Performance testing methods, devices, equipment, and media for low-Earth orbit satellites

Abstract

This application proposes a performance testing method, apparatus, equipment, and medium for low-Earth orbit (LEO) satellites. The method includes acquiring a first test point and a first test time for the LEO satellite to be tested; acquiring a first grounding voltage level and a first signal beam direction of the LEO satellite during the first test time at the first test point; and performing an interference avoidance performance test on the LEO satellite based on the first grounding voltage level and the first signal beam direction to obtain a first target performance test result for the LEO satellite. This improves the accuracy and precision of LEO satellite interference avoidance performance testing, reduces the complexity of LEO satellite interference avoidance performance testing, improves the efficiency of handling anomalies in interference avoidance performance, and improves the stability of LEO satellite operational performance, thereby optimizing the communication stability and quality between high-Earth orbit (HEO) satellites and the Earth's surface.

Description

Technical Field

[0001] This application relates to the field of communication technology, and in particular to a method, apparatus, equipment and medium for testing the performance of low-orbit satellites. Background Technology

[0002] With the development of technology, the number of giant low-Earth orbit (LEO) satellite constellation systems is increasing. During the daily operation of LEO satellites, there is a possibility that they may affect the communication between high-Earth orbit (HEO) satellites and the Earth's surface to a certain extent. Among the relevant technologies, corresponding interference avoidance functions can be configured for LEO satellites to reduce the degree of impact of LEO satellites on the communication between HEO satellites and the Earth's surface.

[0003] Therefore, it is very important to test whether the interference avoidance function of low-orbit satellites is functioning properly. Summary of the Invention

[0004] The present application aims to solve one of the technical problems in the related art at least to a certain extent.

[0005] Therefore, the first objective of this application is to propose a performance testing method for low-Earth orbit satellites.

[0006] The second objective of this application is to provide a performance testing device for low-Earth orbit satellites.

[0007] The third objective of this application is to propose an electronic device.

[0008] The fourth objective of this application is to provide a computer-readable storage medium.

[0009] The fifth objective of this application is to provide a computer program product.

[0010] To achieve the above objectives, a first aspect of this application proposes a performance testing method for a low-Earth orbit (LEO) satellite, comprising: acquiring a first test point and a first test time for the LEO satellite to be tested; acquiring a first grounding level of the LEO satellite at the first test time through the first test point, and acquiring a first signal beam direction of the LEO satellite at the first test time; and performing an interference avoidance performance test on the LEO satellite based on the first grounding level and the first signal beam direction to obtain a first target performance test result for the LEO satellite.

[0011] To achieve the above objectives, a second aspect of this application provides a performance testing apparatus for a low-Earth orbit (LEO) satellite. The apparatus includes: an acquisition module for acquiring a first test point and a first test time of the LEO satellite to be tested; a data acquisition module for acquiring a first grounding voltage level of the LEO satellite at the first test time and a first signal beam direction of the LEO satellite at the first test time through the first test point; and a testing module for performing interference avoidance performance testing on the LEO satellite based on the first grounding voltage level and the first signal beam direction to obtain a first target performance test result of the LEO satellite.

[0012] To achieve the above objectives, a third aspect of this application provides an electronic device, including: a processor and a memory communicatively connected to the processor; the memory stores computer execution instructions; the processor executes the computer execution instructions stored in the memory to implement the low-Earth orbit satellite performance testing method proposed in the first aspect.

[0013] To achieve the above objectives, a fourth aspect of this application provides a computer-readable storage medium storing computer-executable instructions, which, when executed by a processor, are used to implement the performance testing method for low-Earth orbit satellites proposed in the first aspect.

[0014] To achieve the above objectives, a fifth aspect of this application provides a computer program product, including a computer program that, when executed by a processor, implements the performance testing method for low-Earth orbit satellites proposed in the first aspect.

[0015] The performance testing method and apparatus for low-Earth orbit (LEO) satellites provided in this application acquire a first test point and a first test time for the LEO satellite. Through the first test point, the first grounding voltage level and the first signal beam direction of the LEO satellite under the first test time are acquired. Based on the first grounding voltage level and the first signal beam direction, a first target performance test result for the interference avoidance performance of the LEO satellite is obtained. In this application, interference avoidance performance testing is performed using two dimensions: the first grounding voltage level and the first signal beam direction. This improves the accuracy and precision of LEO satellite interference avoidance performance testing. The use of a first test point set on the ground surface to perform the interference avoidance performance test reduces the complexity of the test, optimizes the testing method and effect, and improves the efficiency of identifying performance anomalies in scenarios where LEO satellite interference avoidance performance is abnormal. This, in turn, improves the efficiency of handling anomalies in interference avoidance performance, enhances the stability of LEO satellite operation performance, and ultimately optimizes the communication stability and quality between high-Earth orbit satellites and the ground surface.

[0016] Additional aspects and advantages of the present application will be given in part in the description below, and in part will become apparent from the description below, or will be learned through practice of the present application. Attached Figure Description

[0017] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0018] Figure 1 This is a flowchart illustrating a performance testing method for a low-Earth orbit satellite according to an embodiment of this application.

[0019] Figure 2 This is a flowchart illustrating a performance testing method for a low-Earth orbit satellite according to another embodiment of this application.

[0020] Figure 3 This is a flowchart illustrating a performance testing method for a low-Earth orbit satellite according to another embodiment of this application.

[0021] Figure 4 This is a schematic diagram of a low-orbit satellite performance testing system according to an embodiment of this application;

[0022] Figure 5 This is a schematic diagram of the structure of a performance testing device for a low-orbit satellite according to an embodiment of this application. Detailed Implementation

[0023] The embodiments of this application are described in detail below. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application.

[0024] The following description, with reference to the accompanying drawings, outlines a method, apparatus, device, and medium for testing the performance of low-Earth orbit satellites according to embodiments of this application.

[0025] Figure 1 This is a flowchart illustrating a performance testing method for low-Earth orbit satellites according to an embodiment of this application. Figure 1 As shown, the method includes:

[0026] S101, obtain the first test point and the first test time of the first low-orbit satellite to be tested.

[0027] During the daily operation of a low-Earth orbit (LEO) satellite constellation, communication between LEO satellites and the Earth's surface may interfere with the communication quality between related high-Earth orbit (HEO) satellites and the Earth's surface. In this scenario, corresponding interference avoidance functions can be set up for LEO satellites to reduce the degree of interference between LEO satellites and the Earth's surface communication and the communication quality between HEO satellites and the Earth's surface.

[0028] Optionally, the interference avoidance function of low-Earth orbit satellites may malfunction. In this scenario, the interference avoidance performance of low-Earth orbit satellites can be tested.

[0029] In this embodiment of the application, the low-orbit satellite to be tested can be identified as the first low-orbit satellite, and the test location point for testing the interference avoidance performance of the first low-orbit satellite can be identified as the first test point of the first low-orbit satellite. Optionally, a relevant system for testing the interference avoidance performance of the first low-orbit satellite can be deployed at the first test point. In this scenario, the time for the relevant system at the first test point to test the interference avoidance performance of the first low-orbit satellite can be identified as the first test time.

[0030] It should be noted that the first test time can be the collinearity time between the first low-Earth orbit satellite, the high-Earth orbit satellite that may cause communication interference from the first low-Earth orbit satellite, and the first test point, or it can be the time when the first low-Earth orbit satellite causes communication quality interference to the relevant high-Earth orbit satellite, and the first test point can observe the first low-Earth orbit satellite. No specific limitation is made here.

[0031] S102, through the first test point, acquire the first grounding level of the first low-orbit satellite during the first test time, and obtain the first signal beam direction of the first low-orbit satellite during the first test time.

[0032] In this embodiment of the application, a ground level data acquisition device is deployed at the first test point. Based on the deployment of this device, the first test point on the ground can acquire the ground level of the signal beam sent by the first low-orbit satellite at the first test time at the first test point. This ground level is the first ground level.

[0033] Optionally, the signal beam transmitted by the first low-orbit satellite when it passes the first test point has a set pointing direction, and the pointing direction of the signal beam transmitted by the first low-orbit satellite at the first test time can be determined as the first signal beam direction.

[0034] S103, based on the first ground level and the first signal beam direction, conduct interference avoidance performance test on the first low-orbit satellite, and obtain the first target performance test result of the first low-orbit satellite.

[0035] In a scenario where the interference avoidance performance of the first low-Earth orbit satellite is normal, the landing level and beam direction of the signal beam transmitted by the first low-Earth orbit satellite at the first test point are subject to their respective constraints. In this scenario, the obtained first landing level and first signal beam direction can be compared with their respective constraints to identify whether the first landing level and first signal beam direction match their respective constraints.

[0036] Optionally, the matching results of the first ground level and the first signal beam direction with their respective limiting conditions are obtained, and the interference avoidance performance of the current first low-orbit satellite is identified based on the matching results.

[0037] This can be understood as follows: when the matching result indicates that the first ground level and the first signal beam direction match their respective limiting conditions, it can be determined that the interference avoidance performance of the first low-orbit satellite in the current scenario is normal. Conversely, when the matching result indicates that the first ground level and the first signal beam direction do not match their respective limiting conditions, it can be determined that the interference avoidance performance of the first low-orbit satellite in the current scenario is abnormal.

[0038] Furthermore, based on the above-mentioned judgment, the test results of the interference avoidance performance of the first low-orbit satellite are obtained and used as the test results of the first target performance.

[0039] The proposed performance testing method for a first low-Earth orbit (LEO) satellite involves acquiring a first test point and a first test time for the LEO satellite. The first test point is used to obtain the first grounding voltage level and the first signal beam direction of the LEO satellite during the first test time. Based on the first grounding voltage level and the first signal beam direction, a first target performance test result for the interference avoidance performance of the LEO satellite is obtained. This application improves the accuracy and precision of LEO satellite interference avoidance performance testing by using two dimensions: the first grounding voltage level and the first signal beam direction. The use of a first test point set on the ground surface reduces the complexity of LEO satellite interference avoidance performance testing, optimizes the testing method and effect, and improves the efficiency of identifying performance anomalies in scenarios where LEO satellite interference avoidance performance is abnormal. This, in turn, improves the efficiency of handling anomalies in interference avoidance performance, enhances the stability of LEO satellite operation, and ultimately optimizes the communication stability and quality between high-Earth orbit satellites and the ground surface.

[0040] In the above embodiments, the interference avoidance performance test of the first low-orbit satellite can also be combined with... Figure 2 To understand further, Figure 2 This is a flowchart illustrating a performance testing method for a first low-Earth orbit satellite according to another embodiment of this application, as shown below. Figure 2 As shown, the method includes:

[0041] S201, obtain the first test point and the first test time of the first low-orbit satellite to be tested.

[0042] Optionally, candidate performance test points of the first low-orbit satellite are obtained, first ephemeris data of the first low-orbit satellite is obtained, and a first test point is determined from the candidate performance test points based on the first ephemeris data, wherein the first test point is observable for the first low-orbit satellite.

[0043] In this embodiment of the application, multiple test points can be preset on the ground, and a test point that can achieve the interference avoidance performance test of the first low-orbit satellite to be tested can be determined from the multiple test points as the first test point of the first low-orbit satellite. The multiple preset test points can be determined as candidate performance test points.

[0044] Optionally, ephemeris data of the first low-orbit satellite within a set historical time range can be obtained as the first ephemeris data, and test points that can observe the first low-orbit satellite under test can be identified from the candidate performance test points based on the first ephemeris data. These test points can then be used as the first test points for the interference avoidance performance test of the first low-orbit satellite.

[0045] Optionally, based on the first ephemeris data, the collinearity time between the first low-Earth orbit satellite, the corresponding high-Earth orbit satellite, and the first test point is calculated, and the first test time of the first low-Earth orbit satellite is obtained from the interference time period corresponding to the collinearity time.

[0046] In this embodiment of the application, the first low-orbit satellite, the high-orbit satellite corresponding to the first low-orbit satellite, and the first test point may be in a collinear state. In this scenario, the relevant information of the first low-orbit satellite, the high-orbit satellite corresponding to the first low-orbit satellite, and the first test point can be processed by an algorithm according to the collinearity time calculation method in the related technology to obtain the collinearity time among the three.

[0047] Optionally, the time interval corresponding to the collinearity time is obtained, and then a time that meets the preset conditions is selected from the time interval as the first test time of the first low-orbit satellite.

[0048] S202, acquire the spectrum acquisition software deployed at the first test point to obtain the first landing level matrix of the first low-orbit satellite, and obtain the first landing level corresponding to the first test time from the first landing level matrix.

[0049] In this embodiment of the application, the spectrum acquisition software deployed at the first test point can be used to track and record the landing level of the first low-orbit satellite within a set time range, and the first landing level matrix of the first low-orbit satellite can be obtained based on the recorded landing level and the acquisition time corresponding to the landing level.

[0050] In this scenario, the grounding level corresponding to the first test time can be obtained from the first grounding level matrix. This grounding level is the first grounding level corresponding to the first test time.

[0051] It should be noted that the first grounding level matrix can be in the matrix format corresponding to [Time 1: Data 1, Time 2: Data 2, ...], or it can be based on other preset matrix formats. No specific limitation is made here.

[0052] S203, obtain the second test time before the first test time and the third test time after the first test time, and obtain the second grounding level corresponding to the second test time and the third grounding level corresponding to the third test time from the first grounding level matrix.

[0053] In this embodiment of the application, a time that meets a preset condition can be obtained from a time range whose timing is earlier than the first test time, and used as a second test time preceding the first test time; and a time that meets a preset condition can be obtained from a time range whose timing is later than the first test time, and used as a third test time following the first test time.

[0054] In this scenario, the grounding level corresponding to the second test time can be obtained from the first grounding level matrix as the second grounding level, and the grounding level corresponding to the third test time can be obtained from the first grounding level matrix as the third grounding level.

[0055] S204, based on the first grounding level, the second grounding level and the third grounding level, obtain the first signal beam direction of the first low-orbit satellite during the first test time.

[0056] Optionally, the first telemetry data of the first low-orbit satellite corresponding to the first test time, the second telemetry data corresponding to the second test time, and the third telemetry data corresponding to the third test time can be acquired.

[0057] In this embodiment of the application, for the first low-orbit satellite to be tested, telemetry can be performed through a control center set up on the ground of the first low-orbit satellite. In this scenario, the control center can obtain the telemetry data of the first low-orbit satellite at the first test time as the first telemetry data, obtain the telemetry data of the first low-orbit satellite at the second test time as the second telemetry data, and obtain the telemetry data of the first low-orbit satellite at the third test time as the third telemetry data.

[0058] It should be noted that the acquisition of the above telemetry data can be achieved through the relevant information acquisition module 52 of the ground control center for monitoring the operational status of the first low-orbit satellite, or it can be achieved based on other methods that can acquire satellite status data. No specific limitation is made here.

[0059] Optionally, a first correspondence between the first telemetry data and the first grounding level, a second correspondence between the second telemetry data and the second grounding level, and a third correspondence between the third telemetry data and the third grounding level can be obtained.

[0060] In this embodiment of the application, the first telemetry data and the first grounding level can be processed by the data correspondence analysis algorithm in the related technology, and then the data correspondence between the first telemetry data and the first grounding level can be obtained according to the result of the algorithm processing, which is used as the first correspondence.

[0061] Furthermore, based on the same processing method, the data correspondence between the second telemetry data and the second grounding level is obtained as the second correspondence, and the data correspondence between the third telemetry data and the third grounding level is obtained as the third correspondence.

[0062] Optionally, in response to the first correspondence matching the second correspondence and the first correspondence matching the third correspondence, the first signal beam direction of the first transmitted signal of the first low-orbit satellite at the first test time is determined to be the direction not pointing to the test point.

[0063] In this embodiment of the application, the signal beam sent by the first low-orbit satellite at the first test time can be identified based on the matching results of the first correspondence and the second correspondence, as well as the matching results of the first correspondence and the third correspondence.

[0064] Specifically, when the first correspondence is the same as or similar to the second correspondence, it can be determined that the first correspondence matches the second correspondence; and when the first correspondence is the same as or similar to the third correspondence, it can be determined that the first correspondence matches the third correspondence.

[0065] During the daily operation of the first low-Earth orbit satellite, when the interference avoidance function of the first low-Earth orbit satellite is activated, the signal beam of the first low-Earth orbit satellite should not point to its corresponding ground observation point. Therefore, when the first correspondence matches the second correspondence and the first correspondence matches the third correspondence, it can be determined that the first signal beam of the first low-Earth orbit satellite does not point to the first test point. Furthermore, the direction of the first signal beam in this scenario can be determined as the direction of not pointing to the test point.

[0066] S205, based on the first ground level and the first signal beam direction, performs interference avoidance performance test on the first low-orbit satellite and obtains the first target performance test result of the first low-orbit satellite.

[0067] Optionally, in response to the presence of only background noise in the first ground level and the direction of the first signal beam not pointing to the test point, the first target performance test result of the first low-orbit satellite is determined to be that the interference avoidance performance is normal.

[0068] In this embodiment of the application, when the first landing level obtained by the first test point contains only background noise and the direction of the first signal beam is not pointing to the test point, it can be determined that the signal beam sent by the first low-orbit satellite in the current scenario does not point to the first test point during the first test time, and there is no service signal in the first landing level obtained by the first test point during the first test time. In this scenario, it can be determined that the first target performance test result obtained by the interference avoidance performance test of the first low-orbit satellite is that the interference avoidance performance of the first low-orbit satellite is normal.

[0069] Optionally, in response to the presence of signals other than noise floor in the first ground level, and / or the direction of the first signal beam pointing to the test point, the first target performance test result of the first low-orbit satellite is determined to be an abnormal interference avoidance performance.

[0070] In this embodiment of the application, when the interference avoidance performance of the first low-orbit satellite is effective, the first ground level obtained through the first test point should only contain background noise. Therefore, it can be seen that when there are other signals besides background noise in the first ground level obtained through the first test point, it can be determined that the interference avoidance performance of the first low-orbit satellite may be abnormal. In this scenario, the abnormal interference avoidance performance of the first low-orbit satellite can be taken as the first target performance test result obtained by the interference avoidance performance test of the first low-orbit satellite.

[0071] In this embodiment of the application, when the first signal beam of the first low-orbit satellite points to the first test point, the first test point can obtain the service signal carried in the first signal beam. Therefore, it can be seen that in the scenario where the direction of the first signal beam of the first signal beam sent by the first low-orbit satellite in the first test time is identified as the direction pointing to the test point, the first ground level obtained by the first test point carries the service signal sent by the first low-orbit satellite. In this scenario, it can be determined that the interference avoidance performance of the first low-orbit satellite is not effective, and the abnormal interference avoidance performance can be identified as the first target performance test result obtained by the first low-orbit satellite in the current interference avoidance performance test.

[0072] The performance testing method for low-Earth orbit (LEO) satellites proposed in this application tests interference avoidance performance through two dimensions: the first ground level and the first signal beam direction. This improves the accuracy and precision of LEO satellite interference avoidance performance testing. By using a first test point set on the ground surface to test the interference avoidance performance of LEO satellites, the complexity of the interference avoidance performance testing is reduced. This optimizes the testing method and test results for LEO satellite interference avoidance performance testing. In scenarios where LEO satellite interference avoidance performance is abnormal, the efficiency of performance anomaly identification is improved, thereby improving the efficiency of anomaly handling and enhancing the stability of LEO satellite operation performance. Ultimately, this optimizes the communication stability and quality between high-Earth orbit (HEO) satellites and the ground surface.

[0073] In the above embodiments, the first low-Earth orbit satellite constellation to which the first low-Earth orbit satellite belongs may or may not match the test system deployed at the first test point. This can be considered in conjunction with... Figure 3 To understand further, Figure 3 This is a flowchart illustrating a performance testing method for low-Earth orbit satellites according to another embodiment of this application, as shown below. Figure 3 As shown, the method includes:

[0074] S301, in response to the identification that the first low-orbit satellite constellation to which the first low-orbit satellite belongs is mismatched with the test system of the first test point, the target antenna direction inference strategy is obtained, and the target inference antenna pattern of the mismatched second low-orbit satellite constellation is obtained based on the target antenna direction inference strategy.

[0075] In this embodiment of the application, the first low-Earth orbit satellite constellation to which the first low-Earth orbit satellite belongs may or may not be compatible with the test system of the first test point.

[0076] Optionally, in response to the matching of the test system of the first low-Earth orbit satellite constellation to which the first low-Earth orbit satellite belongs with the test system of the first test point, it can be understood that the test system of the first test point can obtain relevant information such as the position and antenna direction of each first low-Earth orbit satellite in the first low-Earth orbit satellite constellation. In this scenario, the interference avoidance performance test of the corresponding first low-Earth orbit satellite can be performed by the test system deployed on the first test point based on the obtained sidelobe landing level. That is, the interference avoidance performance test of the first low-Earth orbit satellite is achieved by obtaining the first landing level and the first signal beam direction from the first test point as proposed in the above embodiment, and the corresponding first target performance test result is obtained.

[0077] Optionally, when it is identified that the test system deployed at the first test point does not match the first low-Earth orbit satellite constellation, it can be understood that the test system deployed at the first test point cannot obtain detailed information such as the antenna direction information and position information of each first low-Earth orbit satellite in the first low-Earth orbit satellite constellation.

[0078] In this scenario, the mismatched first low-Earth orbit (LEO) satellite constellation can be identified as the second LEO satellite constellation. The antenna orientation of each second LEO satellite in the second LEO satellite constellation can be deduced based on the antenna orientation deduction method in related technologies. Based on the antenna orientation pattern of the deduced second LEO satellite constellation, the interference avoidance performance of each second LEO satellite can be tested.

[0079] Specifically, the antenna orientation of each second low-Earth orbit satellite in the second low-Earth orbit satellite constellation can be deduced based on a preset target antenna orientation deduction strategy, and the deduced antenna orientation of each second low-Earth orbit satellite can be used to obtain the deduced antenna orientation of the second low-Earth orbit satellite constellation. This deduced antenna orientation can be determined as the target deduced antenna orientation of the second low-Earth orbit satellite constellation.

[0080] It should be noted that the second low-Earth orbit satellite constellation can be understood as a non-cooperative constellation of the system to which the first test point belongs, or it can be other types of constellations for which the first test point could not obtain detailed information; no specific limitation is made here.

[0081] In this embodiment of the application, the acquisition of the target antenna direction deduction strategy can be understood in conjunction with the following:

[0082] Optionally, obtain the reference antenna pattern of the first low-Earth orbit satellite constellation.

[0083] In this embodiment of the application, the first low-Earth orbit satellite constellation can be understood as the cooperative satellite constellation of the test system deployed at the first test point. In this scenario, the antenna direction of each first low-Earth orbit satellite in the first low-Earth orbit satellite constellation can be obtained through a preset information acquisition method, and the antenna pattern composed of the antenna directions of each first low-Earth orbit satellite can be determined as the reference antenna pattern of the first low-Earth orbit satellite constellation.

[0084] Optionally, based on multiple preset surface observation points, the data of the first satellite transit arc of the first low-orbit satellite during the first acquisition time period, and the second landing level matrix of the first low-orbit satellite during the first acquisition time period are collected.

[0085] In this embodiment of the application, multiple surface observation points can be set up in the surface area where each of the first low-orbit satellites in the first low-orbit satellite constellation can be observed. The data observation and acquisition systems deployed on each of the multiple surface observation points can be used to observe and acquire data from each of the first low-orbit satellites. The time period for observing and acquiring data from each of the first low-orbit satellites can be marked as the first acquisition time period for each of the first low-orbit satellites.

[0086] In this scenario, for any first low-orbit satellite, the data observation and acquisition systems deployed at multiple surface observation points are used to observe and acquire the transit arc data of the first low-orbit satellite as it passes through each surface observation point during the first acquisition time period. The acquired transit arc data of the first low-orbit satellite during the first acquisition time period is determined as the first satellite transit arc data of the first low-orbit satellite.

[0087] Furthermore, by using data observation and acquisition systems deployed at multiple surface observation points, the landing levels of the first low-orbit satellite as it passes through various surface observation points during the first acquisition period are observed and collected, and a second landing level matrix of the first low-orbit satellite during the first acquisition period is formed based on the collected landing levels.

[0088] Optionally, a candidate antenna orientation deduction strategy is obtained, and based on the candidate antenna orientation deduction strategy, the antenna orientation of the first low-Earth orbit satellite constellation is deduced based on the first satellite transit arc data and the second landing level matrix, to obtain the candidate deduced antenna pattern of the first low-Earth orbit satellite constellation.

[0089] In this embodiment of the application, the antenna direction inference strategy that has not been optimized and adjusted can be determined as the candidate antenna direction inference strategy. The candidate antenna direction inference strategy can be constructed based on the antenna direction inference algorithm in related technologies, or it can be constructed based on other methods that can realize antenna direction inference. No specific limitation is made here.

[0090] In this scenario, antenna orientation can be extrapolated for each of the first low-Earth orbit (LEO) satellites in the first LEO satellite constellation based on a candidate antenna orientation extrapolation strategy. Specifically, for any given LEO satellite, the antenna orientation can be extrapolated based on the first satellite transit arc data and the second landing level matrix of that LEO satellite using the candidate antenna orientation extrapolation strategy. This results in the extrapolated antenna orientations for each LEO satellite, and the antenna pattern composed of the extrapolated antenna orientations for each LEO satellite is determined as the candidate extrapolated antenna pattern for the first LEO satellite constellation.

[0091] Optionally, based on the candidate antenna radiation pattern and the reference antenna radiation pattern, the accuracy of the candidate antenna radiation strategy is adjusted to obtain the target antenna radiation strategy.

[0092] In this embodiment, the candidate antenna pattern and the reference antenna pattern can be processed by an image difference acquisition algorithm based on related technologies. The difference between the two is obtained based on the result of the algorithm processing. Then, the accuracy of the candidate antenna pattern inference strategy is adjusted based on the difference between the two, and the adjusted antenna pattern inference strategy is used as the target antenna pattern inference strategy.

[0093] In this embodiment of the application, the proposed antenna pattern and the reference antenna pattern can also be processed by matching algorithms in related technologies, and the candidate antenna pattern can be optimized and adjusted according to the results of the algorithm processing.

[0094] Optionally, in response to the matching of the candidate antenna pattern with the reference antenna pattern, the candidate antenna pattern prediction strategy is determined as the target antenna pattern prediction strategy.

[0095] In this embodiment of the application, when the candidate antenna pattern and the reference antenna pattern are identified... Figure 1 When the error is less than or equal to the preset error threshold, it can be determined that the candidate antenna pattern matches the reference antenna pattern.

[0096] When a candidate antenna pattern is found to match the reference antenna pattern, it can be determined that the current candidate antenna pattern prediction strategy meets the preset antenna pattern prediction accuracy conditions. In this scenario, the candidate antenna pattern prediction strategy in this scenario can be determined as the target antenna pattern prediction strategy.

[0097] Optionally, in response to a mismatch between the candidate antenna pattern and the reference antenna pattern, the simulation accuracy of the candidate antenna pattern simulation strategy is adjusted, and the antenna pattern simulation of the first low-Earth orbit satellite constellation is continued based on the adjusted candidate antenna pattern simulation strategy until the new candidate antenna pattern obtained based on the adjusted candidate antenna pattern simulation strategy matches the reference antenna pattern, thus obtaining the target antenna pattern simulation strategy.

[0098] In this embodiment of the application, when it is identified that the candidate antenna pattern is inconsistent with the reference antenna pattern or the error is greater than the preset error threshold, it can be determined that the accuracy of the current candidate antenna pattern inference strategy cannot meet the preset antenna pattern inference accuracy condition. In this scenario, the candidate antenna pattern inference strategy needs to be adjusted and optimized.

[0099] Specifically, the accuracy of the candidate antenna direction inference strategy can be adjusted based on a preset inference strategy accuracy adjustment method. Then, the antenna direction of the first low-Earth orbit satellite constellation can be continued to be inferred based on the adjusted candidate antenna direction inference strategy until the new candidate inference antenna pattern of the first low-Earth orbit satellite constellation obtained based on the adjusted candidate antenna direction inference strategy matches the reference antenna pattern. If the accuracy of the current adjusted candidate antenna direction inference strategy meets the preset accuracy condition, then the adjusted candidate antenna direction inference strategy can be determined as the target antenna direction inference strategy.

[0100] Optionally, the second ephemeris data and the second satellite transit arc data of the second low-orbit satellite are acquired, and the third landing level matrix of the second low-orbit satellite is collected through multiple preset surface observation points. Based on the pre-acquired target antenna direction inference strategy and the third landing level matrix, the antenna direction of the second low-orbit satellite is inferred to obtain the target inference antenna pattern of the second low-orbit satellite constellation.

[0101] In this embodiment of the application, multiple surface observation points can be set up in the area where each of the second low-orbit satellites in the second low-orbit satellite constellation can be observed on the ground. For any second low-orbit satellite, the transit arc of the second low-orbit satellite when passing through each surface observation point within a set time period can be obtained through the multiple surface observation points, thereby obtaining the second satellite transit arc data of the second low-orbit satellite. In addition, the landing level of the second low-orbit satellite when passing through each surface observation point within the same set time period can be obtained. Based on the collected landing levels, the landing level matrix of the second low-orbit satellite within the set time period can be obtained as the third landing balance matrix.

[0102] Furthermore, using a target antenna orientation extrapolation strategy, based on the transit arc data of the second satellite and the third landing balance matrix, the antenna orientation of each second low-Earth orbit satellite in the second low-Earth orbit satellite constellation is extrapolated, thereby obtaining the extrapolated antenna orientation of each second low-Earth orbit satellite. Further, the antenna pattern composed of the extrapolated antenna orientations of each second low-Earth orbit satellite is determined as the target extrapolated antenna pattern of the second low-Earth orbit satellite constellation.

[0103] Optionally, parameters of each second low-orbit satellite can be derived from the target-derived antenna pattern to obtain the off-axis angle parameters of each second low-orbit satellite.

[0104] In this embodiment of the application, for the second low-orbit satellite constellation that is not compatible with the test system of the first test point, after obtaining the target simulation antenna pattern of the second low-orbit satellite constellation, the off-axis angle of each second low-orbit satellite can be simulated based on the antenna direction information of each second low-orbit satellite in the target simulation antenna pattern.

[0105] Optionally, the antenna direction information of each second low-orbit satellite can be processed by an off-axis angle acquisition algorithm in related technologies, and the specific parameters of the off-axis angle of each second low-orbit satellite can be obtained based on the results of the algorithm processing, which can then be used as the off-axis angle parameters of each second low-orbit satellite.

[0106] S302, based on the target-inferred antenna pattern, the interference avoidance performance of the second low-Earth orbit satellite in the second low-Earth orbit satellite constellation is tested, and the second target performance test results of the second low-Earth orbit satellite are obtained.

[0107] Optionally, the second test point corresponding to the second low-orbit satellite is obtained, and the main lobe beam direction of the second low-orbit satellite at the fourth test time is obtained based on the target-derived antenna pattern.

[0108] In this embodiment of the application, an observation point that meets the preset observation conditions can be obtained from multiple ground observation points corresponding to the second low-orbit satellite on the ground, and a related interference avoidance performance testing system can be deployed at the observation point to obtain a test point that can realize the interference avoidance performance test of the second low-orbit satellite, which serves as the second test point of the second low-orbit satellite.

[0109] In this embodiment, the main lobe beam transmitted by the second low-orbit satellite can be received through the second test point, and the interference avoidance performance test of the corresponding second low-orbit satellite can be realized based on the grounding level of the main lobe beam.

[0110] Specifically, based on the target antenna pattern obtained through deduction, the transmission direction of the main lobe beam in the signal transmitted by the second low-orbit satellite under test at the preset fourth test time can be obtained, and this transmission direction can be determined as the main lobe beam direction of the second low-orbit satellite. The fourth test time can be the transmission time of the second low-orbit satellite to the signal carrying the main lobe beam, or it can be a time determined based on other set conditions, which is not specifically limited here.

[0111] Optionally, satellite identification information of the second low-orbit satellite can be obtained, and a search can be performed in the target simulation antenna pattern based on the satellite identification information to obtain the antenna direction of the second low-orbit satellite at the fourth test time from the target simulation antenna pattern. Further, the antenna direction can be analyzed and processed based on the main lobe beam determination method in related technologies, and then the main lobe beam direction of the second low-orbit satellite at the fourth test time can be obtained based on the analysis and processing results.

[0112] Optionally, in response to the main lobe beam direction pointing to the second test point, the fourth landing level of the second transmitted signal sent by the second low-orbit satellite at the second test point is obtained.

[0113] In this embodiment of the application, when the main lobe beam direction of the second low-orbit satellite is identified as pointing to the second test point, it can be determined that the second test point can receive the main lobe beam in the transmitted signal of the second low-orbit satellite. Therefore, it can be determined that the interference avoidance performance test of the second low-orbit satellite can be performed by the test system deployed on the second test point.

[0114] Optionally, the signal transmitted by the second low-orbit satellite at the fourth test time can be determined as the second transmitted signal, and based on the landing level acquisition module 51 in the test system deployed at the second test point, the landing level of the second transmitted signal at the second test point can be obtained based on the main lobe beam in the received second transmitted signal, and used as the fourth landing level.

[0115] Optionally, the second test point, the second low-Earth orbit satellite, and the calculated collinearity time corresponding to the second low-Earth orbit satellite are obtained to obtain the fifth landing level of the third transmitted signal sent by the second low-Earth orbit satellite at the second test point during the calculated collinearity time.

[0116] In this embodiment of the application, in the scenario of testing the interference avoidance performance of the second low-orbit satellite through the second test point, the relative positional relationship between the second low-orbit satellite, the second test point, and the high-orbit satellite that may cause interference can be calculated based on the ephemeris data of the second low-orbit satellite, so as to obtain the possible collinearity time among the three, which is used as the calculated collinearity time for the interference avoidance performance test of the second low-orbit satellite.

[0117] In this scenario, the signal transmitted by the second low-orbit satellite during the collinearity time can be received at the second test point to obtain the corresponding ground level of the signal, which is then used as the fifth ground level obtained through the second test point. This signal can then be identified as the third transmitted signal of the second low-orbit satellite.

[0118] Optionally, the second target performance test results of the second low-orbit satellite can be obtained based on the fifth and fourth grounding levels.

[0119] Among them, the result of the second target performance test is that the fifth landing level matches the fourth landing level, and it is determined that the second low-orbit satellite does not have interference avoidance measures.

[0120] In this embodiment of the application, when the fifth grounding level matches the fourth grounding level, it can be determined that the grounding level of the main lobe of the signal transmitted by the second low-orbit satellite during non-calculated collinear time is the same as or similar to the grounding level of the main lobe of the signal transmitted during calculated collinear time.

[0121] Therefore, it can be concluded that the second low-orbit satellite in this scenario did not activate the interference avoidance function when it was collinear with the second test point and the corresponding high-orbit satellite. Thus, it can be determined that the second low-orbit satellite did not have interference avoidance measures, and this result can be taken as the test result obtained by testing the interference avoidance performance of the second low-orbit satellite, i.e., the performance test result of the second target.

[0122] Furthermore, in response to the mismatch between the fifth and fourth grounding levels, the determination that the second low-orbit satellite has interference avoidance measures is the result of the second target performance test.

[0123] In this embodiment of the application, when the fifth landing level does not match the fourth landing level, it can be determined that the main lobe landing level of the signal transmitted by the second low-orbit satellite during non-calculated collinear time is different from the main lobe landing level of the signal transmitted during calculated collinear time.

[0124] Therefore, it can be seen that when the second low-orbit satellite in this scenario is collinear with the second test point and the corresponding high-orbit satellite, it activates the interference avoidance function. Thus, it can be determined that the second low-orbit satellite has interference avoidance measures, and this can be taken as the test result obtained by testing the interference avoidance performance of the second low-orbit satellite, that is, the performance test result of the second target.

[0125] In this embodiment of the application, the second test point may receive a sidelobe beam signal sent by a second low-orbit satellite, which can be understood in conjunction with the following:

[0126] Optionally, in response to the identification that the sidelobe beam direction of the second low-orbit satellite points to the second test point during the fourth test time, the main lobe beam direction of the second low-orbit satellite during the fourth test time is obtained based on the sidelobe beam direction and the target-derived antenna pattern.

[0127] In this embodiment of the application, in the scenario where the sidelobe beam direction in the signal transmitted by the second low-orbit satellite at the fourth test time is pointing towards the second test point, it can be determined that the second test point in this scenario cannot perform the interference avoidance performance test of the second low-orbit satellite based on the received sidelobe beam signal.

[0128] In this scenario, it is necessary to obtain the main lobe beam signal from the signal to which the sidelobe beam belongs, so as to test the interference avoidance performance of the second low-orbit satellite.

[0129] Specifically, based on a preset main lobe beam identification algorithm, the pointing direction of the side lobe beam corresponding to the side lobe beam signal and the target inference antenna pattern of the second low-orbit satellite constellation can be processed by the algorithm. Then, based on the result of the algorithm processing, the pointing direction of the main lobe beam signal corresponding to the signal to which the side lobe beam belongs can be obtained, which can be used as the main lobe beam direction of the second low-orbit satellite in the fourth test time.

[0130] Optionally, the pointing area of ​​the main lobe beam direction is obtained, and the main lobe beam received by the third test point in the pointing area is used to test the interference avoidance performance of the second low-orbit satellite, so as to obtain the second target performance test result of the second low-orbit satellite.

[0131] In this embodiment of the application, the pointing area on the ground can be determined based on the main lobe beam direction of the second low-orbit satellite. In this scenario, the ground level corresponding to the main lobe beam of the second low-orbit satellite can be obtained through the pointing area, thereby realizing the interference avoidance performance test of the second low-orbit satellite.

[0132] Optionally, there is a preset test point in the pointing area of ​​the main lobe beam direction. This test point can be determined as the third test point. In this scenario, the grounding level corresponding to the main lobe beam of the second low-orbit satellite can be obtained by the test system deployed on the third test point set in the pointing area, thereby realizing the interference avoidance performance test of the second low-orbit satellite, and the obtained test result is used as the second target performance test result of the second low-orbit satellite.

[0133] It should be noted that the detailed content of the interference avoidance performance test of the second low-Earth orbit satellite through the third test point in this scenario can be found in the relevant content of the interference avoidance performance test of the second low-Earth orbit satellite through the second test point proposed in the above embodiment, and will not be elaborated here.

[0134] The low-Earth orbit (LEO) satellite performance testing method proposed in this application obtains the target's deduced antenna pattern by deriving the antenna direction of each LEO satellite. This enables interference avoidance testing of each LEO satellite in a constellation that is incompatible with the test system of the first test point, improving the practicality and applicability of interference avoidance performance testing, and thereby optimizing the communication stability and quality between high-Earth orbit (HEO) satellites and the Earth's surface.

[0135] To better understand the above embodiments, it can be combined with Figure 4 , Figure 4 This is a schematic diagram of a low-orbit satellite performance testing system according to an embodiment of this application.

[0136] The test system deployed at each test point proposed in the above embodiments can provide... Figure 4 The test system shown is as follows: Figure 4 As shown, the test system may include Figure 4 The antenna assembly 41, the pivot assembly 42, the receiver assembly 43, the navigation and positioning assembly 44, the support assembly 45, and the control assembly 46 are shown.

[0137] Optionally, through Figure 4 The antenna assembly 41 shown can track and monitor the low-Earth orbit satellite under test, and receive and collect the transmitted signals of the low-Earth orbit satellite under test through the receiving assembly 43. Then, the algorithm software deployed on the control assembly 46 can be used to perform performance testing on the interference avoidance performance of the low-Earth orbit satellite under test.

[0138] like Figure 4As shown, the control component 46 is equipped with spectrum acquisition software. This software can acquire the transmission signals of low-Earth orbit satellites and obtain the corresponding grounding level of the low-Earth orbit satellite at the test point based on the received transmission signals. Then, based on the obtained grounding level, it can identify whether the interference avoidance performance of the corresponding low-Earth orbit satellite is normal, thereby obtaining the interference avoidance performance test results of the corresponding low-Earth orbit satellite.

[0139] In this embodiment of the application, when the ground level acquired by the spectrum acquisition software contains only background noise, it can be determined that the interference avoidance function of the low-orbit satellite transmitting the signal corresponding to the ground level is effective and operating normally. In this scenario, the normal interference avoidance performance can be taken as the test result obtained by the low-orbit satellite in the interference avoidance performance test.

[0140] Correspondingly, when the grounding level acquired by the spectrum acquisition software contains signals other than the noise floor, it can be determined that the interference avoidance function of the low-orbit satellite transmitting the signal corresponding to that grounding level may not exist, or the interference avoidance function may be malfunctioning. In this scenario, the abnormal interference avoidance performance can be taken as the test result obtained by the low-orbit satellite in the interference avoidance performance test.

[0141] like Figure 4 As shown, the testing system also includes... Figure 4 The rotating shaft assembly 42 shown can control the rotation of the antenna assembly 41 through its operation, thereby enabling the antenna assembly 41 to track and monitor relevant satellites.

[0142] like Figure 4 As shown, the testing system also includes... Figure 4 The support component 45 shown can be used to deploy the hardware of the test system for interference avoidance performance testing at various surface test points, thereby enabling interference avoidance performance testing of relevant low-orbit satellites at various surface test points.

[0143] like Figure 4 As shown, the testing system also includes... Figure 4 The navigation and positioning component 44 shown can acquire the position information of low-orbit satellites through the navigation and positioning system deployed in the navigation and positioning component 44. The position information can be latitude and longitude information or other types of position information, which are not specifically limited here.

[0144] It should be noted that, Figure 4 The navigation and positioning system deployed on the navigation and positioning component 44 shown can be the BeiDou positioning system, or other navigation and positioning systems that can acquire location information; no specific limitation is made here.

[0145] In this embodiment of the application, the control component 46 is further provided with driver software. The driver software sends drive commands to control the test system, such as... Figure 4 As shown, the control component 46 is also equipped with simulation calculation software, which meets the relevant simulation calculation requirements in the interference avoidance performance test and displays the relevant simulation test results on a preset display device.

[0146] The first low-Earth orbit (LEO) satellite performance testing system proposed in this application enables the deployment of the testing system at ground-based testing points to perform LEO satellite interference avoidance performance testing. Through the various components deployed in the testing system, interference avoidance performance testing of relevant LEO satellites based on ground-based testing points is realized, reducing the complexity of LEO satellite interference avoidance performance testing and optimizing the testing methods and results.

[0147] Corresponding to the performance testing methods for low-Earth orbit satellites proposed in the above embodiments, one embodiment of this application also proposes a performance testing device for low-Earth orbit satellites. Since the performance testing device for low-Earth orbit satellites proposed in this application corresponds to the performance testing methods for low-Earth orbit satellites proposed in the above embodiments, the implementation methods of the above-mentioned performance testing methods for low-Earth orbit satellites are also applicable to the performance testing device for low-Earth orbit satellites proposed in this application, and will not be described in detail in the following embodiments.

[0148] To achieve the above embodiments, this application also proposes a performance testing device for low-Earth orbit satellites. Figure 4 This is a schematic diagram of the structure of a low-orbit satellite performance testing device according to an embodiment of this application, as shown below. Figure 4 As shown, the low-Earth orbit satellite performance testing device 500 includes an acquisition module 51, a data acquisition module 52, and a testing module 53, wherein:

[0149] The acquisition module 51 is used to acquire the first test point and the first test time of the first low-orbit satellite to be tested;

[0150] The acquisition module 52 is used to acquire the first ground level of the first low-orbit satellite at the first test time through the first test point, and to obtain the first signal beam direction of the first low-orbit satellite at the first test time.

[0151] Test module 53 is used to perform interference avoidance performance test on the first low-orbit satellite based on the first ground level and the first signal beam direction, and obtain the first target performance test result of the first low-orbit satellite.

[0152] In this embodiment of the application, the acquisition module 52 is further configured to: acquire the spectrum acquisition software deployed at the first test point to obtain the first landing level matrix of the first low-orbit satellite, and obtain the first landing level corresponding to the first test time from the first landing level matrix; acquire the second test time preceding the first test time and the third test time following the first test time, and obtain the second landing level corresponding to the second test time and the third landing level corresponding to the third test time from the first landing level matrix; and acquire the first signal beam direction of the first low-orbit satellite under the first test time based on the first landing level, the second landing level and the third landing level.

[0153] In this embodiment of the application, the acquisition module 52 is further configured to: acquire first telemetry data corresponding to the first low-orbit satellite at the first test time, second telemetry data corresponding to the second test time, and third telemetry data corresponding to the third test time; acquire a first correspondence between the first telemetry data and the first grounding level, a second correspondence between the second telemetry data and the second grounding level, and a third correspondence between the third telemetry data and the third grounding level; and, in response to a match between the first and second correspondences and a match between the first and third correspondences, determine that the first signal beam direction of the first transmitted signal of the first low-orbit satellite at the first test time is a direction not pointing to the test point.

[0154] In this embodiment of the application, the test module 53 is further configured to: determine that the first target performance test result of the first low-orbit satellite is normal interference avoidance performance in response to the presence of only background noise in the first ground level and the direction of the first signal beam not pointing to the test point; and determine that the first target performance test result of the first low-orbit satellite is abnormal interference avoidance performance in response to the presence of other signals besides background noise in the first ground level and / or the direction of the first signal beam pointing to the test point.

[0155] In this embodiment of the application, the acquisition module 51 is further configured to: acquire candidate performance test points of the first low-orbit satellite; acquire the first ephemeris data of the first low-orbit satellite, and determine the first test point from the candidate performance test points based on the first ephemeris data, wherein the first test point is observable for the first low-orbit satellite; calculate the collinearity time between the first low-orbit satellite, the corresponding high-orbit satellite and the first test point based on the first ephemeris data, and acquire the first test time of the first low-orbit satellite from the interference time period corresponding to the collinearity time.

[0156] In this embodiment of the application, the test module 53 is further configured to: in response to the identification that the test system of the first low-orbit satellite constellation to which the first low-orbit satellite belongs is mismatched with that of the first test point, obtain a target antenna direction inference strategy, and obtain a target inference antenna pattern of the mismatched second low-orbit satellite constellation based on the target antenna direction inference strategy; perform interference avoidance performance test on the second low-orbit satellite in the second low-orbit satellite constellation based on the target inference antenna pattern, and obtain the second target performance test result of the second low-orbit satellite.

[0157] In this embodiment of the application, the test module 53 is further configured to: acquire a reference antenna pattern of the first low-Earth orbit (LEO) satellite constellation; collect data on the first satellite transit arc segment and the second landing level matrix of the first LEO satellite within a first acquisition time period based on multiple preset surface observation points; acquire a candidate antenna direction deduction strategy, and based on the candidate antenna direction deduction strategy, the first satellite transit arc segment data, and the second landing level matrix, perform antenna direction deduction on the first LEO satellite constellation to obtain a candidate deduction antenna pattern of the first LEO satellite constellation; and adjust the accuracy of the candidate antenna direction deduction strategy based on the candidate deduction antenna pattern and the reference antenna pattern to obtain a target antenna direction deduction strategy.

[0158] In this embodiment of the application, the test module 53 is further configured to: in response to a match between the candidate antenna pattern and the reference antenna pattern, determine the candidate antenna pattern prediction strategy as the target antenna pattern prediction strategy; in response to a mismatch between the candidate antenna pattern and the reference antenna pattern, return to adjust the prediction accuracy of the candidate antenna pattern prediction strategy, and continue to perform antenna pattern prediction on the first low-orbit satellite constellation based on the adjusted candidate antenna pattern prediction strategy, until the new candidate antenna pattern obtained based on the adjusted candidate antenna pattern prediction strategy matches the reference antenna pattern, thereby obtaining the target antenna pattern prediction strategy.

[0159] In this embodiment of the application, the test module 53 is further configured to: acquire the second ephemeris data and the second satellite transit arc data of the second low-orbit satellite, and collect the third landing level matrix of the second low-orbit satellite through multiple preset surface observation points; and perform antenna direction deduction on the second low-orbit satellite based on the pre-acquired target antenna direction deduction strategy and the third landing level matrix to obtain the target deduction antenna pattern of the second low-orbit satellite constellation.

[0160] In this embodiment, the test module 53 is further configured to: obtain the second test point corresponding to the second low-orbit satellite, and obtain the main lobe beam direction of the second low-orbit satellite at the fourth test time based on the target-deduced antenna pattern; in response to the main lobe beam direction pointing to the second test point, obtain the fourth landing level of the second transmission signal sent by the second low-orbit satellite at the second test point during the fourth test time; obtain the second test point, the second low-orbit satellite, and the calculated collinearity time corresponding to the second low-orbit satellite to obtain the fifth landing level of the third transmission signal sent by the second low-orbit satellite at the second test point during the calculated collinearity time; and obtain the second target performance test result of the second low-orbit satellite based on the fifth landing level and the fourth landing level.

[0161] In this embodiment of the application, the test module 53 is further configured to: determine that the second low-orbit satellite does not have interference avoidance measures as the second target performance test result in response to the fifth landing level matching the fourth landing level; and determine that the second low-orbit satellite has interference avoidance measures as the second target performance test result in response to the fifth landing level not matching the fourth landing level.

[0162] In this embodiment of the application, the test module 53 is further configured to: in response to identifying that the sidelobe beam direction of the second low-orbit satellite points to the second test point during the fourth test time, obtain the main lobe beam direction of the second low-orbit satellite during the fourth test time based on the sidelobe beam direction and the target-induced antenna pattern; obtain the pointing area of ​​the main lobe beam direction, and use the main lobe beam received by the preset third test point within the pointing area to perform interference avoidance performance testing on the second low-orbit satellite, thereby obtaining the second target performance test result of the second low-orbit satellite.

[0163] In this embodiment of the application, the test module 53 is further configured to: perform parameter deduction on each second low-orbit satellite based on the target deduction antenna pattern to obtain the off-axis angle parameters of each second low-orbit satellite.

[0164] The low-Earth orbit (LEO) satellite performance testing device proposed in this application acquires a first test point and a first test time for the LEO satellite. Through the first test point, it acquires the first grounding voltage level and the first signal beam direction of the LEO satellite during the first test time. Based on the first grounding voltage level and the first signal beam direction, it obtains the first target performance test result for the LEO satellite's interference avoidance performance. This application improves the accuracy and precision of LEO satellite interference avoidance performance testing by using two dimensions: the first grounding voltage level and the first signal beam direction. By implementing the interference avoidance performance test through a first test point set on the ground surface, the complexity of the LEO satellite interference avoidance performance test is reduced, optimizing the test method and test effect. In scenarios where LEO satellite interference avoidance performance is abnormal, it improves the efficiency of performance anomaly identification, thereby improving the efficiency of anomaly handling and enhancing the stability of LEO satellite operation performance. This, in turn, optimizes the communication stability and quality between high-Earth orbit (HEO) satellites and the ground surface.

[0165] To implement the above embodiments, this application also proposes an electronic device, including: a processor and a memory communicatively connected to the processor; the memory stores computer execution instructions; the processor executes the computer execution instructions stored in the memory to implement the performance testing method for low-orbit satellites provided in the foregoing embodiments.

[0166] To implement the above embodiments, this application also proposes a computer-readable storage medium storing computer-executable instructions, which, when executed by a processor, are used to implement the performance testing method for low-orbit satellites provided in the foregoing embodiments.

[0167] To implement the above embodiments, this application also proposes a computer program product, including a computer program that, when executed by a processor, implements the performance testing method for low-Earth orbit satellites provided in the foregoing embodiments.

[0168] The collection, storage, use, processing, transmission, provision, and disclosure of user personal information involved in this application all comply with the provisions of relevant laws and regulations and do not violate public order and good morals.

[0169] It should be noted that personal information collected from users should be used for legitimate and reasonable purposes and should not be shared or sold outside of these legitimate uses. Furthermore, such collection / sharing should only be conducted after receiving the user's informed consent, including but not limited to notifying the user to read the user agreement / user notice and sign an agreement / authorization that includes authorization of relevant user information before the user uses the function. In addition, any necessary steps must be taken to protect and safeguard access to such personal information data and ensure that others with access to personal information data comply with their privacy policies and procedures.

[0170] This application is intended to provide an implementation scheme for users to selectively prevent the use or access to their personal information data. Specifically, this disclosure is intended to provide hardware and / or software to prevent or block access to such personal information data. Once personal information data is no longer needed, risks can be minimized by restricting data collection and deleting data. Furthermore, where applicable, such personal information is de-identified to protect user privacy.

[0171] In the foregoing descriptions of the embodiments, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0172] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0173] Any process or method description in the flowchart or otherwise herein can be understood as representing a module, segment, or portion of code comprising one or more executable instructions for implementing custom logic functions or processes, and the scope of the preferred embodiments of this application includes additional implementations in which functions may be performed not in the order shown or discussed, including substantially simultaneously or in reverse order depending on the functions involved, as should be understood by those skilled in the art to which embodiments of this application pertain.

[0174] The logic and / or steps represented in the flowchart or otherwise described herein, for example, can be considered as a sequenced list of executable instructions for implementing logical functions, and can be embodied in any computer-readable medium for use by, or in conjunction with, an instruction execution system, apparatus, or device (such as a computer-based system, a processor-included system, or other system that can fetch and execute instructions from, an instruction execution system, apparatus, or device). For the purposes of this specification, "computer-readable medium" can be any means that can contain, store, communicate, propagate, or transmit programs for use by, or in conjunction with, an instruction execution system, apparatus, or device. More specific examples (a non-exhaustive list) of computer-readable media include: an electrical connection having one or more wires (electronic device), a portable computer disk drive (magnetic device), random access memory (RAM), read-only memory (ROM), erasable and editable read-only memory (EPROM or flash memory), fiber optic devices, and portable optical disc read-only memory (CDROM). Alternatively, the computer-readable medium may be paper or other suitable media on which the program can be printed, since the program can be obtained electronically, for example, by optically scanning the paper or other medium, followed by editing, interpreting, or otherwise processing as necessary, and then stored in a computer memory.

[0175] It should be understood that various parts of this application can be implemented using hardware, software, firmware, or a combination thereof. In the above embodiments, multiple steps or methods can be implemented using software or firmware stored in memory and executed by a suitable instruction execution system. For example, if implemented in hardware as in another embodiment, it can be implemented using any one or a combination of the following techniques known in the art: discrete logic circuits having logic gates for implementing logical functions on data signals, application-specific integrated circuits (ASICs) having suitable combinational logic gates, programmable gate arrays (PGAs), field-programmable gate arrays (FPGAs), etc.

[0176] Those skilled in the art will understand that all or part of the steps of the methods in the above embodiments can be implemented by a program instructing related hardware. The program can be stored in a computer-readable storage medium, and when executed, the program includes one or a combination of the steps of the method embodiments.

[0177] Furthermore, the functional units in the various embodiments of this application can be integrated into a processing module, or each unit can exist physically separately, or two or more units can be integrated into a module. The integrated module can be implemented in hardware or as a software functional module. If the integrated module is implemented as a software functional module and sold or used as an independent product, it can also be stored in a computer-readable storage medium.

[0178] The storage medium mentioned above can be a read-only memory, a disk, or an optical disk, etc. Although embodiments of this application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting this application. Those skilled in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of this application.

Claims

1. A performance testing method for low-Earth orbit satellites, characterized in that, The method includes: Obtain the first test point and the first test time for the first low-Earth orbit satellite to be tested; The first landing level of the first low-orbit satellite during the first test time is collected through the first test point, and the first signal beam direction of the first low-orbit satellite during the first test time is obtained. Based on the first grounding level and the first signal beam direction, interference avoidance performance tests are performed on the first low-Earth orbit satellite to obtain the first target performance test results of the first low-Earth orbit satellite, including: In response to the fact that only background noise exists in the first ground level and the direction of the first signal beam is not pointing to the test point, it is determined that the first target performance test result of the first low-orbit satellite is that the interference avoidance performance is normal. In response to the presence of signals other than background noise in the first grounding level, and / or the direction of the first signal beam pointing towards the test point, the first target performance test result of the first low-orbit satellite is determined to be an abnormal interference avoidance performance.

2. The method according to claim 1, characterized in that, The step of acquiring the first grounding level of the first low-Earth orbit satellite at the first test point and obtaining the first signal beam direction of the first low-Earth orbit satellite at the first test time includes: Obtain the spectrum acquisition software deployed at the first test point to obtain the first landing level matrix of the first low-orbit satellite, and obtain the first landing level corresponding to the first test time from the first landing level matrix; Obtain the second test time preceding the first test time and the third test time following the first test time, and obtain the second grounding level corresponding to the second test time and the third grounding level corresponding to the third test time from the first grounding level matrix; Based on the first landing level, the second landing level, and the third landing level, the first signal beam direction of the first low-orbit satellite during the first test time is obtained.

3. The method according to claim 2, characterized in that, The step of obtaining the first signal beam direction of the first low-Earth orbit satellite during the first test time based on the first grounding level, the second grounding level, and the third grounding level includes: Acquire the first telemetry data of the first low-orbit satellite at the first test time, the second telemetry data at the second test time, and the third telemetry data at the third test time; Obtain a first correspondence between the first telemetry data and the first grounding level, a second correspondence between the second telemetry data and the second grounding level, and a third correspondence between the third telemetry data and the third grounding level; In response to the first correspondence matching the second correspondence and the first correspondence matching the third correspondence, it is determined that the first signal beam direction of the first transmitted signal of the first low-orbit satellite at the first test time is not pointing to the test point.

4. The method according to claim 1, characterized in that, The acquisition of the first test point and the first test time of the first low-Earth orbit satellite to be tested includes: Obtain candidate performance test points for the first low-Earth orbit satellite; Acquire the first ephemeris data of the first low-orbit satellite, and determine the first test point from the candidate performance test points based on the first ephemeris data, wherein the first test point is observable for the first low-orbit satellite; Based on the first ephemeris data, the collinearity time between the first low-Earth orbit satellite, the corresponding high-Earth orbit satellite, and the first test point is calculated, and the first test time of the first low-Earth orbit satellite is obtained from the interference time period corresponding to the collinearity time.

5. The method according to claim 1, characterized in that, The method further includes: In response to the identification that the first low-Earth orbit satellite constellation to which the first low-Earth orbit satellite belongs is mismatched with the test system of the first test point, a target antenna direction inference strategy is obtained, and a target inference antenna pattern of the mismatched second low-Earth orbit satellite constellation is obtained based on the target antenna direction inference strategy. Based on the target-deduced antenna pattern, the interference avoidance performance of the second low-Earth orbit satellite in the second low-Earth orbit satellite constellation was tested, and the second target performance test results of the second low-Earth orbit satellite were obtained.

6. The method according to claim 5, characterized in that, The target antenna direction deduction strategy includes: Obtain the reference antenna pattern of the first low-Earth orbit satellite constellation; Based on multiple preset surface observation points, the data of the first satellite transit arc segment of the first low-orbit satellite during the first acquisition time period, and the second landing level matrix of the first low-orbit satellite during the first acquisition time period are collected. A candidate antenna orientation deduction strategy is obtained, and based on the candidate antenna orientation deduction strategy, the antenna orientation of the first low-Earth orbit satellite constellation is deduced based on the first satellite transit arc data and the second landing level matrix, to obtain the candidate deduced antenna pattern of the first low-Earth orbit satellite constellation. Based on the candidate antenna radiation pattern and the reference antenna radiation pattern, the accuracy of the candidate antenna radiation strategy is adjusted to obtain the target antenna radiation strategy.

7. The method according to claim 6, characterized in that, The step of adjusting the accuracy of the candidate antenna direction estimation strategy based on the candidate antenna pattern and the reference antenna pattern to obtain the target antenna direction estimation strategy includes: In response to the matching of the candidate antenna pattern with the reference antenna pattern, the candidate antenna pattern prediction strategy is determined as the target antenna pattern prediction strategy; In response to the mismatch between the candidate antenna pattern and the reference antenna pattern, the system returns to adjust the accuracy of the candidate antenna pattern prediction strategy, and continues to predict the antenna patterns of the first low-Earth orbit satellite constellation based on the adjusted candidate antenna pattern prediction strategy until the new candidate antenna pattern obtained based on the adjusted candidate antenna pattern prediction strategy matches the reference antenna pattern, thus obtaining the target antenna pattern prediction strategy.

8. The method according to claim 5, characterized in that, The method for obtaining the target-parallel antenna pattern of the mismatched second low-Earth orbit satellite constellation based on the target antenna direction deduction strategy includes: Acquire the second ephemeris data and the second satellite transit arc data of the second low-orbit satellite, and collect the third ground level matrix of the second low-orbit satellite through multiple preset surface observation points; Based on the pre-acquired target antenna direction deduction strategy and the third grounding level matrix, the antenna direction of the second low-orbit satellite is deduced to obtain the target deduction antenna pattern of the second low-orbit satellite constellation.

9. The method according to claim 5, characterized in that, The interference avoidance performance test of the second low-Earth orbit satellite based on the target-deduced antenna pattern is used to obtain the second target performance test results of the second low-Earth orbit satellite, including: Obtain the second test point corresponding to the second low-orbit satellite, and obtain the main lobe beam direction of the second low-orbit satellite at the fourth test time based on the target-derived antenna pattern; In response to the main lobe beam direction pointing to the second test point, the fourth landing level of the second transmitted signal sent by the second low-orbit satellite at the second test point is obtained during the fourth test time. The second test point, the second low-orbit satellite, and the calculated collinearity time corresponding to the second low-orbit satellite are obtained to obtain the fifth grounding level of the third transmitted signal sent by the second low-orbit satellite at the second test point during the calculated collinearity time. Based on the fifth and fourth grounding levels, the second target performance test results of the second low-orbit satellite are obtained.

10. The method according to claim 9, characterized in that, The step of obtaining the second target performance test results of the second low-Earth orbit satellite based on the fifth and fourth grounding levels includes: In response to the fifth landing level matching the fourth landing level, it is determined that the second low-orbit satellite does not have interference avoidance measures as the performance test result of the second target; In response to the mismatch between the fifth landing level and the fourth landing level, it is determined that the second low-orbit satellite has the interference avoidance measures as the performance test result of the second target.

11. The method according to claim 9, characterized in that, The method further includes: In response to the identification that the sidelobe beam direction of the second low-orbit satellite points to the second test point at the fourth test time, the main lobe beam direction of the second low-orbit satellite at the fourth test time is obtained based on the sidelobe beam direction and the target deduced antenna pattern. The pointing region of the main lobe beam direction is obtained, and the main lobe beam received through the third test point preset within the pointing region is used to perform interference avoidance performance test on the second low-orbit satellite, thereby obtaining the second target performance test result of the second low-orbit satellite.

12. The method according to claim 5, characterized in that, The method further includes: Based on the target-derived antenna pattern, the parameters of each second low-orbit satellite are derived to obtain the off-axis angle parameters of each second low-orbit satellite.

13. A performance testing device for low-orbit satellites, characterized in that, The device includes: The acquisition module is used to acquire the first test point and the first test time of the first low-Earth orbit satellite to be tested. The acquisition module is used to acquire the first grounding level of the first low-orbit satellite at the first test time through the first test point, and to obtain the first signal beam direction of the first low-orbit satellite at the first test time. The testing module is used to perform interference avoidance performance testing on the first low-Earth orbit satellite based on the first grounding level and the first signal beam direction, and to obtain the first target performance test results of the first low-Earth orbit satellite, including: In response to the fact that only background noise exists in the first ground level and the direction of the first signal beam is not pointing to the test point, it is determined that the first target performance test result of the first low-orbit satellite is that the interference avoidance performance is normal. In response to the presence of signals other than background noise in the first grounding level, and / or the direction of the first signal beam pointing towards the test point, the first target performance test result of the first low-orbit satellite is determined to be an abnormal interference avoidance performance.

14. An electronic device, characterized in that, include: A processor, and a memory communicatively connected to the processor; The memory stores computer-executed instructions; The processor executes computer execution instructions stored in the memory to implement the method as described in any one of claims 1-12.

15. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer-executable instructions, which, when executed by a processor, are used to implement the method as described in any one of claims 1-12.

16. A computer program product, characterized in that, Includes a computer program that, when executed by a processor, implements the method of any one of claims 1-12.

Images