Fault analysis method for low earth orbit satellite

Abstract

The invention discloses a fault analysis method for a low earth orbit satellite, and relates to the technical field of electric data analysis. The method comprises the following steps: collecting related data of influence of space debris on low-orbit satellite signal transmission, analyzing the related data of influence of the space debris on low-orbit satellite signal transmission to obtain an influence coefficient of the space debris on low-orbit satellite signal transmission, collecting related data of inter-satellite link network load balancing, and analyzing the related data of influence of the space debris on low-orbit satellite signal transmission. The inter-satellite link network load balancing related data is analyzed to obtain an inter-satellite link network load balancing evaluation coefficient, the IQ signal related data is collected, and the IQ signal related data is analyzed to obtain a difference evaluation coefficient between an IQ signal real-time value and a standard value. According to the invention, the problem that the communication interference between the low-orbit satellite and the ground station is too high in the prior art is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of electrical data analysis, and in particular to a fault analysis method for a low-orbit satellite. Background Art

[0002] With the rapid development of low-orbit satellite communication networks, fault analysis of low-orbit satellites has become increasingly important in order to ensure the safety and reliability of these satellites in orbit. The background of this approach lies in the unique operating environment of low-orbit satellites, whose high-speed movement relative to the earth's surface leads to frequent ground station switching, signal obstruction, and dynamically changing communication conditions.

[0003] Existing fault analysis methods are implemented through telemetry data analysis and real-time monitoring and early warning systems. For example, the invention patent with publication number CN119623314A discloses a method, device and equipment for predicting the orbital state of a low-orbit satellite, including: defining the pseudo-drag coefficient according to the atmospheric drag perturbation formula; performing a decomposition operation based on the pseudo-drag coefficient correlation analysis on the space environment parameters according to the VMD algorithm to obtain the space environment characteristic parameters, and the space environment parameters include the solar radiation flux index and the geomagnetic index; using the space environment characteristic parameters and the preset equivalent drag coefficient to train the initial SVM model for pseudo-drag coefficient prediction to obtain an optimized SVM model; predicting the pseudo-drag coefficient at future moments by optimizing the SVM model to obtain a pseudo-drag prediction value; predicting and calculating the orbital state of the low-orbit satellite according to the pseudo-drag prediction value to obtain a state prediction result.

[0004] For example, the invention patent with announcement number CN116560887B discloses a low-orbit satellite fault analysis method based on knowledge collaboration, including: building a knowledge graph based on the satellite fault manual and satellite maintenance log, and establishing a fault diagnosis model based on knowledge graph retrieval; designing a knowledge service system with knowledge collaboration based on the cloud-native KubeEdge platform; applying the knowledge graph and fault diagnosis model to the knowledge service system to realize a knowledge service system with knowledge collaboration and complete the analysis of low-orbit satellite faults.

[0005] The above technology has at least the following technical problems: In the prior art, there may be a large amount of space junk or space debris in the orbit of low-orbit satellites, which may cause communication interference to low-orbit satellites, resulting in excessive communication interference between low-orbit satellites and ground stations. Summary of the invention

[0006] The present invention solves the problem of excessive communication interference in the communication between the low-orbit satellite and the ground station in the prior art by providing a fault analysis method for the low-orbit satellite, thereby achieving the effect of reducing the communication interference in the communication between the low-orbit satellite and the ground station.

[0007] The present invention provides a fault analysis method for a low-orbit satellite, comprising the following steps: collecting data related to the influence of space debris on the signal transmission of the low-orbit satellite, analyzing the data related to the influence of space debris on the signal transmission of the low-orbit satellite, obtaining the influence coefficient of space debris on the signal transmission of the low-orbit satellite, performing threshold comparison on the influence coefficient of space debris on the signal transmission of the low-orbit satellite, issuing an alarm according to the comparison result and performing attitude adjustment on the low-orbit satellite; collecting data related to inter-satellite link network load balancing, analyzing the data related to inter-satellite link network load balancing, obtaining the inter-satellite link network load balancing evaluation coefficient, performing threshold comparison on the inter-satellite link network load balancing evaluation coefficient, evaluating whether there is a random link failure according to the comparison result and optimizing the inter-satellite link of the low-orbit satellite; collecting data related to IQ signals, analyzing the data related to IQ signals, obtaining the difference evaluation coefficient between the real-time value and the standard value of the IQ signals, performing threshold comparison on the difference evaluation coefficient between the real-time value and the standard value of the IQ signals, issuing an instruction according to the comparison result to perform link repair on the low-orbit satellite.

[0008] Furthermore, the specific analysis process for analyzing the data related to the impact of space debris on low-orbit satellite signal transmission is as follows: the data related to the impact of space debris on low-orbit satellite signal transmission include space orbit offset, real-time space debris density and received signal power attenuation change; the weight factor of the space orbit offset, the weight factor of the real-time space debris density and the weight factor of the received signal power attenuation change are obtained from the database, the space orbit offset, the real-time space debris density and the received signal power attenuation change are arranged in time series, the space orbit offset, the real-time space debris density and the received signal power attenuation change at each time series point are corrected using the corresponding weight factors, and the results of each correction are coupled and averaged to obtain the impact coefficient of space debris on low-orbit satellite signal transmission.

[0009] Furthermore, the specific process of performing threshold comparison on the coefficient of influence of space debris on low-orbit satellite signal transmission is as follows: obtaining the threshold of influence of space debris on low-orbit satellite signal transmission from the database, performing threshold comparison on the coefficient of influence of space debris on low-orbit satellite signal transmission and the threshold of influence of space debris on low-orbit satellite signal transmission; if the coefficient of influence of space debris on low-orbit satellite signal transmission is less than the threshold of influence of space debris on low-orbit satellite signal transmission, no adjustment is made to the low-orbit satellite; if the coefficient of influence of space debris on low-orbit satellite signal transmission is greater than or equal to the threshold of influence of space debris on low-orbit satellite signal transmission, the central processing unit issues an alarm and sends out instructions to adjust the attitude of the low-orbit satellite.

[0010] Furthermore, the specific process of issuing an alarm and adjusting the attitude of the low-orbit satellite based on the comparison results is as follows: the central processor sends an alarm to the ground station and shuts down internal sensitive equipment; the ground station receives the alarm, verifies and confirms it, formulates an avoidance strategy based on the current state and fuel reserves of the low-orbit satellite, generates an attitude adjustment instruction based on the avoidance strategy, and sends the attitude adjustment instruction to the low-orbit satellite operation module.

[0011] Furthermore, the specific process of analyzing the inter-satellite link network load balancing related data is as follows: the inter-satellite link network load balancing related data include single-satellite bandwidth utilization, traffic peak ratio and congestion triggering threshold; the weight factor of the single-satellite bandwidth utilization, the weight factor of the traffic peak ratio and the weight factor of the congestion triggering threshold are obtained from the database, the single-satellite bandwidth utilization, the traffic peak ratio and the congestion triggering threshold are arranged in a spatial sequence, the single-satellite bandwidth utilization, the traffic peak ratio and the congestion triggering threshold of each spatial sequence point are corrected using the corresponding weight factor, and the results of each correction processing are coupled and averaged to obtain the inter-satellite link network load balancing evaluation coefficient.

[0012] Furthermore, the specific process of threshold comparison of the intersatellite link network load balancing evaluation coefficient is as follows: obtain the intersatellite link network load balancing evaluation threshold from the database, compare the intersatellite link network load balancing evaluation coefficient with the intersatellite link network load balancing evaluation threshold, if the intersatellite link network load balancing evaluation coefficient is less than the intersatellite link network load balancing evaluation threshold, there is a random link failure in the low-orbit satellite and the intersatellite link is optimized for the low-orbit satellite, if the intersatellite link network load balancing evaluation coefficient is greater than or equal to the intersatellite link network load balancing evaluation threshold, no adjustment is made to the low-orbit satellite.

[0013] Furthermore, the specific process of evaluating whether there are random link failures and optimizing the inter-satellite links of low-orbit satellites based on the comparison results is as follows: performing threshold comparison on the inter-satellite link network load balancing evaluation coefficient, optimizing the inter-satellite links based on the threshold comparison results of the inter-satellite link network load balancing evaluation coefficient, including dynamically allocating bandwidth and designing a dynamic protocol adaptation mechanism, and simulating and verifying the compatibility under different topologies.

[0014] Furthermore, the specific process of analyzing the IQ signal related data is as follows: the IQ signal related data includes the signal-to-noise ratio of the IQ signal, the bit error rate of the IQ signal, the spectrum flatness of the IQ signal and the delay jitter of the IQ signal; the weight factor of the signal-to-noise ratio of the IQ signal, the weight factor of the bit error rate of the IQ signal, the weight factor of the spectrum flatness of the IQ signal and the weight factor of the delay jitter of the IQ signal are obtained from the database, the signal-to-noise ratio of the IQ signal, the bit error rate of the IQ signal, the spectrum flatness of the IQ signal and the delay jitter of the IQ signal are arranged in a phase sequence, and the deviation between the real-time value and the standard value of the signal-to-noise ratio of the IQ signal, the bit error rate of the IQ signal, the spectrum flatness of the IQ signal and the delay jitter of the IQ signal at each phase sequence point is corrected using the corresponding weight factor, and the results of each correction process are coupled and averaged to obtain the difference evaluation coefficient between the real-time value and the standard value of the IQ signal.

[0015] Furthermore, the specific process of performing threshold comparison on the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is as follows: obtaining the difference evaluation threshold between different components of the IQ signal from the database, performing threshold comparison on the difference evaluation coefficient between the real-time value and the standard value of the IQ signal and the difference evaluation threshold between different components of the IQ signal; if the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is less than the difference evaluation threshold between different components of the IQ signal, optimizing the IQ signal of the low-orbit satellite; if the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is less than the difference evaluation threshold between different components of the IQ signal, issuing an instruction to perform link repair on the low-orbit satellite.

[0016] Furthermore, the specific process of issuing instructions to repair the link of the low-orbit satellite based on the comparison results is: analyzing the difference evaluation coefficient between the real-time value and the standard value of the IQ signal, formulating a link repair strategy, sending instructions to the low-orbit satellite through the ground control station according to the link repair strategy, re-analyzing the difference evaluation coefficient between the real-time value and the standard value of the IQ signal, and performing a communication test.

[0017] One or more technical solutions provided by the present invention have at least the following technical effects or advantages: 1. By performing a threshold comparison on the difference evaluation coefficient between the real-time value and the standard value of the IQ signal, an instruction is issued according to the comparison result to repair the link of the low-orbit satellite, thereby achieving the effect of reducing the communication interference between the low-orbit satellite and the ground station, and effectively solving the problem of excessive communication interference between the low-orbit satellite and the ground station in the prior art.

[0018] 2. By comparing the thresholds of the inter-satellite link network load balancing evaluation coefficients, it is possible to evaluate whether there are random link failures based on the comparison results and optimize the inter-satellite links of low-orbit satellites, thereby achieving the effect of improving the stability of the inter-satellite links and effectively solving the problem of poor inter-satellite link stability in the prior art.

[0019] 3. By comparing the thresholds of the influence coefficients of space debris on the signal transmission of low-orbit satellites, an alarm is issued and the attitude of the low-orbit satellite is adjusted according to the comparison results, thereby achieving the effect of improving the safety of low-orbit satellites and effectively solving the problem of low safety of low-orbit satellites in existing technologies. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 A flow chart of a fault analysis method for a low-orbit satellite provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0021] The embodiment of the present invention solves the problem of excessive communication interference in the communication between the low-orbit satellite and the ground station in the prior art by providing a fault analysis method for the low-orbit satellite. By performing a threshold comparison on the difference evaluation coefficient between the real-time value and the standard value of the IQ signal, an instruction is issued according to the comparison result to repair the link of the low-orbit satellite, thereby achieving the effect of reducing the communication interference in the communication between the low-orbit satellite and the ground station.

[0022] The technical solution in the embodiment of the present invention is to solve the above-mentioned problem of excessive communication interference between the low-orbit satellite and the ground station. The overall idea is as follows: By collecting and analyzing the relevant data of space debris, intersatellite link network load balancing and IQ signals, the influence coefficient and evaluation coefficient are obtained respectively, and the threshold value is compared. According to the comparison results, the attitude of the low-orbit satellite is adjusted to avoid collision with space debris, the intersatellite link is optimized to prevent random failures, and the link problem is repaired to keep the communication smooth, thus achieving the effect of reducing the communication interference between the low-orbit satellite and the ground station.

[0023] In order to better understand the above technical solution, the above technical solution will be described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0024] like Figure 1As shown, it is a flow chart of a fault analysis method for a low-orbit satellite provided by an embodiment of the present invention, and the method includes the following steps: collecting data related to the impact of space debris on low-orbit satellite signal transmission, analyzing the data related to the impact of space debris on low-orbit satellite signal transmission, obtaining the impact coefficient of space debris on low-orbit satellite signal transmission, performing threshold comparison on the impact coefficient of space debris on low-orbit satellite signal transmission, issuing an alarm according to the comparison result and adjusting the attitude of the low-orbit satellite; collecting data related to inter-satellite link network load balancing, analyzing the data related to inter-satellite link network load balancing, obtaining the inter-satellite link network load balancing evaluation coefficient, performing threshold comparison on the inter-satellite link network load balancing evaluation coefficient, evaluating whether there is a random link failure according to the comparison result and optimizing the inter-satellite link of the low-orbit satellite; collecting data related to IQ signals, analyzing the data related to IQ signals, obtaining the difference evaluation coefficient between the real-time value and the standard value of the IQ signals, performing threshold comparison on the difference evaluation coefficient between the real-time value and the standard value of the IQ signals, and issuing an instruction to repair the link of the low-orbit satellite according to the comparison result.

[0025] Furthermore, the specific analysis process for analyzing the data related to the impact of space debris on low-orbit satellite signal transmission is as follows: the data related to the impact of space debris on low-orbit satellite signal transmission include space orbit offset, real-time space debris density and received signal power attenuation change; the weight factor of the space orbit offset, the weight factor of the real-time space debris density and the weight factor of the received signal power attenuation change are obtained from the database, the space orbit offset, the real-time space debris density and the received signal power attenuation change are arranged in time series, the space orbit offset, the real-time space debris density and the received signal power attenuation change at each time series point are corrected using the corresponding weight factors, and the results of each correction are coupled and averaged to obtain the impact coefficient of space debris on low-orbit satellite signal transmission.

[0026] In this embodiment, the specific method for obtaining the influence coefficient of space debris on low-orbit satellite signal transmission is: ; ; In the formula, It represents the influence coefficient of space debris on the signal transmission of low-orbit satellites. It is used to evaluate the influence of space debris on the signal transmission of low-orbit satellites. Several time monitoring points are set. , Represents the total number of time monitoring points, Indicates The space orbit deviation at the time monitoring point, The weight factor representing the space orbit offset, Indicates The real-time space debris density at each time monitoring point, A weighting factor representing the real-time space debris density, Indicates The received signal power attenuation changes at each time monitoring point, A weighting factor that represents the change in received signal power attenuation.

[0027] When the system is running, the mapping table of weight factors is obtained through the database, and the corresponding weight factors are quickly extracted according to the current space orbit offset, real-time space debris density and received signal power attenuation change, such as the weight factor of space orbit offset, the weight factor of real-time space debris density and the weight factor of received signal power attenuation change. This mapping table defines a clear set of association rules, which converts the specific values ​​of space orbit offset, real-time space debris density and received signal power attenuation change into their corresponding weight factors. Under this mechanism, whether it is to achieve a one-to-one precise match or a many-to-one relationship where multiple parameters converge into a single weight, the dynamic acquisition of weight factors can be effectively achieved.

[0028] The space orbit offset refers to the deviation between the actual orbit of the satellite and the predetermined orbit. The satellite is tracked and measured by ground tracking stations, and the actual orbital parameters of the satellite are monitored using radar, optics or other tracking technologies. The actual orbital parameters are then compared with the predetermined orbital parameters to calculate the orbital offset.

[0029] Real-time space debris density refers to the distribution of the number of debris objects in space within a certain time and space range, which can be directly obtained through ground radar systems.

[0030] The received signal power attenuation change refers to the situation that the power loss caused by various factors during the transmission of the signal changes with time or environmental conditions under certain conditions. The signal attenuation is analyzed by using electromagnetic simulation software (such as CST, ANSYS HFSS, etc.) to simulate the signal propagation environment.

[0031] High real-time space debris density may cause satellite collisions or require collision avoidance maneuvers, which may cause orbital deviations and lead to deteriorating communications. High debris density may increase the probability of signals being blocked or reflected, thereby causing changes in signal power attenuation and leading to deteriorating communications. Orbital deviations may cause changes in signal transmission paths, which in turn affect power attenuation and lead to deteriorating communications.

[0032] The greater the space orbit offset, the greater the impact of space debris on low-orbit satellite signal transmission; the greater the real-time space debris density, the greater the impact of space debris on low-orbit satellite signal transmission; the greater the change in received signal power attenuation, the greater the impact of space debris on low-orbit satellite signal transmission.

[0033] Furthermore, the specific process of performing threshold comparison on the coefficient of influence of space debris on low-orbit satellite signal transmission is as follows: obtaining the threshold of influence of space debris on low-orbit satellite signal transmission from the database, performing threshold comparison on the coefficient of influence of space debris on low-orbit satellite signal transmission and the threshold of influence of space debris on low-orbit satellite signal transmission; if the coefficient of influence of space debris on low-orbit satellite signal transmission is less than the threshold of influence of space debris on low-orbit satellite signal transmission, no adjustment is made to the low-orbit satellite; if the coefficient of influence of space debris on low-orbit satellite signal transmission is greater than or equal to the threshold of influence of space debris on low-orbit satellite signal transmission, the central processing unit issues an alarm and sends out instructions to adjust the attitude of the low-orbit satellite.

[0034] In this embodiment, first, the system needs to extract the threshold of the impact of space debris on the signal transmission of low-orbit satellites from a specially constructed database. This threshold is pre-set based on the design safety standards and operating requirements of the satellite to evaluate the potential threat of space debris to the safety of satellite operation. Then, the system compares and analyzes the impact coefficient of space debris on the signal transmission of low-orbit satellites obtained by real-time monitoring and calculation with the impact threshold extracted from the database. During the comparison process, if the calculated impact coefficient is lower than the impact threshold, it indicates that the threat of space debris to low-orbit satellites is within an acceptable range, so the satellite control system will not take any adjustment measures, and the satellite will continue to operate according to the established orbit and attitude. However, if the impact coefficient is greater than or equal to the impact threshold, it indicates that the threat of space debris to low-orbit satellites has reached a level that requires action. In this case, the central processor will immediately trigger the alarm system, send an alarm to the ground control center, and automatically generate and send instructions to the control system of the low-orbit satellite, instructing the satellite to make necessary attitude adjustments to avoid the area where the space debris blocks the signal.

[0035] Furthermore, the specific process of issuing an alarm and adjusting the attitude of the low-orbit satellite based on the comparison results is as follows: the central processor sends an alarm to the ground station and shuts down internal sensitive equipment; the ground station receives the alarm, verifies and confirms it, formulates an avoidance strategy based on the current state and fuel reserves of the low-orbit satellite, generates an attitude adjustment instruction based on the avoidance strategy, and sends the attitude adjustment instruction to the low-orbit satellite operation module.

[0036] In this embodiment, when the central processing unit (CPU) detects that the influence coefficient of space debris on the signal transmission of the low-orbit satellite reaches or exceeds the preset influence threshold, the alarm system is immediately activated, the CPU sends an alarm signal to the ground station, and shuts down sensitive equipment on the satellite through the internal command system to prevent damage to these equipment in a potential collision. The ground station receives the alarm signal from the satellite and starts the verification and confirmation process to ensure the accuracy and urgency of the alarm. The ground station analyzes the current state of the satellite, including its orbital position, attitude, speed, fuel reserves and other information. The automation system formulates a strategy to avoid space debris based on the current state and fuel reserves of the satellite. The avoidance strategy includes orbit change, speed adjustment, attitude adjustment and other operations to avoid the collision path of space debris. According to the formulated avoidance strategy, the ground station generates a specific attitude adjustment instruction, and the ground station sends the attitude adjustment instruction to the operation module of the low-orbit satellite through the uplink. After receiving the attitude adjustment instruction sent by the ground station, the operation module of the low-orbit satellite performs corresponding operations to adjust the attitude. While the satellite performs the attitude adjustment, it also needs to perform orbit maneuvers to completely avoid the threat of space debris.

[0037] The specific steps of the automation system to formulate a strategy to avoid space debris based on the current state and fuel reserves of the satellite are: automatically collect the current orbital parameters of the satellite (such as position, speed, orbital inclination, etc.), obtain the attitude information of the satellite (such as pitch, yaw, roll angle), monitor the fuel reserves of the satellite, including the type and remaining amount of propellant, use collision prediction algorithms (such as Conjunction Analysis for Satellite Traffic CONSAT) to assess the collision risk between the satellite and space debris, determine the time, distance and collision probability of the debris approaching the satellite, assess the degree of damage caused by the debris to the satellite, and determine whether avoidance measures are needed based on the threat assessment results. If avoidance is required, the system will generate a series of avoidance strategies, including: Orbital maneuver: change the orbital altitude or orbital inclination. Attitude adjustment: change the direction of the satellite to avoid the interference area of ​​space debris signals. Speed ​​change: accelerate or decelerate to change the orbital position of the satellite to avoid the interference area of ​​space debris signals. Use MATLAB to simulate the selected avoidance strategy to verify its effectiveness and safety. According to the final avoidance strategy, generate specific operation instructions, which should include execution time, operation steps and expected results.

[0038] Furthermore, the specific process of analyzing the inter-satellite link network load balancing related data is as follows: the inter-satellite link network load balancing related data include single-satellite bandwidth utilization, traffic peak ratio and congestion triggering threshold; the weight factor of the single-satellite bandwidth utilization, the weight factor of the traffic peak ratio and the weight factor of the congestion triggering threshold are obtained from the database, the single-satellite bandwidth utilization, the traffic peak ratio and the congestion triggering threshold are arranged in a spatial sequence, the single-satellite bandwidth utilization, the traffic peak ratio and the congestion triggering threshold of each spatial sequence point are corrected using the corresponding weight factor, and the results of each correction processing are coupled and averaged to obtain the inter-satellite link network load balancing evaluation coefficient.

[0039] In this embodiment, the specific method for obtaining the inter-satellite link network load balancing evaluation coefficient is: ; ; In the formula, It represents the intersatellite link network load balancing evaluation coefficient, which is used to evaluate the impact of intersatellite link network load balancing on intersatellite links. Several data monitoring points are set. , Indicates the total number of data monitoring points, Indicates The bandwidth utilization of a single satellite under each data monitoring point, The weight factor representing the bandwidth utilization of a single satellite, Indicates The peak traffic ratio under each data monitoring point, The weight factor representing the traffic peak ratio, Indicates The congestion triggering threshold under the data monitoring point is Indicates the weight factor of the congestion trigger threshold.

[0040] When the system is running, the mapping table of weight factors is obtained through the database. For example, the corresponding weight factors are quickly extracted according to the current single-satellite bandwidth utilization, traffic peak ratio and congestion trigger threshold, such as the weight factor of single-satellite bandwidth utilization, the weight factor of traffic peak ratio and the weight factor of congestion trigger threshold. This mapping table defines a clear set of association rules, which converts the specific values ​​of single-satellite bandwidth utilization, traffic peak ratio and congestion trigger threshold into their corresponding weight factors. Under this mechanism, whether it is to achieve one-to-one precise matching or a many-to-one relationship in which multiple parameters converge into a single weight, the dynamic acquisition of weight factors can be effectively achieved.

[0041] The bandwidth utilization rate of a single satellite refers to the ratio of the bandwidth actually used by a single satellite in a period of time to its total available bandwidth. It is calculated by monitoring the data transmission volume of the satellite in a specific period of time and comparing it with the total bandwidth capacity of the satellite. The formula is: (actual data transmission volume / total bandwidth capacity)*100%.

[0042] The peak traffic ratio refers to the ratio of the maximum value of data transmission traffic to the average value within a certain period of time. By monitoring the data traffic over a period of time, the maximum and average values ​​of the traffic are calculated, and then the ratio between the two is calculated. The formula is: (peak traffic / average traffic)*100%.

[0043] The congestion trigger threshold refers to the maximum bandwidth utilization that the satellite communication system can withstand. The congestion trigger threshold changes dynamically. If there are multiple low-orbit satellites around, the congestion trigger threshold is lowered according to a predefined ratio. If there is only one low-orbit satellite around, the congestion trigger threshold is increased according to a predefined ratio.

[0044] If the bandwidth utilization of a single satellite approaches or reaches the congestion trigger threshold, it indicates that the bandwidth resources of the satellite are about to be exhausted and the system is facing the risk of congestion. A high traffic peak ratio means large traffic fluctuations, which will cause the bandwidth utilization of a single satellite to exceed the congestion trigger threshold at the peak. The congestion trigger threshold is the standard for determining whether to take traffic management measures, while the bandwidth utilization of a single satellite and the traffic peak ratio are indicators for monitoring system performance. When the product of the bandwidth utilization of a single satellite and the traffic peak ratio exceeds the congestion trigger threshold, the system will take measures such as traffic control and bandwidth allocation adjustment to prevent or alleviate congestion.

[0045] Furthermore, the specific process of threshold comparison of the intersatellite link network load balancing evaluation coefficient is as follows: obtain the intersatellite link network load balancing evaluation threshold from the database, compare the intersatellite link network load balancing evaluation coefficient with the intersatellite link network load balancing evaluation threshold, if the intersatellite link network load balancing evaluation coefficient is less than the intersatellite link network load balancing evaluation threshold, there is a random link failure in the low-orbit satellite and the intersatellite link is optimized for the low-orbit satellite, if the intersatellite link network load balancing evaluation coefficient is greater than or equal to the intersatellite link network load balancing evaluation threshold, no adjustment is made to the low-orbit satellite.

[0046] In this embodiment, first, the system needs to extract the threshold value of the intersatellite link network load balancing evaluation from a specially constructed database. This threshold value is pre-set based on the performance requirements, reliability standards and historical operation data of the intersatellite link. It serves as an important basis for judging whether the intersatellite link network load balancing is in a normal working state. Then, the system will calculate in real time or obtain the intersatellite link network load balancing evaluation coefficient from the monitoring system. This coefficient is based on the actual working conditions of the intersatellite link, such as the bandwidth utilization rate of a single satellite, the peak traffic ratio and the congestion trigger threshold, and it reflects the current performance level of the intersatellite link. Then, the system compares and analyzes the intersatellite link network load balancing evaluation coefficient calculated in real time with the evaluation threshold value extracted from the database. If it is found that the intersatellite link network load balancing evaluation coefficient is less than the evaluation threshold value, it indicates that there is a random link failure in the low-orbit satellite. At this time, the system will start the intersatellite link optimization program, which includes a variety of measures such as adjustment of link parameters, reallocation of link resources, activation of backup links or establishment of new link connections to improve link performance and ensure the continuity and reliability of communication. On the contrary, if the intersatellite link network load balancing evaluation coefficient is greater than or equal to the evaluation threshold, it means that the intersatellite link network load balancing is in good condition, and the system will not take any adjustment measures, and the low-orbit satellite will continue to operate according to the established working mode. The implementation of the entire technical solution aims to ensure the effective management and optimization of the intersatellite link network load balancing through real-time monitoring and intelligent evaluation, thereby ensuring the stability and efficiency of the low-orbit satellite network.

[0047] Furthermore, the specific process of evaluating whether there are random link failures and optimizing the inter-satellite links of low-orbit satellites based on the comparison results is as follows: performing threshold comparison on the inter-satellite link network load balancing evaluation coefficient, optimizing the inter-satellite links based on the threshold comparison results of the inter-satellite link network load balancing evaluation coefficient, including dynamically allocating bandwidth and designing a dynamic protocol adaptation mechanism, and simulating and verifying the compatibility under different topologies.

[0048] In this embodiment, the system first extracts the threshold of the intersatellite link network load balancing evaluation from the database. The threshold is based on the link performance index, system reliability requirements and historical data analysis, and is used to determine whether the working status of the intersatellite link meets the established standards. Then, the system monitors and calculates the intersatellite link network load balancing evaluation coefficient in real time to quantify the current performance of the link. Next, the system compares the calculated intersatellite link network load balancing evaluation coefficient with the preset threshold. If the evaluation coefficient is lower than the threshold, it indicates that there is a bottleneck or potential failure in the link resources. At this time, the system will start the link optimization program. The optimization measures include dynamically allocating bandwidth, that is, automatically adjusting the bandwidth allocation of each link according to the actual needs and priority of the link to maximize bandwidth utilization and link performance; designing a dynamic protocol adaptation mechanism, that is, automatically selecting and adapting the most suitable communication protocol according to the link characteristics and communication requirements to improve the data transmission efficiency and stability of the link. In order to ensure the effectiveness of the optimization measures, the system will also verify the compatibility under different network topologies through simulation, that is, test the performance of the dynamic allocation of bandwidth and protocol adaptation mechanism under various topological structures in the simulated intersatellite link environment to ensure that the optimization measures can adapt to different network configurations and operating conditions in actual operation. The implementation of the entire technical solution aims to improve the overall performance and reliability of intersatellite links and ensure the smooth operation of the satellite network through intelligent resource management and dynamic optimization strategies.

[0049] The specific steps of dynamically allocating bandwidth are: real-time monitoring of intersatellite link traffic data, establishing a bandwidth resource pool, centrally managing all available bandwidth resources, selecting a bandwidth allocation algorithm with the shortest path first, and dynamically adjusting link bandwidth through control instructions based on the algorithm results. If the intersatellite link network load balancing evaluation coefficient is still less than the intersatellite link network load balancing evaluation threshold after dynamic bandwidth allocation, a dynamic protocol adaptation mechanism is designed.

[0050] The specific steps of designing a dynamic protocol adaptation mechanism are as follows: build a library containing multiple communication protocols, such as TCP, UDP, SDRP, and CCSDS, analyze the characteristics of the current intersatellite link, such as delay, packet loss rate, and bandwidth, select the most suitable communication protocol according to the link characteristics, such as selecting a protocol when the packet loss rate is higher than 10%, configure the selected protocol parameters in real time, and optimize the protocol configuration to improve communication efficiency based on link performance feedback. If the intersatellite link network load balancing evaluation coefficient is still less than the intersatellite link network load balancing evaluation threshold after designing the dynamic protocol adaptation mechanism, simulation is performed to verify the compatibility under different topologies.

[0051] The specific steps of simulation verification of compatibility under different topologies are as follows: Use MATLAB to establish a simulation model of the intersatellite link, simulate different network topologies, including clusters, constellations, link redundancy, etc., monitor key performance indicators during the simulation, such as throughput, delay, packet loss rate, bandwidth utilization, etc., and adjust the parameters of the dynamic bandwidth allocation and protocol adaptation mechanism according to the analysis results. If the intersatellite link network load balancing evaluation coefficient is still less than the intersatellite link network load balancing evaluation threshold after simulation verification of compatibility under different topologies, an alarm is issued.

[0052] Furthermore, the specific process of analyzing the IQ signal related data is as follows: the IQ signal related data includes the signal-to-noise ratio of the IQ signal, the bit error rate of the IQ signal, the spectrum flatness of the IQ signal and the delay jitter of the IQ signal; the weight factor of the signal-to-noise ratio of the IQ signal, the weight factor of the bit error rate of the IQ signal, the weight factor of the spectrum flatness of the IQ signal and the weight factor of the delay jitter of the IQ signal are obtained from the database, the signal-to-noise ratio of the IQ signal, the bit error rate of the IQ signal, the spectrum flatness of the IQ signal and the delay jitter of the IQ signal are arranged in a phase sequence, and the deviation between the real-time value and the standard value of the signal-to-noise ratio of the IQ signal, the bit error rate of the IQ signal, the spectrum flatness of the IQ signal and the delay jitter of the IQ signal at each phase sequence point is corrected using the corresponding weight factor, and the results of each correction process are coupled and averaged to obtain the difference evaluation coefficient between the real-time value and the standard value of the IQ signal.

[0053] In this embodiment, the specific method for obtaining the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is: ; ; In the formula, Indicates the difference evaluation coefficient between the real-time value and the standard value of the IQ signal, which is used to evaluate the situation of the IQ signal after being affected by space debris. Indicates the number of the phase monitoring point, c, Represents the total number of phase monitoring points, Indicates The signal-to-noise ratio of the IQ signal at each phase monitoring point is represents the signal-to-noise ratio of the standard IQ signal, The weight factor representing the signal-to-noise ratio of the IQ signal, Indicates The bit error rate of the IQ signal at each phase monitoring point, The weight factor representing the bit error rate of the IQ signal, represents the bit error rate of the standard IQ signal, Indicates The spectrum flatness of the IQ signal at each phase monitoring point, The weight factor representing the spectral flatness of the IQ signal, Indicates the spectrum flatness of the standard IQ signal, Indicates The delay jitter of the IQ signal at each phase monitoring point is The weight factor representing the delay jitter of the IQ signal, Indicates the delay jitter of the standard IQ signal.

[0054] When the system is running, the mapping table of weight factors is obtained through the database, and the corresponding weight factors are quickly extracted according to the current signal-to-noise ratio of the IQ signal, the bit error rate of the IQ signal, the spectrum flatness of the IQ signal, and the delay jitter of the IQ signal, such as the weight factor of the signal-to-noise ratio of the IQ signal, the weight factor of the bit error rate of the IQ signal, the weight factor of the spectrum flatness of the IQ signal, and the weight factor of the delay jitter of the IQ signal. This mapping table defines a clear set of association rules, which converts the specific values ​​of the signal-to-noise ratio of the IQ signal, the bit error rate of the IQ signal, the spectrum flatness of the IQ signal, and the delay jitter of the IQ signal into their corresponding weight factors. Under this mechanism, whether it is to achieve a one-to-one precise match or a many-to-one relationship in which multiple parameters converge into a single weight, the dynamic acquisition of weight factors can be effectively achieved.

[0055] The signal-to-noise ratio can be calculated by measuring the signal power and the noise power and then calculating their ratio.

[0056] The bit error rate can be measured by transmitting a known bit sequence through simulation or an actual communication system and then detecting the number of bit errors at the receiving end.

[0057] Spectrum flatness refers to the consistency of the signal amplitude across the entire frequency band. A spectrum analyzer is used to scan the entire frequency band of the signal and measure the amplitude at different frequency points.

[0058] Delay jitter refers to the degree of delay variation during signal transmission. Time measurement equipment (such as a time interval analyzer) is used to measure the fluctuation of signal arrival time. For example, if a signal arrives every 50 milliseconds but is delayed or advanced, it can be called delay jitter.

[0059] The signal-to-noise ratio is a key factor affecting the bit error rate. The higher the signal-to-noise ratio, the less noise in the signal, and the lower the bit error rate. Poor spectrum flatness causes the signal power to decrease in certain frequency bands, thus affecting the signal-to-noise ratio. Delay jitter causes the signal to lose synchronization at the receiving end, affecting the synchronization and correct decoding of the signal, thereby increasing the bit error rate. Delay jitter is caused by system nonlinearity, which also affects spectrum flatness.

[0060] The higher the signal-to-noise ratio, the better the quality of the IQ signal is usually, and the smaller the difference evaluation coefficient between the real-time value and the standard value is. The higher the bit error rate, the larger the difference evaluation coefficient between the real-time value and the standard value. Poor spectrum flatness will cause the amplitude of some frequency components to deviate from the standard value, thereby increasing the difference evaluation coefficient between the real-time value and the standard value. Large delay jitter will lead to inaccurate signal timing, which will also increase the difference evaluation coefficient between the real-time value and the standard value.

[0061] Furthermore, the specific process of performing threshold comparison on the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is as follows: obtaining the difference evaluation threshold between different components of the IQ signal from the database, performing threshold comparison on the difference evaluation coefficient between the real-time value and the standard value of the IQ signal and the difference evaluation threshold between different components of the IQ signal; if the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is less than the difference evaluation threshold between different components of the IQ signal, optimizing the IQ signal of the low-orbit satellite; if the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is less than the difference evaluation threshold between different components of the IQ signal, issuing an instruction to perform link repair on the low-orbit satellite.

[0062] In this embodiment, first, the system extracts the thresholds for evaluating the difference between different components of the IQ signal from a pre-configured database. These thresholds are set according to the performance requirements of the satellite communication system, historical data analysis, and preset safety standards, and are used to determine whether the quality of the IQ signal meets the communication requirements. Next, the system monitors and calculates the difference evaluation coefficient between the real-time value and the standard value of the IQ signal of the low-orbit satellite in real time. The coefficient is a comprehensive indicator that includes parameters such as signal-to-noise ratio, bit error rate, spectrum flatness, and delay jitter to quantify the overall performance of the IQ signal. Then, the system compares the calculated difference evaluation coefficient between the real-time value and the standard value of the IQ signal with the evaluation threshold extracted from the database. If the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is greater than or equal to the evaluation threshold, it indicates that the quality of the IQ signal does not meet the expected standard. At this time, the system will start the optimization program, including adjusting the transmission power, changing the modulation and demodulation mode, optimizing the filter settings, or reconfiguring the signal and other measures to improve the quality of the IQ signal. If the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is greater than or equal to the evaluation threshold, it means that the quality of the IQ signal meets the requirements. However, if there is a link failure or potential problem, the system will issue a command to repair the link of the low-orbit satellite, which involves link reconfiguration, fault detection, positioning and repair operations. The implementation of the entire technical solution is aimed at ensuring that the IQ signal of the low-orbit satellite is always in the best working state and ensuring the stability and reliability of satellite communications.

[0063] Adjust the transmit power: First, monitor the output level of the current transmit power of the low-orbit satellite. According to the difference evaluation coefficient between the real-time value of the IQ signal and the standard value and the communication link status, if the real-time value of the IQ signal is less than the standard value, increase the transmit power; if the real-time value of the IQ signal is greater than or equal to the standard value, reduce the transmit power. Adjust the transmit power through the power amplifier (PA) on the satellite. If the power needs to be increased, the gain of the PA can be increased; if the power needs to be reduced, the gain can be reduced. After adjustment, monitor the change in transmit power through the ground station or other satellites, and evaluate whether the IQ signal quality has improved. If the difference evaluation coefficient between the real-time value of the IQ signal and the standard value is still greater than the difference evaluation threshold between the real-time value of the IQ signal and the standard value, change the modulation and demodulation mode.

[0064] Change the modulation and demodulation mode: Evaluate whether the modulation mode currently used (such as BPSK, QPSK, 16-QAM, etc.) is suitable for the current communication environment. Select a more suitable modulation mode according to the channel conditions and communication requirements. For example, if the signal-to-noise ratio is lower than the predetermined threshold of 20dB, it is necessary to switch to a more robust modulation mode. Update the configuration on the satellite's modem, including the modulation mode and the corresponding demodulation parameters. After changing the modulation mode, perform a link test to ensure that the signal can be sent and received correctly. If the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is still greater than the difference evaluation threshold between the real-time value and the standard value of the IQ signal, optimize the filter settings.

[0065] Optimize filter settings: Check the bandwidth, cutoff frequency, and filtering effect of the current filter. According to the quality of the IQ signal, adjust the parameters of the filter, such as bandwidth, cutoff frequency, and roll-off factor, to reduce interference and signal distortion. If necessary, design a new filter to meet specific communication needs. Verify the performance of the filter through the signal analysis tool to ensure that the signal quality is improved. If the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is still greater than the difference evaluation threshold between the real-time value and the standard value of the IQ signal, reconfigure the signal processing algorithm and reconfigure the retrograde signal.

[0066] Reconfigure the signal processing algorithm: Analyze the performance of the current signal processing algorithm, including bit error rate, signal synchronization, and channel coding efficiency. Select a more appropriate signal processing algorithm or design a new algorithm based on communication requirements and environmental changes. Update the algorithm configuration on the satellite's signal processing unit, including encoding, decoding, synchronization, and equalization. Verify the performance of the new algorithm through simulation and actual communication tests to ensure that the signal quality meets the communication standard. If the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is still greater than the difference evaluation threshold between the real-time value and the standard value of the IQ signal, an alarm is issued to the satellite ground station.

[0067] Furthermore, the specific process of issuing instructions to repair the link of the low-orbit satellite based on the comparison results is: analyzing the difference evaluation coefficient between the real-time value and the standard value of the IQ signal, formulating a link repair strategy, sending instructions to the low-orbit satellite through the ground control station according to the link repair strategy, re-analyzing the difference evaluation coefficient between the real-time value and the standard value of the IQ signal, and performing a communication test.

[0068] In this embodiment, the IQ signal data of the low-orbit satellite is monitored and collected in real time, including key parameters such as signal-to-noise ratio, bit error rate, spectrum flatness, and delay jitter, and the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is calculated. The difference evaluation coefficient between the real-time value and the standard value of the IQ signal is compared with a preset threshold value to determine whether there is performance degradation or link failure. According to the analysis result of the difference evaluation coefficient between the real-time value and the standard value of the IQ signal, the specific cause of the performance degradation is identified, and a targeted link repair strategy is formulated. The link repair strategy is converted into a specific instruction sequence, and the uplink of the ground control station is used to perform the link repair. The command is sent to the low-orbit satellite. After executing the link repair command, the IQ signal data is collected again, the difference evaluation coefficient between the new IQ signal real-time value and the standard value is calculated, the effect of the link repair operation is evaluated, and the difference evaluation coefficient between the IQ signal real-time value and the standard value before and after the repair is compared to verify whether the link performance is improved. A series of communication tests are performed, such as signal transmission test, bit error rate test, link stability test, and the test results are analyzed to determine whether the link has returned to normal working state. If the link performance still does not meet the standard, the link repair strategy is adjusted according to the test results, and the above steps are repeated until the problem is solved.

[0069] Signal transmission test: Generate a known signal (such as a sine wave, square wave, or a specific modulated signal) as a test signal, send the test signal through a communication link, and at the receiving end, use an oscilloscope, spectrum analyzer, or other test equipment to receive the signal and analyze its amplitude, phase, frequency and other parameters. Compare the received signal with the original signal sent to check for distortion, attenuation, or other changes.

[0070] Bit error rate test: The transmitter generates a known bit sequence, which can be a pseudo-random sequence or other standard test sequence, and sends the test sequence through the communication link. The receiving end receives the data and stores it. The received data is compared with the original data sequence sent, and the bit error rate is calculated. The test is repeated under different conditions (such as different signal strengths, noise levels, etc.) to evaluate how the bit error rate changes with the conditions.

[0071] Link stability test: Continuously transmit specially designed test data on the link, continuously monitor multiple link parameters in real time, such as signal strength, bit error rate, delay, jitter, etc., record the changes in link performance over time, and analyze the fluctuations in link performance.

[0072] The link repair strategy includes controlling the direction of the satellite antenna through software instructions and quickly switching to the backup link. Quickly switching to the backup link means building multiple non-intersecting shortest paths as alternatives, and dynamically switching the optimal path based on the priority mechanism (latency and packet loss rate). If the latency is higher than the preset value, it switches to a route with a latency lower than the preset value. If the packet loss rate is higher than the preset value, it switches to a route with a packet loss rate lower than the preset value to improve fault tolerance.

[0073] It will be appreciated by those skilled in the art that embodiments of the present invention may be provided as methods, systems, or computer program products. Therefore, the present invention may take the form of a complete hardware embodiment, a complete software embodiment, or an embodiment combining software and hardware. Furthermore, the present invention may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0074] The present invention is described with reference to flowcharts and / or block diagrams of methods, devices (systems), and computer program products according to embodiments of the present invention. It should be understood that each process and / or block in the flowchart and / or block diagram, as well as the combination of processes and / or blocks in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 A process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0075] These computer program instructions may also be stored in a computer-readable memory capable of directing a computer or other programmable data processing device to operate in a specific manner, so that the instructions stored in the computer-readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 A process or multiple processes and / or boxes Figure 1 A function specified in one or more boxes.

[0076] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operating steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing instructions for implementing the process. Figure 1 A process or multiple processes and / or boxes Figure 1 The steps for the functions specified in one or more boxes.

[0077] Although the preferred embodiments of the present invention have been described, those skilled in the art may make other changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present invention.

[0078] Obviously, those skilled in the art may make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. A fault analysis method for a low-orbit satellite, characterized in that: The following steps are involved: Collect data related to the impact of space debris on low-orbit satellite signal transmission, analyze the data related to the impact of space debris on low-orbit satellite signal transmission, obtain the impact coefficient of space debris on low-orbit satellite signal transmission, compare the threshold of the impact coefficient of space debris on low-orbit satellite signal transmission, issue an alarm and adjust the attitude of the low-orbit satellite according to the comparison results; Collect intersatellite link network load balancing related data, analyze the intersatellite link network load balancing related data, obtain the intersatellite link network load balancing evaluation coefficient, compare the thresholds of the intersatellite link network load balancing evaluation coefficient, evaluate whether there is a random link failure based on the comparison results, and optimize the intersatellite link of the low-orbit satellite; Collect and analyze IQ signal related data to obtain the difference evaluation coefficient between the real-time value and the standard value of the IQ signal, perform threshold comparison on the difference evaluation coefficient between the real-time value and the standard value of the IQ signal, and issue instructions to repair the link of the low-orbit satellite based on the comparison results.

2. The fault analysis method for a low-orbit satellite according to claim 1, characterized in that: The specific analysis process of analyzing the data related to the impact of space debris on low-orbit satellite signal transmission is as follows: The data related to the impact of space debris on low-orbit satellite signal transmission include space orbit deviation, real-time space debris density and changes in received signal power attenuation; The weight factor of the space orbit offset, the weight factor of the real-time space debris density and the weight factor of the received signal power attenuation change are obtained from the database, and the space orbit offset, the real-time space debris density and the received signal power attenuation change are arranged in time series. The space orbit offset, the real-time space debris density and the received signal power attenuation change at each time series point are corrected using the corresponding weight factors, and the results of each correction are coupled and averaged to obtain the influence coefficient of space debris on low-orbit satellite signal transmission.

3. The fault analysis method for a low-orbit satellite according to claim 1, characterized in that: The specific process of comparing the threshold values ​​of the influence coefficient of space debris on low-orbit satellite signal transmission is as follows: The threshold of the impact of space debris on low-orbit satellite signal transmission is obtained from the database, and the impact coefficient of space debris on low-orbit satellite signal transmission is compared with the threshold of the impact of space debris on low-orbit satellite signal transmission. If the impact coefficient of space debris on low-orbit satellite signal transmission is less than the threshold of the impact of space debris on low-orbit satellite signal transmission, the low-orbit satellite will not be adjusted. If the impact coefficient of space debris on low-orbit satellite signal transmission is greater than or equal to the threshold of the impact of space debris on low-orbit satellite signal transmission, the central processing unit will issue an alarm and send out instructions to adjust the attitude of the low-orbit satellite.

4. The fault analysis method for a low-orbit satellite according to claim 1, characterized in that: The specific process of issuing an alarm and adjusting the attitude of the low-orbit satellite according to the comparison result is as follows: The central processor sends an alarm to the ground station and shuts down internal sensitive equipment. The ground station receives the alarm, verifies and confirms it, formulates an avoidance strategy based on the current status and fuel reserves of the low-orbit satellite, generates attitude adjustment instructions based on the avoidance strategy, and sends the attitude adjustment instructions to the low-orbit satellite operation module.

5. The fault analysis method for a low-orbit satellite according to claim 1, characterized in that: The specific process of analyzing the intersatellite link network load balancing related data is as follows: The data related to intersatellite link network load balancing include single-satellite bandwidth utilization, traffic peak ratio and congestion trigger threshold; The weight factors of single-satellite bandwidth utilization, traffic peak ratio and congestion trigger threshold are obtained from the database, and the single-satellite bandwidth utilization, traffic peak ratio and congestion trigger threshold are arranged in a spatial sequence. The single-satellite bandwidth utilization, traffic peak ratio and congestion trigger threshold of each spatial sequence point are corrected using the corresponding weight factors, and the results of each correction are coupled and averaged to obtain the inter-satellite link network load balancing evaluation coefficient.

6. The fault analysis method for a low-orbit satellite according to claim 1, characterized in that: The specific process of comparing the thresholds of the inter-satellite link network load balancing evaluation coefficients is as follows: The intersatellite link network load balancing evaluation threshold is obtained from the database, and the intersatellite link network load balancing evaluation coefficient is compared with the intersatellite link network load balancing evaluation threshold. If the intersatellite link network load balancing evaluation coefficient is less than the intersatellite link network load balancing evaluation threshold, there is a random link failure in the low-orbit satellite and the intersatellite link is optimized for the low-orbit satellite. If the intersatellite link network load balancing evaluation coefficient is greater than or equal to the intersatellite link network load balancing evaluation threshold, no adjustment is made to the low-orbit satellite.

7. The fault analysis method for a low-orbit satellite according to claim 1, characterized in that: The specific process of evaluating whether there is a random link failure based on the comparison result and optimizing the inter-satellite link of the low-orbit satellite is as follows: The thresholds of the inter-satellite link network load balancing evaluation coefficients are compared, and the inter-satellite links are optimized according to the threshold comparison results of the inter-satellite link network load balancing evaluation coefficients, including dynamic allocation of bandwidth and design of dynamic protocol adaptation mechanism, and the compatibility under different topologies is simulated and verified.

8. The fault analysis method for a low-orbit satellite according to claim 1, characterized in that: The specific process of analyzing the IQ signal related data is as follows: IQ signal related data include the signal-to-noise ratio of the IQ signal, the bit error rate of the IQ signal, the spectrum flatness of the IQ signal and the delay jitter of the IQ signal; The weight factor of the signal-to-noise ratio of the IQ signal, the weight factor of the bit error rate of the IQ signal, the weight factor of the spectrum flatness of the IQ signal and the weight factor of the delay jitter of the IQ signal are obtained from the database, and the signal-to-noise ratio of the IQ signal, the bit error rate of the IQ signal, the spectrum flatness of the IQ signal and the delay jitter of the IQ signal are arranged in a phase sequence, and the deviation between the real-time value and the standard value of the signal-to-noise ratio of the IQ signal, the bit error rate of the IQ signal, the spectrum flatness of the IQ signal and the delay jitter of the IQ signal at each phase sequence point is corrected using the corresponding weight factor, and the results of each correction processing are coupled and averaged to obtain the difference evaluation coefficient between the real-time value and the standard value of the IQ signal.

9. The fault analysis method for a low-orbit satellite according to claim 1, characterized in that: The specific process of performing threshold comparison on the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is as follows: The difference assessment threshold between different components of the IQ signal is obtained from the database, and the difference assessment coefficient between the real-time value and the standard value of the IQ signal is compared with the difference assessment threshold between different components of the IQ signal. If the difference assessment coefficient between the real-time value and the standard value of the IQ signal is less than the difference assessment threshold between different components of the IQ signal, the IQ signal of the low-orbit satellite is optimized. If the difference assessment coefficient between the real-time value and the standard value of the IQ signal is less than the difference assessment threshold between different components of the IQ signal, an instruction is issued to repair the link of the low-orbit satellite.

10. The fault analysis method for a low-orbit satellite according to claim 1, characterized in that: The specific process of issuing instructions to repair the link of the low-orbit satellite according to the comparison result is as follows: Analyze the difference evaluation coefficient between the real-time value and the standard value of the IQ signal, formulate a link repair strategy, send instructions to the low-orbit satellite through the ground control station according to the link repair strategy, re-analyze the difference evaluation coefficient between the real-time value and the standard value of the IQ signal, and conduct communication tests.

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