Low-orbit satellite communication method, system and device and readable storage medium

Abstract

The embodiment of the invention provides a low-orbit satellite communication method, system and device and a readable storage medium. Sending a to-be-tested data packet to a transit satellite through a low-orbit satellite communication module under the condition of multiple antenna included angles, and receiving a test result of the to-be-tested data packet; based on the test result, determining the signal intensity of different data frames under the condition of different antenna included angles; fitting the data frame format and the signal intensity, determining a corresponding transmission success rate, and establishing a transmission mapping relationship among the satellite number, the antenna included angle, the transmission success rate, the data frame format and the signal intensity of the transit satellite; and determining a target transmission satellite based on the transmission mapping relationship according to the to-be-transmitted data and the transmission optimization target corresponding to the to-be-transmitted data, and transmitting the to-be-transmitted data through the target transmission satellite. According to the method provided by the embodiment of the invention, the reliability and efficiency of low-orbit satellite Internet of Things communication are improved.

Description

Technical Field

[0001] This application belongs to the field of communication technology, and in particular relates to a low-orbit satellite communication method, system, device and readable storage medium. Background Technology

[0002] With the development of satellite communication, the development of technologies such as satellite-ground network convergence and direct terminal connection to satellite has triggered a revolution in satellite Internet of Things (IoT). On the satellite IoT end side, low-orbit satellites are the mainstream development direction due to their flexible data transmission methods, large access capacity, and low power consumption.

[0003] In the existing technology, the evaluation of the actual network communication performance of low-Earth orbit satellite modules mainly relies on manual operation. However, manual operation leads to low testing efficiency and poor testing results. It is also difficult to adaptively adjust the antenna angle of the ground test equipment to adapt to satellites passing over at different elevation angles. The testing results are easily affected by the ground antenna angle, which limits the testing range and makes it difficult to meet the needs of low-Earth orbit satellite communication actual network performance evaluation. Summary of the Invention

[0004] This application provides a low-Earth orbit satellite communication method, system, device, and readable storage medium, which can enrich test scenarios and test data, thereby improving the efficiency and effectiveness of low-Earth orbit satellite performance evaluation and increasing the data transmission success rate in practical applications.

[0005] In a first aspect, embodiments of this application provide a low-Earth orbit satellite communication method, the method comprising: The test data packets are sent to the overpassing satellite under various antenna angle conditions through the low-orbit satellite communication module, and the test results of the test data packets are received. The test data packets include data frames with different data frame formats. Based on the test results, the signal strength of different data frames under different antenna angles was determined; The data frame format and signal strength are fitted to determine the corresponding transmission success rate, and a transmission mapping relationship is established between the satellite number, antenna angle, transmission success rate, data frame format and signal strength of the overpassing satellite. Based on the data to be transmitted and the corresponding transmission optimization target, the target transmission satellite is determined based on the transmission mapping relationship, and the data to be transmitted is transmitted through the target transmission satellite.

[0006] Secondly, embodiments of this application provide a low-Earth orbit satellite communication system, the system comprising: The power supply circuit, including a first sub-power supply circuit, a second sub-power supply circuit and a third sub-power supply circuit, is used to power on the low-Earth orbit satellite communication system. The main control circuit is connected to the first sub-power supply circuit. The communication interface circuit, connected in parallel with the main control circuit to the first sub-power supply circuit, is used to communicate with external devices; The low-orbit satellite communication module, connected to the second sub-power circuit, is used to send data packets to be tested to the passing satellite under various antenna angle conditions. The data packets to be tested include data frames with different data frame formats. Antenna array, comprising multiple antennas set at different preset angles; The radio frequency switch, connected to the third sub-power supply circuit, is used to control each antenna in the antenna array; The main control circuit is configured to: receive the test results of the data packet to be tested, determine the signal strength of different data frames under different antenna angles based on the test results, fit the data frame format and signal strength, determine the corresponding transmission success rate, and establish the transmission mapping relationship between the satellite number, antenna angle, transmission success rate, data frame format and signal strength of the passing satellite. Based on the data to be transmitted received by the communication interface circuit and the corresponding transmission optimization target, the target transmission satellite is determined based on the transmission mapping relationship, and the data to be transmitted is transmitted through the target transmission satellite.

[0007] Thirdly, embodiments of this application provide a low-Earth orbit satellite communication device, comprising: The communication module is used to send data packets to be tested to the passing satellite under various antenna angle conditions through the low-orbit satellite communication module, and to receive the test results of the data packets to be tested. The data packets to be tested include data frames of different data frame formats. The test module is used to determine the signal strength of different data frames under different antenna angles based on the test results. The fitting module is used to fit the data frame format and signal strength, determine the corresponding transmission success rate, and establish the transmission mapping relationship between the satellite number, antenna angle, transmission success rate, data frame format and signal strength of the overpassing satellite. The transmission module is used to determine the target transmission satellite based on the transmission mapping relationship according to the data to be transmitted and the corresponding transmission optimization target, and then transmit the data to be transmitted through the target transmission satellite.

[0008] Fourthly, embodiments of this application provide a terminal device, the device including: a processor and a memory storing computer program instructions; the processor reads and executes the computer program instructions to implement the low-Earth orbit satellite communication method as described in the first aspect.

[0009] Fifthly, embodiments of this application provide a computer storage medium storing computer program instructions, which, when executed by a processor, implement the low-Earth orbit satellite communication method as described in the first aspect.

[0010] In a sixth aspect, embodiments of this application provide a computer program product, including a computer program that, when executed, implements the low-Earth orbit satellite communication method as described in the first aspect.

[0011] The low-Earth orbit (LEO) satellite communication method, system, apparatus, and readable storage medium of this application transmit test data packets to passing satellites under various antenna angle conditions via a LEO satellite communication module and receive test results of the test data packets. The test data packets include data frames with different data frame formats. Based on the test results, the signal strength of different data frames under different antenna angle conditions is determined. Testing data frames with different formats under different antenna angle conditions covers multi-dimensional performance data, avoiding situations where test scenarios are singular and data is incomplete. The data frame format and signal strength are fitted to determine the corresponding transmission success rate, and a transmission mapping relationship is established between the satellite number, antenna angle, transmission success rate, data frame format, and signal strength of the passing satellite. This digitizes the communication environment and performance relationship, improving the efficiency and effectiveness of performance evaluation. Based on the data to be transmitted and its corresponding transmission optimization target, the target transmission satellite is determined according to the transmission mapping relationship, and the data to be transmitted is transmitted through the target transmission satellite, improving the transmission success rate of the data to be transmitted, thereby improving the reliability and efficiency of LEO satellite IoT communication. Attached Figure Description

[0012] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments of this application will be briefly introduced below. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0013] Figure 1 This is a flowchart illustrating a low-Earth orbit satellite communication method provided in an embodiment of this application; Figure 2 This is a schematic diagram of a low-Earth orbit satellite communication system provided in an embodiment of this application; Figure 3 This is a schematic diagram of a low-orbit satellite communication module real-network communication test system provided in an embodiment of this application; Figure 4 This is a flowchart illustrating another low-Earth orbit satellite communication method provided in an embodiment of this application; Figure 5 This is a schematic diagram of a device structure provided in an embodiment of this application; Figure 6 This is a schematic diagram of the structure of a terminal device provided in an embodiment of this application. Detailed Implementation

[0014] The features and exemplary embodiments of various aspects of this application will be described in detail below. To make the objectives, technical solutions, and advantages of this application clearer, the application will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only intended to explain this application and not to limit it. For those skilled in the art, this application can be implemented without some of these specific details. The following description of the embodiments is merely to provide a better understanding of this application by illustrating examples.

[0015] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of additional identical elements in the process, method, article, or apparatus that includes said element.

[0016] On the satellite IoT end side, low-orbit satellites have become the preferred terminal devices for satellite IoT due to their flexible data transmission methods, large access capacity, and low power consumption.

[0017] In existing technologies, the evaluation of the real-world network communication performance of low-Earth orbit satellite modules mainly relies on manual operation. However, manual evaluation has the following drawbacks: Because the transit time of low-Earth orbit (LEO) satellite constellations at ground test points is discontinuous, the efficiency of actual network performance testing of LEO satellite communication modules is low and the time required is long during the research and development or customer promotion process, making manual testing very inconvenient.

[0018] Because the elevation angle relative to the ground test point varies each time a low-orbit satellite passes overhead, the angle of the ground antenna affects the test results of satellite communication. When the ground antenna angle remains unchanged, the data transmission success rate is low when most satellites pass overhead.

[0019] Currently, there is no evaluation method that can cover satellite transmission results with various antenna angles and different data frame packets, which limits the test range. Alternatively, although it can measure the performance of single-hop paths and continuous paths of arbitrary length, it cannot adaptively adjust the antenna angle of the ground test equipment to adapt to satellites passing over at different elevation angles, thus limiting its application in the testing of low-Earth orbit satellite modules. Its test results are affected by the angle of the ground antenna.

[0020] In view of this, this application provides a low-Earth orbit (LEO) satellite communication method that adaptively determines the angle of the target antenna for communication based on the acquired constellation calendar (i.e., the transit time window sequence in this application) and allocates test data to achieve full-scale data communication testing of the LEO satellite module in a real network. This can improve the efficiency and effectiveness of real network performance evaluation. At the same time, when implemented in a real environment, it can quickly evaluate the most suitable antenna angle and communication data frame format for the terminal in the deployment environment, which is convenient for the practical application of the LEO satellite communication module and for users to import data and determine the target antenna and target transmission satellite based on the user-imported data.

[0021] To address the problems of the prior art, embodiments of this application provide a low-orbit satellite communication method, system, apparatus, and readable storage medium.

[0022] The low-orbit satellite communication method provided in the embodiments of this application will be introduced first below.

[0023] Figure 1 A flowchart illustrating a low-Earth orbit satellite communication method according to an embodiment of this application is shown. Figure 1 As shown, the method may include the following steps: S101: Transmits data packets to be tested to passing satellites under various antenna angle conditions via a low-orbit satellite communication module, and receives the test results of the data packets to be tested.

[0024] The data packets to be tested include data frames in different data frame formats.

[0025] Specifically, under various antenna angle conditions, a test data packet is sent to an overpassing satellite via a low-orbit satellite communication module, and the test results of the test data packet are received. The antenna angle is a fixed angle formed by the physical axis of the antenna on the ground test device and the reference plane. Various antenna angles can be achieved by switching the target antenna in the antenna array. The test results can be received through the low-orbit satellite communication module or by sending a request directly to the satellite communication platform.

[0026] The data packet under test includes data frames with different data frame formats. Different data frame formats can have different data frame lengths and different byte lengths. The data frame length refers to the total number of bytes included in a data frame. Different data frame formats can define the volume and structure of data transmission, thereby directly affecting the transmission time, channel occupancy rate and bit error probability.

[0027] The data frames in the data packet under test can be generated according to a preset test case format, or they can be received from data frames sent by a terminal device according to a preset test case format. In one preset test case format, the data frame format can include the data frame length and the byte length. This preset test case format can use X to represent the data frame length and Y to represent the byte length. Table 1 is a preset test case format table: Table 1. A Preset Test Case Format

[0028] As shown in Table 1, the maximum data frame length can be set to A, and the maximum byte length can be set to B. Different data structures correspond to different data frame formats, and the data frame format can include the data frame length and the maximum byte length.

[0029] This application embodiment actively traverses the combination of antenna angle and data structure to perform multiple controlled experiments during each satellite transit, thereby separating and correlating factors that affect low-Earth orbit satellite communication, such as channel time-varying, terminal configuration, and data structure. This allows the testing process to comprehensively test the data transmission results under different conditions, improving the comprehensiveness of the testing process and results.

[0030] S102: Based on the test results, determine the signal strength of different data frames under different antenna angles.

[0031] Specifically, based on the test results, the signal strength under each test data is determined, and it is correlated with the data frame and antenna angle of that test data to determine the signal strength of different data frames under different antenna angles.

[0032] The antenna array includes antennas with different antenna angles. The antenna angle refers to the angle between the angle in which the antenna is facing and the reference plane. The satellite elevation angle refers to the angle between the passing satellite and the reference plane during the passing process.

[0033] For example, based on multiple experiments, it was found that when the difference between the antenna angle and the satellite elevation angle is within 15°, the signal between the satellite and the antenna during transmission is relatively good. The antenna can be configured for testing based on the angle difference and the transit information of the transiting satellite to test the signal strength of the data packet to be tested transmitted from the antenna with different antenna angles to the transiting satellite. Table 2 is a test relationship table of angle difference and signal strength.

[0034] Table 2. A test relationship between included angle difference and signal strength.

[0035] As shown in Table 2, the horizontal row represents the signal strength, which is good, medium, and poor, respectively, and the vertical row represents the number of antennas, which can be denoted as n. n=3 indicates that there are three antennas. This represents the angle difference. The larger n is, the more antennas are configured, and the wider the range of angle differences that can be evaluated.

[0036] This application embodiment configures multiple antennas, allowing different passing satellites to select suitable antennas for testing at different satellite elevation angles. This maintains high signal quality under various conditions, optimizes test results, and thus improves data transmission success rate.

[0037] S103: Fit the data frame format and signal strength to determine the corresponding transmission success rate, and establish the transmission mapping relationship between the satellite number, antenna angle, transmission success rate, data frame format and signal strength of the passing satellite.

[0038] Specifically, fitting the data frame format and signal strength to determine the corresponding transmission success rate can be done through data processing algorithms. That is, by inputting the data frame format and signal strength, the corresponding transmission success rate can be obtained through fitting.

[0039] Fitting refers to determining the relationship between variables from discrete data points using methods such as linear regression and neural networks.

[0040] In addition, a transmission mapping relationship is established for the satellite number, antenna angle, transmission success rate, data frame format, and signal strength of the transiting satellites. The essence of the transmission mapping relationship is a multi-dimensional performance lookup table or a structured knowledge base, which is used to guide the optimization of data transmission.

[0041] This application embodiment determines the stable relationship between the communication environment and performance by testing the data packet and structures the stable relationship. Thus, in the application stage, the transmission method can be determined directly based on the currently known transmission data and transmission optimization goals, according to the transmission mapping relationship, which improves the transmission success rate and increases the selection space of transmission paths.

[0042] S104: Based on the data to be transmitted and the corresponding transmission optimization target, determine the target transmission satellite based on the transmission mapping relationship, and transmit the data to be transmitted through the target transmission satellite.

[0043] Specifically, after receiving the test results of all data frames in the data packet to be tested and updating the transmission mapping relationship based on the test results, the transmission mapping relationship can be matched with the data to be transmitted and the corresponding transmission optimization target to determine the target transmission satellite that matches it from the currently visible overpassing satellites, and the data to be transmitted can be transmitted through the target transmission satellite.

[0044] The embodiments of this application can determine the corresponding target transmission satellite in the transmission mapping relationship based on the data to be transmitted and the transmission optimization target, so that the transmission process and transmission results are more in line with the transmission optimization target, thereby improving the transmission success rate and reducing the risk of transmission failure.

[0045] This application embodiment, through the configuration of multi-angle antennas and comprehensive data frame testing, can comprehensively evaluate the performance of low-Earth orbit satellite communication modules under various conditions. At the same time, by using data fitting and establishing transmission mapping relationships, it provides a more reliable basis for determining the target transmission satellite, avoiding problems such as communication performance uncertainty caused by incomplete testing, and improving the communication reliability and efficiency of low-Earth orbit satellite networking.

[0046] In some embodiments, transmitting data packets to be tested to an overpassing satellite via a low-Earth orbit satellite communication module under various antenna angle conditions includes: Based on the transit information of transiting satellites, determine the transit time window; Within the transit time window, based on the transit elevation angle of the transiting satellite, the antenna in the antenna array with the smallest angle difference from the transit elevation angle is determined as the target antenna, and the data packet to be tested is sent to the transiting satellite based on the target antenna.

[0047] Specifically, the transit information of the transiting satellite is obtained. The transit information is a set of data describing the visualized trajectory of the transiting satellite relative to a specific location, including but not limited to the transit start time, transit end time, maximum elevation angle time, and corresponding elevation angle sequence.

[0048] By parsing and extracting the transit information, an effective time range that can be used for communication testing can be obtained, namely the transit time window. This can avoid the waste of energy and time caused by making invalid communication attempts when the transiting satellite is not visible or the signal is weak. The transit time window refers to the time interval from when the satellite elevation angle of the transiting satellite is higher than the communication threshold to when the satellite elevation angle is lower than the communication threshold.

[0049] In addition, within the transit time window, based on the current transit elevation angle of the transit satellite, the angle difference between the included angle of each antenna in the antenna array and the transit elevation angle is compared, and the antenna with the smallest included angle difference is determined as the target antenna. The data packet to be tested is then sent to the transit satellite through the target antenna.

[0050] Furthermore, each antenna in the antenna array can be used in turn as the target antenna to send the data packet to be tested to the passing satellite in order to determine the test results of the data packet under various angle differences.

[0051] The data packet to be tested includes multiple data frames, which can be sent sequentially to ensure that the data tested on the same target antenna is not repeated, thereby improving testing efficiency.

[0052] This application embodiment optimizes energy consumption and schedules tasks through the transit time window, improving the efficiency of real-network testing and the accuracy of performance testing of low-orbit satellite communication modules. By switching the target antenna and sending the data packets to be tested to the transiting satellite through the target antenna, the flexibility and adaptability of the test are enhanced.

[0053] In some embodiments, the transmission optimization objective includes at least one of the following: maximizing the data transmission success rate and minimizing the data transmission latency.

[0054] Specifically, in the actual application scenarios of low-Earth orbit satellite communication, the communication strategy may change and needs to be adjusted according to the attributes of the data to be transmitted and the priority of the business logic.

[0055] The transmission optimization objectives include at least one of maximizing the data transmission success rate and minimizing the data transmission latency. Maximizing the data transmission success rate means prioritizing the satellite number corresponding to the highest transmission success rate among the available transmission links for the data to be transmitted. Minimizing the data transmission latency means selecting the satellite link with the shortest time from data transmission to confirmation of reception among the available transmission links for the data to be transmitted.

[0056] Furthermore, if there are at least two transmission links that maximize the data transmission success rate, and the difference in the data transmission success rate does not exceed the preset success rate difference, satellite links can be further selected based on transmission delay, transmission load, and other factors to determine the target transmission satellite.

[0057] This application embodiment enhances adaptability to complex environments by transmitting optimized target dynamic switching decision logic, thereby ensuring high efficiency and reliability of data transmission, reducing complexity, and improving usability.

[0058] In some embodiments, based on the data to be transmitted and the corresponding transmission optimization target, a target transmission satellite is determined according to a transmission mapping relationship, and the data to be transmitted is transmitted through the target transmission satellite, including: Traverse the transmission mapping relationship to determine the transmission success rate and signal strength that match the format of the data frame to be transmitted. With the goal of maximizing data transmission success rate, the satellite with the satellite number corresponding to the maximum transmission success rate is identified as the target satellite, and the antenna with the included angle is identified as the target antenna. Data to be transmitted is sent to the target satellite based on the target antenna, so as to transmit the data based on the target satellite.

[0059] Specifically, based on the data structure of the data to be transmitted, that is, the data frame format of the data to be transmitted is used as the query condition, and the transmission mapping relationship is traversed and searched. In this way, test results with the same or similar data format as the data to be transmitted can be selected from the transmission mapping relationship. Then, based on the test results, the transmission success rate and signal strength that match the data to be transmitted are determined.

[0060] In addition, when the goal of transmission optimization is to maximize the data transmission success rate, the overpassing satellite corresponding to the satellite number with the maximum transmission success rate is identified as the target satellite. At the same time, the target antenna is identified based on the antenna angle recorded in the test records. Thus, the target satellite and target antenna that maximize the transmission success rate of the data to be transmitted can be matched according to the transmission mapping relationship.

[0061] In addition, the target antenna sends the data to be transmitted to the target satellite, thereby enabling the target satellite to transmit the data.

[0062] This application embodiment, through transmission optimization target and transmission mapping relationship, can determine the target antenna and target satellite for transmitting the data to be transmitted according to the data frame format of the data to be transmitted, so as to ensure the maximum data transmission success rate, improve the reliability of data transmission, and avoid blindness and uncertainty when determining the corresponding transmission mode of the data to be transmitted, thereby improving the service capabilities of low-orbit satellite communication.

[0063] In some embodiments, transmitting data packets to be tested to an overpassing satellite via a low-Earth orbit satellite communication module under various antenna angle conditions includes: Obtain the transit time window sequence of multiple transiting satellites; Based on the transit time window sequence and the data packets to be tested, the transiting satellites are dynamically allocated to perform each test task in the data packets to be tested until all test results of the data packets to be tested are received.

[0064] Specifically, the transit time window sequence of multiple transiting satellites is obtained. The transit time window sequence includes a set of start times, end times, and satellite identifiers of multiple transiting satellites organized in chronological order. This allows for the reasonable scheduling of test tasks based on the transit time window sequence, ensuring the efficiency and orderliness of the test process.

[0065] In addition, the multiple data frames included in the data packet to be tested and the test tasks corresponding to each data frame are dynamically assigned to each passing satellite so that each passing satellite can perform the test tasks until all test results of the data packet to be tested are received.

[0066] Dynamic allocation can be performed through schedulers, preset allocation algorithms, etc. There may be multiple test tasks, and the transit time of a single transiting satellite may not be sufficient to complete all test tasks. In addition, low-Earth orbit satellites are generally presented in the form of constellations, that is, multiple low-Earth orbit satellites are jointly responsible for transmission tasks. Therefore, test tasks can be assigned to different satellites to determine the actual network performance of each satellite during the current transit time, thereby ensuring the comprehensiveness and richness of the test results.

[0067] The dynamic allocation method of this application embodiment can flexibly select a suitable transit satellite to complete the test task based on the transit time of the transit satellite and the data structure of the data packet to be tested. This improves the flexibility and efficiency of the test process, while avoiding the problems of low test efficiency and long cycle caused by resource dispersion in the low-orbit satellite test environment. This improves the reliability, comprehensiveness and flexibility of the test.

[0068] In some embodiments, fitting the data frame format and signal strength to determine the corresponding transmission success rate includes: By using a preset linear fitting method, the data frame format and signal strength are fitted to determine the corresponding transmission success rate.

[0069] Specifically, by using a preset linear fitting method, the data frame format of the current test task and the signal strength in the corresponding test results are fitted to obtain the transmission success rate of the current test task. The preset linear fitting method can be expressed as: S = a*X + b*Y + c*P + d; Where S represents the transmission success rate, X represents the data frame length, Y represents the byte length, P represents the signal strength, and a, b, and c represent the corresponding transmission parameters. The transmission parameters are coefficients determined by fitting and can characterize the influence weights of data frame format and signal strength on the transmission success rate.

[0070] This application embodiment uses a preset linear fitting method to convert data frame format and signal strength into a calculable and interpretable preset linear fitting method. The preset linear fitting method captures the dominant influence of data load characteristics and channel conditions on the test results. The transmission success rate obtained based on the preset linear fitting method improves communication efficiency and reliability.

[0071] The low-orbit satellite communication device provided in the embodiments of this application is described below.

[0072] Figure 2 A schematic diagram of a low-Earth orbit satellite communication system structure according to an embodiment of this application is shown. Figure 2 As shown, a low-Earth orbit satellite communication system includes: The power supply circuit 201 includes a first sub-power supply circuit 2011, a second sub-power supply circuit 2012 and a third sub-power supply circuit 2013, and is used to power on the low-Earth orbit satellite communication system. The main control circuit 202 is connected to the first sub-power supply circuit 2011; The communication interface circuit 203 is connected in parallel with the main control circuit to the first sub-power supply circuit 2011 and is used to communicate with external devices. The low-orbit satellite communication module 204, connected to the second sub-power circuit 2012, is used to send data packets to be tested to the passing satellite under various antenna angle conditions, wherein the data packets to be tested include data frames of different data frame formats. Antenna array 205 includes multiple antennas set at different preset angles; RF switch 206, connected to third sub-power circuit 2013, is used to control each antenna in antenna array; The main control circuit 202 is configured to: receive the test results of the data packet to be tested, determine the signal strength of different data frames under different antenna angles based on the test results, fit the data frame format and signal strength, determine the corresponding transmission success rate, and establish the transmission mapping relationship between the satellite number, antenna angle, transmission success rate, data frame format and signal strength of the passing satellite. Based on the data to be transmitted received by the communication interface circuit and the corresponding transmission optimization target, the target transmission satellite is determined based on the transmission mapping relationship, and the data to be transmitted is transmitted through the target transmission satellite.

[0073] Specifically, the power supply circuit 201 serves as the energy supply center for the low-Earth orbit satellite communication system, providing electrical energy input to various functional units within the system and ensuring its continuous operation.

[0074] The power supply circuit 201 includes a power input interface 2010, a first sub-power supply circuit 2011, a second sub-power supply circuit 2012, and a third sub-power supply circuit 2013. The first sub-power supply circuit 2011 is used to supply power to the main control circuit 202 and the communication interface circuit 203, the second power supply circuit 2012 is used to supply power to the low-orbit satellite communication module 204, and the third sub-power supply circuit 2013 is used to supply power to the radio frequency switch 206.

[0075] The main control circuit 202 can receive the test results of the data packet under test, determine the signal strength of different data frames under different antenna angles based on the test results, fit the data frame format and signal strength, determine the corresponding transmission success rate, and establish the transmission mapping relationship between the satellite number of the overpassing satellite, antenna angle, transmission success rate, data frame format and signal strength. Based on the data to be transmitted received by the communication interface circuit and the corresponding transmission optimization target, the target transmission satellite is determined based on the transmission mapping relationship, and the data to be transmitted is transmitted through the target transmission satellite.

[0076] The main control circuit 202 and the communication interface circuit 203 can be connected via a Universal Asynchronous Receiver / Transmitter (UART) or a communication interface to receive control commands and related data sent by the host computer (i.e., external devices). The main control circuit 202 and the second sub-power supply circuit 2012 are connected via General-purpose input / output (GPIO) to control the power supply of the low-Earth orbit satellite module 204. The main control circuit 202 and the low-Earth orbit satellite communication module 204 are connected via UART to control the low-Earth orbit satellite communication module 204 to transmit data packets under test. The main control circuit 202 and the RF switch 206 are connected via GPIO to control the RF switch 206 to switch the path of the corresponding antenna.

[0077] Antenna array 205 includes multiple antennas set at different preset angles, named ANT1 to ANTn, where n≥3. The antennas are arranged in an arithmetic sequence. For example, when n=3, the antenna angles with the reference plane are 15°, 45°, and 75°. When n=5, the antenna angles with the reference plane are 10°, 30°, 50°, 70°, and 90°. This ensures that the angle difference between the overpassing satellite and the target antenna can be controlled within 15°, facilitating the testing of the data packet under test in an environment with good signal strength.

[0078] Taking n=3 as an example, if the elevation angle of the passing satellite is between 0° and 30°, and a target antenna with an antenna angle of 15° to the reference plane is used, then the difference between the elevation angle of the passing satellite and the antenna angle of the target antenna is within 15°; if the elevation angle of the passing satellite is between 30° and 60°, and a target antenna with an antenna angle of 45° to the reference plane is used, then the difference between the elevation angle of the passing satellite and the antenna angle of the target antenna is within 15°; if the elevation angle of the passing satellite is between 60° and 90°, and a target antenna with an antenna angle of 75° to the reference plane is used, then the difference between the elevation angle of the passing satellite and the antenna angle of the target antenna is within 15°.

[0079] Figure 3 This is a schematic diagram of a low-orbit satellite communication module real-network communication test system provided in an embodiment of this application, as shown below. Figure 3 As shown, it includes a low-orbit satellite communication system 301, a test host computer 302, and a satellite data platform 303.

[0080] The host computer 302 is used to receive the input of the data packet to be tested, control the low-orbit satellite communication system 301 to execute the data packet to be tested, receive the constellation calendar of the satellite data platform 303, and view the communication data of the satellite data platform 303.

[0081] Figure 4 This is a flowchart illustrating another low-Earth orbit (LEO) satellite communication method provided in this application embodiment, applied to a real-world network communication test system for LEO satellite communication modules, such as... Figure 4 As shown, it includes: S401: Place the low-Earth orbit satellite communication system 301 flat in the field environment and load the low-Earth orbit satellite module in the system's SOCKET fixture; S402: Select the data packet to be tested or receive the input of the data packet to be tested in the test host computer 302. The data packet to be tested includes the control of the low-orbit satellite communication system 301 to test the satellite data transmission under various antenna angles and satellite elevation angles.

[0082] S403: The test host computer 302 obtains the transit calendar of the constellation under test from the satellite data platform 303 according to the test location. The transit calendar includes information such as transit time interval and transit satellite elevation angle. S404: The host computer 302 sends the test data cases, transit satellite time and elevation angle to the low-Earth orbit satellite communication system 301 via USB; S405: Before an overpassing satellite passes over, the main control microcontroller unit (MCU) of the low-Earth orbit satellite communication system 301 turns on the power supply of the low-Earth orbit satellite module through GPIO and sends the frame packets of the data to be tested through UART; S406: The main control MCU controls the RF switch to switch the target antenna for testing based on the elevation angle of the passing satellite and the antenna configuration; S407: After the satellite passes over the orbit, the main control MCU disconnects the power supply to the low-Earth orbit satellite module via GPIO control; S408: Determine whether the test case has been completed. If the test case has not been completed, the low-Earth orbit satellite communication system 301 repeats the above process until the test of the data packet to be tested is completed. S409: If the test cases have been completed, the low-Earth orbit satellite communication system 301 notifies the test host computer 302. S410: Test the host computer 302 to retrieve data from the satellite data platform 303; S411: Output the data transmission results of the LEO satellite module under various test conditions based on the test results, so as to determine the actual network performance of the LEO satellite module; S412: Users can use the actual network communication performance evaluation results to determine the antenna angle and communication data frame format of the terminal satellite, and perform data transmission performance formula fitting for the low-orbit satellite module. After configuring the angle between the antenna and the passing satellite, the data frame length X and byte length Y that meet the requirements of the low-orbit satellite module are traversed, and the actual signal strength P and data transmission success rate S are measured. Based on the measured data, the following formula is used for fitting: S=a*X+b*Y+c*P+d, and the parameters a, b, c, and d are determined. S413: When low-Earth orbit satellite modules are used in real networks, appropriate transmission satellites and data frame structures should be selected for data transmission to ensure a high data transmission success rate.

[0083] For example, the low-orbit satellite communication system 301 is placed flat in an outdoor environment, and the low-orbit satellite module is loaded in the SOCKET fixture. It is configured with three antennas, and the antenna angles between the three antennas and the reference plane are 15°, 45° and 75°.

[0084] On the host computer 302, select the standard test case (i.e., the test data package), which means: configure the angle difference between all overpassing satellites and the antenna. ≤15°, iterate through and test 9 data formats (e.g., short frame short byte, short frame medium byte, short frame long byte, medium frame short byte, medium frame medium byte, medium frame long byte, long frame short byte, long frame medium byte, long frame long byte); configure the angle difference between all overpassing satellites and the antenna to be less than 15°. ≤45°, traversing and testing 9 data formats; configuring the angle difference between the antenna and the antenna of all overpassing satellites to be less than 45°. ≤75°, iterate through and test 9 data formats.

[0085] The host computer 302 retrieves the transit calendar of the constellation under test from the satellite data platform 303 based on the test location. The transit calendar includes information such as the transit time interval and the elevation angle of the transiting satellites. For example, Table 3 shows a schematic diagram of the transit calendar. Table 3. Transit Calendar Diagram

[0086] The host computer 302 sends the above test data test cases, transit satellite time and satellite elevation angle to the low-Earth orbit satellite communication system 301 via USB.

[0087] Before satellite number 1 passes overhead, the main control MCU of the low-Earth orbit satellite communication system 301 turns on the power supply of the low-Earth orbit satellite module through GPIO control and sends short frame short byte data packets through UART.

[0088] Based on the elevation angle of satellite number 1 (24.2°), the main control MCU controls the RF switch to switch the target antenna with an antenna angle of 15°, which is a good point for short frame and short byte data communication test.

[0089] After satellite number 1 passes over the Earth, the main control MCU disconnects the power supply to the low-Earth orbit satellite module via GPIO control.

[0090] Before satellite number 2 passes overhead, repeat the above process until all standard test cases are completed.

[0091] After completing all standard test cases, the host computer 302 retrieves the data transmission data from the satellite data platform 303 and outputs the data transmission results of the LEO satellite module under test under various test conditions based on the test results, in order to evaluate the actual network performance of the LEO satellite module. Table 4 is a schematic table of the data transmission results: Table 4. Schematic diagram of data transmission results

[0092] This ensures that after the low-orbit satellite communication module is deployed in a specific environment, the antenna angle and data frame format can be specifically set according to the actual network performance test results, so as to ensure a high success rate of satellite communication data transmission and meet the user's transmission needs.

[0093] For example, the low-Earth orbit satellite communication system 301 is placed flat in an outdoor environment, with the low-Earth orbit satellite module loaded in the SOCKET fixture and configured with five antennas. The antenna angles between the five antennas and the reference plane are 10°, 30°, 50°, 70°, and 90°.

[0094] On the test host computer 302, a custom data frame format for the data packet under test is defined. X represents the data frame length in the data packet under test, and Y represents the byte length of the data frame in the data packet under test. This is done when X ≤ 400 and Y ≤ 120, i.e., configuring the angle difference between the overpassing satellite and the antenna. ≤10°, iterate through all combinations of X and Y with a gradient of 10; configure the angle difference between the overpassing satellite and the antenna to be less than 10°. ≤50°, iterate through all combinations of X and Y with a gradient of 10; configure the angle difference between the overpassing satellite and the antenna to be less than 50°. ≤90°, iterate through all combinations of X and Y with a gradient of 10.

[0095] The host computer 302 retrieves the transit calendar of the constellation under test from the satellite data platform 303 based on the test location. The transit calendar includes information such as the transit time interval and the elevation angle of the transiting satellites. For example, Table 5 shows a schematic diagram of the transit calendar. Table 5. Transit Calendar Diagram

[0096] The host computer 302 sends the above test data test cases, transit satellite time and satellite elevation angle to the low-Earth orbit satellite communication system 301 via USB.

[0097] Before satellite number 1 passes overhead, the main control MCU of the low-Earth orbit satellite communication system 301 turns on the power supply of the low-Earth orbit satellite module through GPIO control and sends data X=10, Y=10 through UART.

[0098] Based on the satellite elevation angle of satellite number 1 (24.2°), the main control MCU controls the radio frequency switch to switch the target antenna with an antenna angle of 10° and records the signal strength P1.

[0099] After satellite number 1 passes over the Earth, the main control MCU disconnects the power supply to the low-Earth orbit satellite module via GPIO control.

[0100] Before satellite number 2 passes overhead, the main control MCU of the low-Earth orbit satellite communication system 301 turns on the power supply of the low-Earth orbit satellite module through GPIO control and sends data X=10, Y=20 through UART.

[0101] Based on the satellite elevation angle of satellite number 2 (21.8°), the main control MCU controls the radio frequency switch to switch the target antenna with an antenna angle of 10° and records the signal strength P2.

[0102] This process is repeated automatically to complete all test items.

[0103] After completing all the data packets to be tested, the host computer 302 retrieves the data transmission data from the satellite data platform 303 and outputs the data transmission results of the low-Earth orbit satellite module under various test conditions based on the test results, in order to evaluate the actual network performance of the low-Earth orbit satellite module. Table 6 is a schematic table of data transmission results: Table 6. Data Transmission Results Diagram

[0104] Based on the test results, a formula was fitted to the data transmission performance of the low-orbit satellite module: data frame length X and byte length Y, measured signal strength P and data transmission success rate S.

[0105] Based on the measured data, a formula was fitted: S=a*X+b*Y+c*P+d, to determine the parameters a, b, c, and d. This allows the low-orbit satellite module to select the appropriate target transmission satellite and data frame structure for data transmission when applied in a real network, ensuring a high transmission success rate.

[0106] The low-Earth orbit satellite communication system provided in this application embodiment can transform the testing method into a physical implementation, realizing the automation of the transmission process, high reliability of execution, and adaptability to the dynamic space environment.

[0107] In some embodiments, the main control circuit is configured as follows: In response to control commands including the transit time window and the target antenna, the second sub-power circuit is controlled to power on the low-Earth orbit satellite communication module and the third sub-power circuit is controlled to power on the radio frequency switch within the transit time window. The radio frequency switch is controlled to switch to the target antenna and the low-Earth orbit satellite communication module is controlled to send the data packet to be tested or the data to be transmitted. After the transit window ends, the control power circuit de-energizes the low-Earth orbit satellite communication module.

[0108] Figure 5 This is a schematic diagram of a device structure provided in an embodiment of this application. Figure 5 As shown, the device may include a communication module 510, a testing module 520, a fitting module 530, and a transmission module 540.

[0109] The communication module 510 is used to send data packets to be tested to the passing satellite under various antenna angle conditions through the low-orbit satellite communication module, and to receive the test results of the data packets to be tested, wherein the data packets to be tested include data frames of different data frame formats. Test module 520 is used to determine the signal strength of different data frames under different antenna angles based on the test results; The fitting module 530 is used to fit the data frame format and signal strength, determine the corresponding transmission success rate, and establish the transmission mapping relationship between the satellite number, antenna angle, transmission success rate, data frame format and signal strength of the passing satellite. The transmission module 540 is used to determine the target transmission satellite based on the transmission mapping relationship according to the data to be transmitted and the corresponding transmission optimization target, and to transmit the data to be transmitted through the target transmission satellite.

[0110] In some embodiments, the communication module 510 transmits data packets to be tested to the passing satellite via a low-Earth orbit satellite communication module under various antenna angle conditions, for the purpose of: Based on the transit information of transiting satellites, determine the transit time window; Within the transit time window, based on the transit elevation angle of the transiting satellite, the antenna in the antenna array with the smallest angle difference from the transit elevation angle is determined as the target antenna, and the data packet to be tested is sent to the transiting satellite based on the target antenna.

[0111] In some embodiments, the transmission optimization objective includes at least one of the following: maximizing data transmission success rate and minimizing data transmission latency.

[0112] In some embodiments, the transmission module 540 determines the target transmission satellite based on a transmission mapping relationship according to the data to be transmitted and the corresponding transmission optimization target, and transmits the data to be transmitted through the target transmission satellite, for the purpose of: Traverse the transmission mapping relationship to determine the transmission success rate and signal strength that match the format of the data frame to be transmitted. With the goal of maximizing data transmission success rate, the satellite with the satellite number corresponding to the maximum transmission success rate is identified as the target satellite, and the antenna with the included angle is identified as the target antenna. Data to be transmitted is sent to the target satellite based on the target antenna, so as to transmit the data based on the target satellite.

[0113] In some embodiments, the communication module 510 transmits data packets to be tested to the passing satellite via a low-Earth orbit satellite communication module under various antenna angle conditions, for the purpose of: Obtain the transit time window sequence of multiple transiting satellites; Based on the transit time window sequence and the data packets to be tested, the transiting satellites are dynamically allocated to perform each test task in the data packets to be tested until all test results of the data packets to be tested are received.

[0114] In some embodiments, the fitting module 530 fits the data frame format and signal strength to determine the corresponding transmission success rate, for the purpose of: By using a preset linear fitting method, the data frame format and signal strength are fitted to determine the corresponding transmission success rate.

[0115] Figure 6 A schematic diagram of the hardware structure of the terminal device provided in an embodiment of this application is shown.

[0116] The terminal device may include a processor 601 and a memory 602 storing computer program instructions.

[0117] Specifically, the processor 601 may include a central processing unit (CPU), an application specific integrated circuit (ASIC), or one or more integrated circuits that can be configured to implement the embodiments of this application.

[0118] Memory 602 may include mass storage for data or instructions. For example, and not limitingly, memory 602 may include a hard disk drive (HDD), floppy disk drive, flash memory, optical disk, magneto-optical disk, magnetic tape, or Universal Serial Bus (USB) drive, or a combination of two or more of these. In one instance, memory 602 may include removable or non-removable (or fixed) media, or memory 602 may be non-volatile solid-state memory. Memory 602 may be internal or external to the integrated gateway disaster recovery device.

[0119] In one instance, memory 602 may be read-only memory (ROM). In one instance, the ROM may be a mask-programmed ROM, a programmable ROM (PROM), an erasable PROM (EPROM), an electrically erasable PROM (EEPROM), an electrically rewritable ROM (EAROM), or flash memory, or a combination of two or more of these.

[0120] Memory 602 may include read-only memory (ROM), random access memory (RAM), disk storage media device, optical storage media device, flash memory device, electrical, optical, or other physical / tangible memory storage device. Therefore, generally, memory includes one or more tangible (non-transitory) computer-readable storage media (e.g., memory devices) encoded with software including computer-executable instructions, and when the software is executed (e.g., by one or more processors), it is operable to perform the operations described with reference to the method according to the first aspect of this disclosure.

[0121] The processor 601 reads and executes computer program instructions stored in the memory 602 to achieve... Figure 6 The low-Earth orbit satellite communication method shown in the embodiment.

[0122] In one example, the terminal device may further include a communication interface 603 and a bus 604. Wherein, for example... Figure 6 As shown, the processor 601, memory 602, and communication interface 603 are connected through bus 604 and complete communication with each other.

[0123] The communication interface 603 is mainly used to realize communication between various modules, devices, units and / or equipment in the embodiments of this application.

[0124] Bus 604 includes hardware, software, or both, that couples components of an online data traffic metering device together. For example, and not limitingly, the bus may include an Accelerated Graphics Port (AGP) or other graphics bus, an Extended Industry Standard Architecture (EISA) bus, a Front Side Bus (FSB), a Hyper Transport (HT) interconnect, an Industry Standard Architecture (ISA) bus, an Infinite Bandwidth Interconnect, a Low Pin Count (LPC) bus, a memory bus, a Microchannel Architecture (MCA) bus, a Peripheral Component Interconnect (PCI) bus, a PCI-Express (PCI-X) bus, a Serial Advanced Technology Attachment (SATA) bus, a Video Electronics Standards Association Local (VLB) bus, or other suitable buses, or combinations of two or more of these. Where appropriate, bus 604 may include one or more buses. Although specific buses are described and illustrated in embodiments of this application, this application contemplates any suitable bus or interconnect.

[0125] The terminal device can execute the online data traffic billing method in this application embodiment based on the currently blocked spam text messages and text messages reported by users, thereby realizing the low-orbit satellite communication method.

[0126] Furthermore, in conjunction with the low-Earth orbit satellite communication methods in the above embodiments, this application embodiment can provide a computer storage medium for implementation. This computer storage medium stores computer program instructions; when these computer program instructions are executed by a processor, they implement any of the low-Earth orbit satellite communication methods in the above embodiments.

[0127] This application also provides a computer program product, including a computer program that, when executed by a processor, implements any of the low-Earth orbit satellite communication methods described above.

[0128] It should be clarified that this application is not limited to the specific configurations and processes described above and shown in the figures. For the sake of brevity, detailed descriptions of known methods are omitted here. In the above embodiments, several specific steps are described and shown as examples. However, the method process of this application is not limited to the specific steps described and shown. Those skilled in the art can make various changes, modifications, and additions, or change the order of steps, after understanding the spirit of this application.

[0129] The functional blocks shown in the above-described block diagram can be implemented as hardware, software, firmware, or a combination thereof. When implemented in hardware, they can be, for example, electronic circuits, application-specific integrated circuits (ASICs), appropriate firmware, plug-ins, function cards, etc. When implemented in software, the elements of this application are programs or code segments used to perform the required tasks. Programs or code segments can be stored on a machine-readable medium or transmitted over a transmission medium or communication link via data signals carried on a carrier wave. "Machine-readable medium" can include any medium capable of storing or transmitting information. Examples of machine-readable media include electronic circuits, semiconductor memory devices, read-only memory (ROM), flash memory, erasable read-only memory (EROM), floppy disks, compact disc read-only memory (CD-ROM), optical disks, hard disks, fiber optic media, radio frequency (RF) links, etc. Code segments can be downloaded via computer networks such as the Internet, intranets, etc.

[0130] It should also be noted that the exemplary embodiments mentioned in this application describe methods or systems based on a series of steps or apparatus. However, this application is not limited to the order of the above steps; that is, the steps can be performed in the order mentioned in the embodiments, or in a different order, or several steps can be performed simultaneously.

[0131] The aspects of this disclosure have been described above with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this disclosure. It should be understood that each block in the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, or other programmable data processing apparatus to produce a machine such that these instructions, executable via the processor of the computer or other programmable data processing apparatus, enable the implementation of the functions / actions specified in one or more blocks of the flowchart illustrations and / or block diagrams. Such a processor can be, but is not limited to, a general-purpose processor, a special-purpose processor, a special application processor, or a field-programmable logic circuit. It is also understood that each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, can also be implemented by special-purpose hardware performing the specified functions or actions, or can be implemented by a combination of special-purpose hardware and computer instructions.

[0132] The above description is merely a specific implementation of this application. Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working processes of the systems, modules, and units described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be repeated here. It should be understood that the protection scope of this application is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in this application, and these modifications or substitutions should all be covered within the protection scope of this application.

Claims

1. A low-Earth orbit satellite communication method, characterized in that, include: The low-Earth orbit satellite communication module transmits data packets to be tested to an overpassing satellite under various antenna angle conditions, and receives the test results of the data packets to be tested, wherein the data packets to be tested include data frames of different data frame formats. Based on the test results, the signal strength of different data frames under different antenna angles is determined; The data frame format and the signal strength are fitted to determine the corresponding transmission success rate, and a transmission mapping relationship is established between the satellite number of the passing satellite, the antenna angle, the transmission success rate, the data frame format, and the signal strength. Based on the data to be transmitted and the corresponding transmission optimization target, a target transmission satellite is determined according to the transmission mapping relationship, and the data to be transmitted is transmitted through the target transmission satellite.

2. The method according to claim 1, characterized in that, The transmission of data packets to be tested to an overpassing satellite via a low-Earth orbit satellite communication module under various antenna angle conditions includes: Based on the transit information of the transiting satellites, the transit time window is determined; Within the transit time window, based on the transit elevation angle of the transiting satellite, the antenna in the antenna array with the smallest angle difference from the transit elevation angle is determined as the target antenna, and the data packet to be tested is sent to the transiting satellite based on the target antenna.

3. The method according to claim 1, characterized in that, The transmission optimization objectives include at least one of the following: maximizing data transmission success rate and minimizing data transmission latency.

4. The method according to claim 1, characterized in that, The step of determining the target transmission satellite based on the transmission mapping relationship according to the data to be transmitted and the corresponding transmission optimization target, and transmitting the data to be transmitted through the target transmission satellite, includes: Traverse the transmission mapping relationship to determine the transmission success rate and signal strength that match the format of the data frame to be transmitted; When the transmission optimization objective is to maximize the data transmission success rate, the transit satellite corresponding to the satellite number corresponding to the maximum transmission success rate is determined as the target satellite, and the antenna corresponding to the antenna angle is determined as the target antenna. The data to be transmitted is sent to the target satellite based on the target antenna, so as to transmit the data to be transmitted based on the target satellite.

5. The method according to claim 1, characterized in that, The transmission of data packets to be tested to an overpassing satellite via a low-Earth orbit satellite communication module under various antenna angle conditions includes: Obtain the transit time window sequence of multiple transiting satellites; Based on the transit time window sequence and the data packet to be tested, transit satellites are dynamically allocated to execute each test task in the data packet to be tested until all test results of the data packet to be tested are received.

6. The method according to claim 1, characterized in that, The step of fitting the data frame format and the signal strength to determine the corresponding transmission success rate includes: By using a preset linear fitting method, the data frame format and the signal strength are fitted to determine the corresponding transmission success rate.

7. A low-Earth orbit satellite communication system, characterized in that, The system includes: The power supply circuit, including a first sub-power supply circuit, a second sub-power supply circuit and a third sub-power supply circuit, is used to power on the low-Earth orbit satellite communication system. The main control circuit is connected to the first sub-power supply circuit. A communication interface circuit, connected in parallel with the main control circuit to the first sub-power supply circuit, is used to communicate with external devices; A low-orbit satellite communication module, connected to the second sub-power circuit, is used to send data packets to be tested to an overpassing satellite under various antenna angle conditions, wherein the data packets to be tested include data frames of different data frame formats; Antenna array, comprising multiple antennas set at different preset angles; A radio frequency switch, connected to the third sub-power supply circuit, is used to control each of the antennas in the antenna array; The main control circuit is configured to: receive the test results of the data packet to be tested; determine the signal strength of different data frames under different antenna angles based on the test results; fit the data frame format and the signal strength to determine the corresponding transmission success rate; and establish a transmission mapping relationship between the satellite number of the overpassing satellite, the antenna angle, the transmission success rate, the data frame format, and the signal strength. Based on the data to be transmitted received by the communication interface circuit and the corresponding transmission optimization target, the target transmission satellite is determined based on the transmission mapping relationship, and the data to be transmitted is transmitted through the target transmission satellite.

8. The system according to claim 7, characterized in that, The main control circuit is configured as follows: In response to control commands including a transit time window and a target antenna, within the transit time window, the second sub-power circuit is controlled to power on the low-Earth orbit satellite communication module and the third sub-power circuit is controlled to power on the radio frequency switch, the radio frequency switch is controlled to switch to the target antenna, and the low-Earth orbit satellite communication module is controlled to send the data packet to be tested or the data to be transmitted. After the transit time window ends, the power supply circuit is controlled to power off the low-orbit satellite communication module.

9. A low-orbit satellite communication device, characterized in that, include: The communication module is used to send data packets to be tested to an overpassing satellite under various antenna angle conditions through a low-orbit satellite communication module, and to receive the test results of the data packets to be tested, wherein the data packets to be tested include data frames of different data frame formats; The testing module is used to determine the signal strength of different data frames under different antenna angles based on the test results. The fitting module is used to fit the data frame format and the signal strength to determine the corresponding transmission success rate, and to establish a transmission mapping relationship between the satellite number of the passing satellite, the antenna angle, the transmission success rate, the data frame format and the signal strength. The transmission module is used to determine the target transmission satellite based on the transmission mapping relationship according to the data to be transmitted and the corresponding transmission optimization target, and to transmit the data to be transmitted through the target transmission satellite.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer program instructions, which, when processed and executed, implement the low-Earth orbit satellite communication method as described in any one of claims 1 to 6.

Images