusive inclusion, so that the process, method, article or equipment including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or equipment. In the absence of more restrictions, the elements defined by the sentence "include one" do not exclude the existence of other identical elements in the process, method, article or equipment including the elements. In the present application, if it is mentioned that a certain action is performed according to a certain element, it means at least the meaning of performing the action according to the element, which includes two situations: performing the action only according to the element and performing the action according to the element and other elements. Multiple, multiple, multiple, etc. expressions include 2, 2 times, 2 kinds and more than 2, more than 2 times, more than 2 kinds.

[0072] The serial numbers used in describing the steps of the method do not themselves constitute any limitation on the order of these steps. For example, the step with a larger serial number does not necessarily have to be executed after the step with a smaller serial number. The step with a larger serial number may be executed first and then the step with a smaller serial number. They may also be executed in parallel, as long as this execution order is reasonable for those skilled in the art. For another example, multiple steps with consecutive serial numbers (e.g., step 101, step 102, step 103, etc.) do not limit other steps that can be executed in between. For example, there may be other steps between step 101 and step 102.

[0073] This specification includes combinations of the various embodiments described herein. Individual references to embodiments (e.g., "one embodiment" or "some embodiments" or "preferred embodiments"); however, these embodiments are not mutually exclusive unless indicated as mutually exclusive or it is clear to a person skilled in the art that they are mutually exclusive. It should be noted that the word "or" is used in this specification in a non-exclusive sense unless the context clearly indicates or requires otherwise.

[0074] All documents mentioned in this specification are considered to be included in the disclosure of this application as a whole, so that they can be used as a basis for modification when necessary. In addition, it should be understood that the above is only a preferred embodiment of this specification and is not intended to limit the scope of protection of this specification. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of one or more embodiments of this specification should be included in the scope of protection of one or more embodiments of this specification.

[0075] In some cases, the actions or steps described in the claims may be performed in a different order than in the embodiments and still achieve the desired results. In addition, the processes depicted in the drawings do not necessarily require the specific order or sequential order shown to achieve the desired results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.

Claims

1. A low-orbit satellite inter-satellite handover method, characterized in that: include: Determine the source satellite to be tracked, and the main lobe beam coverage range maximizes the coverage of the orbit where the source satellite is located within the terminal field of view; Determine a target satellite to be tracked, when the source satellite tracked by the terminal switches to the target satellite, the mechanical servo rotates so that the source satellite and the target satellite are always located within the coverage of the main lobe beam during inter-satellite switching, the coverage of the main lobe beam spans the orbit of the source satellite and the orbit of the target satellite, and the orbital inclinations of the source satellite and the target satellite are greater than 75°; The terminal establishes connection with the source satellite and the target satellite and completes switching, and the mechanical servo rotation maximizes the coverage of the main lobe beam to cover the orbit where the target satellite is located within the terminal's field of view.

2. The low-orbit satellite inter-satellite switching method according to claim 1, characterized in that: Also includes: The mechanical servo rotates from east to west in a direction perpendicular to the satellite orbit to compensate for orbital drift.

3. The low-orbit satellite inter-satellite switching method according to claim 1, characterized in that: Also includes: The beam direction of the one-dimensional phased array antenna is adjusted so that the source satellite is always located at the center of the antenna main lobe of the terminal, and the coverage range of the main lobe beam always covers the orbit where the source satellite is located.

4. The low-orbit satellite inter-satellite switching method according to claim 1, characterized in that: Also includes: According to the link budget in each service scenario, the one-dimensional phased array antenna index of the terminal is calculated.

5. The low-orbit satellite inter-satellite switching method according to claim 4, characterized in that: Also includes: According to the indicator, the target satellite to be tracked and the algorithm and parameters for switching between the target satellites are determined.

6. The low-orbit satellite inter-satellite switching method according to claim 1, characterized in that: When the current service satellite is not the last satellite on a certain orbital plane that meets the continuous service duration requirement, and the satellite will leave the field of view of the terminal in x seconds, the current service satellite is set as the source satellite; Setting an adjacent satellite on the orbit of the source satellite that enters the terminal field of view after the source satellite as the target satellite; Starting from x seconds before the source satellite leaves the terminal's field of view, the beam direction is changed through a one-dimensional phased array antenna to establish connections with the source satellite and the target satellite in a time-division manner until the switching process is completed.

7. The low-orbit satellite inter-satellite switching method according to claim 1, characterized in that: When the current service satellite is the last satellite on a certain orbital plane that meets the continuous service duration requirement, and the satellite will leave the terminal's field of view in x seconds, the current service satellite is set as the source satellite; The satellite that last enters the terminal field of view on the adjacent orbit of the orbit where the source satellite is located is set as the target satellite; Starting from x seconds before the source satellite leaves the terminal's field of view, the one-dimensional phased array antenna is connected to the source satellite and the target satellite in a time-division manner by rotating the mechanical servo until the switching process is completed.

8. The low-orbit satellite inter-satellite switching method according to claim 1, characterized in that: The scanning range of the terminal beam along the long axis direction of the antenna field of view reaches 80°-180°; The mechanical servo rotates in the direction along which the satellite moves, and the rotation angle range in this direction reaches 20-180°.

9. A low-orbit satellite intersatellite switching system, characterized in that: include: A memory for storing computer executable instructions; as well as, A processor, coupled to the memory, configured to implement the steps of the method according to any one of claims 1 to 8 when executing the computer executable instructions.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores computer-executable instructions, and when the computer-executable instructions are executed by a processor, the steps in the method according to any one of claims 1 to 8 are implemented.

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