A fault analysis method for low-earth orbit satellites

Abstract

The present invention discloses a fault analysis method for low-earth orbit satellites, which relates to the technical field of electrical data analysis. The method includes: collecting data related to the impact of space debris on the signal transmission of low-earth orbit satellites, analyzing the data related to the impact of space debris on the signal transmission of low-earth orbit satellites to obtain the impact coefficient of space debris on the signal transmission of low-earth orbit satellites, collecting data related to the network load balancing of inter-satellite links, analyzing the data related to the network load balancing of inter-satellite links to obtain the evaluation coefficient of the network load balancing of inter-satellite links, collecting data related to IQ signals, and analyzing the data related to IQ signals to obtain the difference evaluation coefficient between the real-time value and the standard value of IQ signals. The present invention solves the problem of excessive communication interference in the communication between low-earth orbit satellites and ground stations in the prior art.

Description

Technical Field

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

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

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

[0004] For example, a method for fault analysis of low-earth orbit satellites based on knowledge collaboration disclosed in the invention patent with the announcement number CN116560887B includes: constructing a knowledge graph according to the satellite fault manual and the satellite maintenance log, and establishing a fault diagnosis model based on knowledge graph retrieval; designing a knowledge service system for knowledge collaboration based on the cloud-native KubeEdge platform; and applying the knowledge graph and the fault diagnosis model to the knowledge service system to implement the knowledge service system for knowledge collaboration and complete the analysis of low-earth orbit satellite faults.

[0005] The above technologies have at least the following technical problems:

[0006] In the prior art, there may be a large amount of space debris or space junk in the orbit where the low-earth orbit satellite is located, and the space debris or space junk will cause communication interference to the low-earth orbit satellite, resulting in the problem of excessive communication interference between the low-earth orbit satellite and the ground station. Summary of the Invention

[0007] By providing a fault analysis method for low-earth orbit satellites, the present invention solves the problem of excessive communication interference between the low-earth orbit satellite and the ground station in the prior art, and achieves the effect of reducing the communication interference between the low-earth orbit satellite and the ground station.

[0008] The present invention provides a fault analysis method for low-earth orbit satellites, including the following steps: collecting data related to the impact of space debris on the signal transmission of low-earth orbit satellites, analyzing the data related to the impact of space debris on the signal transmission of low-earth orbit satellites to obtain the impact coefficient of space debris on the signal transmission of low-earth orbit satellites, comparing the impact coefficient of space debris on the signal transmission of low-earth orbit satellites with a threshold, issuing an alarm according to the comparison result and adjusting the attitude of the low-earth orbit satellite; collecting data related to the load balancing of the inter-satellite link network, analyzing the data related to the load balancing of the inter-satellite link network to obtain the load balancing evaluation coefficient of the inter-satellite link network, comparing the load balancing evaluation coefficient of the inter-satellite link network with a threshold, evaluating whether there is a random link failure according to the comparison result and optimizing the inter-satellite link of the low-earth orbit satellite; collecting data related to IQ signals, analyzing the data related to IQ signals to obtain the difference evaluation coefficient between the real-time value and the standard value of the IQ signal, comparing the difference evaluation coefficient between the real-time value and the standard value of the IQ signal with a threshold, and issuing an instruction to repair the link of the low-earth orbit satellite according to the comparison result.

[0009] Further, the specific analysis process for analyzing the data related to the impact of space debris on the signal transmission of low-earth orbit satellites is as follows: the data related to the impact of space debris on the signal transmission of low-earth orbit satellites includes the space orbit offset, the real-time space debris density, and the change in the attenuation of the received signal power; obtaining the weight factors of the space orbit offset, the real-time space debris density, and the change in the attenuation of the received signal power from the database, arranging the space orbit offset, the real-time space debris density, and the change in the attenuation of the received signal power in a time series, correcting the space orbit offset, the real-time space debris density, and the change in the attenuation of the received signal power at each time series point using the corresponding weight factors, and coupling and averaging the results of each correction process to obtain the impact coefficient of space debris on the signal transmission of low-earth orbit satellites.

[0010] Further, the specific process for comparing the impact coefficient of space debris on the signal transmission of low-earth orbit satellites with a threshold is as follows: obtaining the impact threshold of space debris on the signal transmission of low-earth orbit satellites from the database, comparing the impact coefficient of space debris on the signal transmission of low-earth orbit satellites with the impact threshold of space debris on the signal transmission of low-earth orbit satellites. If the impact coefficient of space debris on the signal transmission of low-earth orbit satellites is less than the impact threshold of space debris on the signal transmission of low-earth orbit satellites, the low-earth orbit satellite is not adjusted. If the impact coefficient of space debris on the signal transmission of low-earth orbit satellites is greater than or equal to the impact threshold of space debris on the signal transmission of low-earth orbit satellites, the central processing unit issues an alarm and issues an instruction to adjust the attitude of the low-earth orbit satellite.

[0011] Further, the specific process of issuing an alarm based on the comparison result and adjusting the attitude of the low-Earth orbit satellite is as follows: The central processor issues an alarm to the ground station and shuts down the internal sensitive devices. The ground station receives the alarm, verifies and confirms it, formulates an avoidance strategy based on the current state and fuel reserve of the low-Earth orbit satellite, generates an attitude adjustment instruction according to the avoidance strategy, and sends the attitude adjustment instruction to the low-Earth orbit satellite operation module.

[0012] Further, the specific process of analyzing the data related to the load balancing of the inter-satellite link network is as follows: The data related to the load balancing of the inter-satellite link network includes the single-satellite bandwidth utilization rate, the traffic peak ratio, and the congestion trigger threshold. Obtain the weight factors of the single-satellite bandwidth utilization rate, the weight factor of the traffic peak ratio, and the weight factor of the congestion trigger threshold from the database. Arrange the single-satellite bandwidth utilization rate, the traffic peak ratio, and the congestion trigger threshold in a spatial sequence. Use the corresponding weight factors to correct the single-satellite bandwidth utilization rate, the traffic peak ratio, and the congestion trigger threshold at each spatial sequence point, and couple and average the results of each correction process to obtain the evaluation coefficient of the load balancing of the inter-satellite link network.

[0013] Further, the specific process of comparing the evaluation coefficient of the load balancing of the inter-satellite link network with a threshold is as follows: Obtain the evaluation threshold of the load balancing of the inter-satellite link network from the database. Compare the evaluation coefficient of the load balancing of the inter-satellite link network with the evaluation threshold of the load balancing of the inter-satellite link network. If the evaluation coefficient of the load balancing of the inter-satellite link network is less than the evaluation threshold of the load balancing of the inter-satellite link network, there is a random link failure in the low-Earth orbit satellite and the inter-satellite link of the low-Earth orbit satellite is optimized. If the evaluation coefficient of the load balancing of the inter-satellite link network is greater than or equal to the evaluation threshold of the load balancing of the inter-satellite link network, no adjustment is made to the low-Earth orbit satellite.

[0014] Further, 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-Earth orbit satellite is as follows: Compare the evaluation coefficient of the load balancing of the inter-satellite link network with a threshold. Optimize the inter-satellite link according to the threshold comparison result of the evaluation coefficient of the load balancing of the inter-satellite link network, including dynamically allocating bandwidth and designing a dynamic protocol adaptation mechanism, and simulate and verify the compatibility under different topologies.

[0015] Further, the specific process for 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 spectral flatness of the IQ signal, and the delay jitter of the IQ signal; Obtain the weight factors of the signal-to-noise ratio of the IQ signal, the weight factors of the bit error rate of the IQ signal, the weight factors of the spectral flatness of the IQ signal, and the weight factors of the delay jitter of the IQ signal from the database, arrange the signal-to-noise ratio of the IQ signal, the bit error rate of the IQ signal, the spectral flatness of the IQ signal, and the delay jitter of the IQ signal in the phase sequence, and use the corresponding weight factors to correct 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 spectral flatness of the IQ signal, and the delay jitter of the IQ signal at each phase sequence point, and couple and average the results of each correction process to obtain the difference evaluation coefficient between the real-time value and the standard value of the IQ signal.

[0016] Further, the specific process for comparing the difference evaluation coefficient between the real-time value and the standard value of the IQ signal with the threshold is as follows: Obtain the difference evaluation threshold between different components of the IQ signal from the database, compare the difference evaluation coefficient between the real-time value and the standard value of the IQ signal with 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, optimize the IQ signal of the low-earth 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, send a command to repair the link of the low-earth orbit satellite.

[0017] Further, the specific process for sending a command to repair the link of the low-earth 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 a command to the low-earth 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 a communication test.

[0018] One or more technical solutions provided by the present invention have at least the following technical effects or advantages:

[0019] 1. By comparing the difference evaluation coefficient between the real-time value and the standard value of the IQ signal with the threshold, a command is sent to repair the link of the low-earth orbit satellite according to the comparison result, thereby achieving the effect of reducing the communication interference between the low-earth orbit satellite and the ground station, and effectively solving the problem of excessive communication interference between the low-earth orbit satellite and the ground station in the prior art.

[0020] 2. By comparing the threshold of the inter-satellite link network load balancing evaluation coefficient, it is possible to evaluate whether there is a random link failure according to the comparison result and optimize the inter-satellite link of the low-earth orbit satellite, thereby achieving the effect of improving the stability of the inter-satellite link and effectively solving the problem of overly poor stability of the inter-satellite link in the prior art.

[0021] 3. By comparing the threshold of the influence coefficient of space debris on the signal transmission of low-earth orbit satellites, an alarm is issued according to the comparison result and the attitude of the low-earth orbit satellite is adjusted, thereby achieving the effect of improving the safety of the low-earth orbit satellite and effectively solving the problem of overly low safety of the low-earth orbit satellite in the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a flowchart of a fault analysis method for low-earth orbit satellites provided by an embodiment of the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0023] An embodiment of the present invention provides a fault analysis method for low-earth orbit satellites, which solves the problem of overly high communication interference between low-earth orbit satellites and ground stations in the prior art. By comparing the threshold of 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-earth orbit satellite, thereby achieving the effect of reducing the communication interference between the low-earth orbit satellite and the ground station.

[0024] The technical solution in the embodiment of the present invention is to solve the above problem of overly high communication interference between low-earth orbit satellites and ground stations. The general idea is as follows:

[0025] By collecting and analyzing relevant data of space debris, inter-satellite link network load balancing, and IQ signals, influence coefficients and evaluation coefficients are obtained respectively, and threshold comparisons are made. According to the comparison results, the attitude of the low-earth orbit satellite is adjusted to avoid being hit by space debris, the inter-satellite link is optimized to prevent random failures, and the link problem is repaired to keep the communication smooth, achieving the effect of reducing the communication interference between the low-earth orbit satellite and the ground station.

[0026] 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 of the specification and specific embodiments.

[0027] Such as Figure 1As shown in the figure, it is a flowchart of a fault analysis method for low-Earth orbit satellites provided by an embodiment of the present invention. The method includes the following steps: collecting data related to the impact of space debris on the signal transmission of low-Earth orbit satellites, analyzing the data related to the impact of space debris on the signal transmission of low-Earth orbit satellites to obtain the impact coefficient of space debris on the signal transmission of low-Earth orbit satellites, comparing the impact coefficient of space debris on the signal transmission of low-Earth orbit satellites with a threshold, and issuing an alarm and adjusting the attitude of the low-Earth orbit satellite according to the comparison result; collecting data related to the load balancing of the inter-satellite link network, analyzing the data related to the load balancing of the inter-satellite link network to obtain the evaluation coefficient of the load balancing of the inter-satellite link network, comparing the evaluation coefficient of the load balancing of the inter-satellite link network with a threshold, and evaluating whether there is a random link failure and optimizing the inter-satellite link of the low-Earth orbit satellite according to the comparison result; collecting data related to IQ signals, analyzing the data related to IQ signals to obtain the difference evaluation coefficient between the real-time value and the standard value of the IQ signal, comparing the difference evaluation coefficient between the real-time value and the standard value of the IQ signal with a threshold, and issuing an instruction to repair the link of the low-Earth orbit satellite according to the comparison result.

[0028] Further, the specific analysis process for analyzing the data related to the impact of space debris on the signal transmission of low-Earth orbit satellites is as follows: The data related to the impact of space debris on the signal transmission of low-Earth orbit satellites includes the space orbit offset, the real-time space debris density, and the change in the received signal power attenuation; obtaining the weight factors of the space orbit offset, the real-time space debris density, and the change in the received signal power attenuation from the database, arranging the space orbit offset, the real-time space debris density, and the change in the received signal power attenuation in a time series, performing correction processing on the space orbit offset, the real-time space debris density, and the change in the received signal power attenuation at each time series point using the corresponding weight factors, and coupling and averaging the results of each correction processing to obtain the impact coefficient of space debris on the signal transmission of low-Earth orbit satellites.

[0029] In this embodiment, the specific method for obtaining the impact coefficient of space debris on the signal transmission of low-Earth orbit satellites is as follows:

[0030] ;

[0031] ;

[0032] In the formula, represents the impact coefficient of space debris on the signal transmission of low-Earth orbit satellites, which is used to evaluate the impact of space debris on the signal transmission of low-Earth orbit satellites. Set several time monitoring points,

[0033] , represents the total number of time monitoring points, represents the 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.

[0034] 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.

[0035] 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.

[0036] 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.

[0037] 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.

[0038] 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.

[0039] The greater the space orbit offset, the greater the influence coefficient of space debris on the signal transmission of low-earth orbit satellites; the greater the real-time space debris density, the greater the influence coefficient of space debris on the signal transmission of low-earth orbit satellites; the greater the attenuation change of the received signal power, the greater the influence coefficient of space debris on the signal transmission of low-earth orbit satellites.

[0040] Furthermore, the specific process of comparing the influence coefficient of space debris on the signal transmission of low-earth orbit satellites with a threshold is as follows: Obtain the influence threshold of space debris on the signal transmission of low-earth orbit satellites from the database, and compare the influence coefficient of space debris on the signal transmission of low-earth orbit satellites with the influence threshold of space debris on the signal transmission of low-earth orbit satellites. If the influence coefficient of space debris on the signal transmission of low-earth orbit satellites is less than the influence threshold of space debris on the signal transmission of low-earth orbit satellites, the low-earth orbit satellite will not be adjusted. If the influence coefficient of space debris on the signal transmission of low-earth orbit satellites is greater than or equal to the influence threshold of space debris on the signal transmission of low-earth orbit satellites, the central processing unit will issue an alarm and issue an instruction to adjust the attitude of the low-earth orbit satellite.

[0041] In this embodiment, first, the system needs to extract the influence threshold of space debris on the signal transmission of low-earth orbit satellites from a specially constructed database. This threshold is preset based on the design safety standards and operation requirements of the satellite to evaluate the potential threat level of space debris to the safe operation of the satellite. Then, the system compares and analyzes the influence coefficient of space debris on the signal transmission of low-earth orbit satellites obtained by real-time monitoring and calculation with the influence threshold extracted from the database. During the comparison process, if the calculated influence coefficient is lower than the influence threshold, it indicates that the threat of space debris to the low-earth orbit satellite is within an acceptable range. Therefore, the satellite control system will not take any adjustment measures, and the satellite will continue to operate in the established orbit and attitude. However, if the influence coefficient is greater than or equal to the influence threshold, it indicates that the threat of space debris to the low-earth orbit satellite has reached a level that requires action. In this case, the central processing unit will immediately trigger the alarm system, send an alarm to the ground control center, and at the same time automatically generate and issue an instruction to the control system of the low-earth orbit satellite, instructing the satellite to make necessary attitude adjustments to avoid the area where the space debris blocks the signal.

[0042] Furthermore, the specific process of issuing an alarm and adjusting the attitude of the low-earth orbit satellite according to the comparison result is as follows: The central processing unit issues an alarm to the ground station and shuts down the internal sensitive equipment. The ground station receives the alarm, verifies and confirms it, formulates an avoidance strategy based on the current state and fuel reserve of the low-earth orbit satellite, generates an attitude adjustment instruction according to the avoidance strategy, and sends the attitude adjustment instruction to the operation module of the low-earth orbit satellite.

[0043] In this embodiment, when the central processing unit (CPU) monitors that the influence coefficient of space debris on the signal transmission of a low-earth orbit satellite reaches or exceeds a preset influence threshold, it immediately activates the alarm system. The CPU sends an alarm signal to the ground station and shuts down the sensitive devices on the satellite through the internal instruction system to prevent damage to these devices 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 information such as its orbital position, attitude, speed, fuel reserve, etc. The automation system formulates a strategy to avoid space debris based on the current state of the satellite and its fuel reserve. The avoidance strategy includes operations such as orbit change, speed adjustment, and attitude adjustment to avoid the collision path of space debris. According to the formulated avoidance strategy, the ground station generates specific attitude adjustment instructions. The ground station sends the attitude adjustment instructions to the operation module of the low-earth orbit satellite through the uplink. After receiving the attitude adjustment instructions sent by the ground station, the operation module of the low-earth orbit satellite performs corresponding operations to adjust the attitude. While the satellite performs attitude adjustment, it also needs to perform orbital maneuvers to completely avoid the threat of space debris.

[0044] The specific steps for the automation system to formulate a strategy to avoid space debris based on the current state of the satellite and its fuel reserve are as follows: 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 angles), monitor the fuel reserve situation of the satellite, including the type of propellant and the remaining amount, use a collision prediction algorithm (such as Conjunction Analysis for Satellite Traffic CONSAT) to evaluate the collision risk between the satellite and space debris, determine the time, distance, and collision probability of the debris approaching the satellite, evaluate the degree of damage caused by the debris to the satellite, and determine whether avoidance measures need to be taken based on the threat assessment results. If avoidance is required, the system will generate a series of avoidance strategies, including: Orbit maneuver: Change the orbit altitude or orbital inclination. Attitude adjustment: Change the pointing of the satellite to avoid the signal interference area of space debris. Speed change: Accelerate or decelerate to change the orbital position of the satellite to avoid the signal interference area of space debris. Use matlab to simulate the selected avoidance strategy to verify its effectiveness and safety, and generate specific operation instructions according to the finally determined avoidance strategy. The instructions should include the execution time, operation steps, and expected results.

[0045] Further, the specific process for analyzing the data related to the inter-satellite link network load balancing is as follows: The data related to the inter-satellite link network load balancing includes the single-satellite bandwidth utilization rate, the traffic peak ratio, and the congestion trigger threshold; obtain the weight factors of the single-satellite bandwidth utilization rate, the weight factors of the traffic peak ratio, and the weight factors of the congestion trigger threshold from the database, arrange the single-satellite bandwidth utilization rate, the traffic peak ratio, and the congestion trigger threshold in a spatial sequence, use the corresponding weight factors to correct the single-satellite bandwidth utilization rate, the traffic peak ratio, and the congestion trigger threshold at each spatial sequence point, and couple and average the results of each correction process to obtain the inter-satellite link network load balancing evaluation coefficient.

[0046] In this embodiment, the specific method for obtaining the inter-satellite link network load balancing evaluation coefficient is as follows:

[0047] ;

[0048] ;

[0049] In the formula, represents the inter-satellite link network load balancing evaluation coefficient, which is used to evaluate the impact of the inter-satellite link network load balancing on the inter-satellite link. Set several data monitoring points, , represents the total number of data monitoring points, represents the single-satellite bandwidth utilization rate at the th data monitoring point, represents the weight factor of the single-satellite bandwidth utilization rate, represents the traffic peak ratio at the th data monitoring point, represents the weight factor of the traffic peak ratio, represents the congestion trigger threshold at the th data monitoring point, represents the weight factor of the congestion trigger threshold.

[0050] When the system is running, obtain the mapping table of the weight factors through the database. For example, quickly extract the corresponding weight factors according to the current single-satellite bandwidth utilization rate, traffic peak ratio, and congestion trigger threshold, such as the weight factors of the single-satellite bandwidth utilization rate, the weight factors of the traffic peak ratio, and the weight factors of the congestion trigger threshold. This mapping table defines a clear set of association rules, which converts the specific values of the single-satellite bandwidth utilization rate, the traffic peak ratio, and the congestion trigger threshold into their corresponding weight factors. Under this mechanism, whether it is to achieve an exact one-to-one match or a one-to-many relationship where multiple parameters converge into a single weight, the dynamic acquisition of the weight factors can be effectively achieved.

[0051] The single-satellite bandwidth utilization rate refers to the ratio of the bandwidth actually used by a single satellite within a certain period of time to its total available bandwidth. It is calculated by monitoring the data transmission volume of the satellite within a specific time period and comparing it with the total bandwidth capacity of the satellite. The formula is: (Actual data transmission volume / Total bandwidth capacity) * 100%.

[0052] The peak traffic ratio refers to the ratio of the maximum value to the average value of the data transmission traffic within a certain period of time. By monitoring the data traffic within a period of time, calculating the maximum and average values of the traffic, and then obtaining the ratio of the two. The formula is: (Peak traffic / Average traffic) * 100%.

[0053] The congestion trigger threshold refers to the maximum bandwidth utilization rate that the satellite communication system can tolerate. The congestion trigger threshold is dynamically changing. If there are multiple low-Earth orbit satellites around, the congestion trigger threshold is reduced according to a predefined ratio. If there is only one low-Earth orbit satellite around, the congestion trigger threshold is increased according to a predefined ratio.

[0054] If the single-satellite bandwidth utilization rate approaches or reaches the congestion trigger threshold, it indicates that the bandwidth resources of the satellite are about to be exhausted and the system faces congestion risks. A high peak traffic ratio means large traffic fluctuations, which will cause the single-satellite bandwidth utilization rate to exceed the congestion trigger threshold at the peak. The congestion trigger threshold is the criterion for judging whether to take traffic management measures, while the single-satellite bandwidth utilization rate and the peak traffic ratio are the indicators for monitoring the system performance. When the product of the single-satellite bandwidth utilization rate and the peak traffic ratio exceeds the congestion trigger threshold, the system will take measures such as traffic control and bandwidth allocation adjustment to prevent or alleviate congestion.

[0055] Furthermore, the specific process of comparing the inter-satellite link network load balancing evaluation coefficient with the threshold is as follows: Obtain the inter-satellite link network load balancing evaluation threshold from the database, compare the inter-satellite link network load balancing evaluation coefficient with the inter-satellite link network load balancing evaluation threshold. If the inter-satellite link network load balancing evaluation coefficient is less than the inter-satellite link network load balancing evaluation threshold, there are random link failures in the low-Earth orbit satellite and inter-satellite link optimization is performed on the low-Earth orbit satellite. If the inter-satellite link network load balancing evaluation coefficient is greater than or equal to the inter-satellite link network load balancing evaluation threshold, no adjustment is made to the low-Earth orbit satellite.

[0056] In this embodiment, first, the system needs to extract the threshold for the inter-satellite link network load balancing evaluation from a specially constructed database. This threshold is preset according to factors such as the performance requirements, reliability standards, and historical operation data of the inter-satellite link, and it serves as an important basis for judging whether the inter-satellite link network load balancing is in a normal working state. Next, the system will calculate in real time or obtain from the monitoring system the evaluation coefficient of the inter-satellite link network load balancing. This coefficient is comprehensively derived based on the actual working conditions of the inter-satellite link, such as the single-satellite bandwidth utilization rate, traffic peak ratio, and congestion trigger threshold, and it reflects the current performance level of the inter-satellite link. Then, the system will conduct a comparative analysis of the evaluation coefficient of the inter-satellite link network load balancing calculated in real time with the evaluation threshold extracted from the database. If it is found that the evaluation coefficient of the inter-satellite link network load balancing is less than the evaluation threshold, it indicates that there is a random link failure in the low-earth orbit satellite. At this time, the system will start the inter-satellite link optimization program, which includes various measures such as adjusting link parameters, reallocating link resources, enabling backup links, or establishing new link connections, to improve the link performance and ensure the continuity and reliability of communication. On the contrary, if the evaluation coefficient of the inter-satellite link network load balancing is greater than or equal to the evaluation threshold, it means that the inter-satellite link network load balancing is in a good state, and the system will not take any adjustment measures, and the low-earth 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 inter-satellite link network load balancing through real-time monitoring and intelligent evaluation, thereby guaranteeing the stability and efficiency of the low-earth orbit satellite network.

[0057] Furthermore, the specific process for evaluating whether there is a random link failure based on the comparison result and optimizing the inter-satellite link of the low-earth orbit satellite is as follows: conduct a threshold comparison of the evaluation coefficient of the inter-satellite link network load balancing, and optimize the inter-satellite link according to the threshold comparison result of the evaluation coefficient of the inter-satellite link network load balancing, including dynamically allocating bandwidth and designing a dynamic protocol adaptation mechanism, and verifying the compatibility under different topologies through simulation.

[0058] In this embodiment, the system first extracts the threshold for the inter-satellite link network load balancing evaluation from the database. This threshold is obtained based on link performance metrics, system reliability requirements, and historical data analysis, and is used to determine whether the operating state of the inter-satellite link meets the established standards. Then, the system monitors and calculates the inter-satellite link network load balancing evaluation coefficient in real time to quantify the current performance of the link. Next, the system compares the calculated inter-satellite link network load balancing evaluation coefficient with the preset threshold. If the evaluation coefficient is lower than the threshold, it indicates that there are bottlenecks or potential failures 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 demand and priority of the link to maximize the bandwidth utilization rate 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. To ensure the effectiveness of the optimization measures, the system will also verify the compatibility under different network topologies through simulation, that is, testing the performance of the dynamic bandwidth allocation and protocol adaptation mechanism under various topological structures in a simulated inter-satellite link environment to ensure that the optimization measures can adapt to different network configurations and operating conditions in actual operations. The implementation of the entire technical solution aims to improve the overall performance and reliability of the inter-satellite link through intelligent resource management and dynamic optimization strategies, and ensure the smooth operation of the satellite network.

[0059] The specific steps for dynamically allocating bandwidth are as follows: Real-time monitor the traffic data of the inter-satellite link, establish a bandwidth resource pool to centrally manage all available bandwidth resources, select the shortest path first bandwidth allocation algorithm, and dynamically adjust the link bandwidth through control instructions according to the algorithm results. If the inter-satellite link network load balancing evaluation coefficient is still less than the inter-satellite link network load balancing evaluation threshold after dynamically allocating bandwidth, then design the dynamic protocol adaptation mechanism.

[0060] The specific steps for designing the dynamic protocol adaptation mechanism are as follows: Construct a library containing multiple communication protocols, such as TCP, UDP, SDRP, CCSDS, analyze the characteristics of the current inter-satellite link, such as latency, packet loss rate, 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 parameters of the selected protocol in real time, and optimize the protocol configuration according to the link performance feedback to improve the communication efficiency. If the inter-satellite link network load balancing evaluation coefficient is still less than the inter-satellite link network load balancing evaluation threshold after designing the dynamic protocol adaptation mechanism, then verify the compatibility under different topologies through simulation.

[0061] The specific steps for simulating and verifying the compatibility under different topologies are as follows: Use Matlab to establish a simulation model of the inter-satellite link, simulate different network topologies, including satellite swarms, constellations, link redundancy, etc., monitor key performance indicators during the simulation process, such as throughput, latency, 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 inter-satellite link network load balancing evaluation coefficient is still less than the inter-satellite link network load balancing evaluation threshold after simulating and verifying the compatibility under different topologies, an alarm is issued.

[0062] Furthermore, the specific process for 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 spectral flatness of the IQ signal, and the delay jitter of the IQ signal; Obtain the weight factors of the signal-to-noise ratio of the IQ signal, the weight factors of the bit error rate of the IQ signal, the weight factors of the spectral flatness of the IQ signal, and the weight factors of the delay jitter of the IQ signal from the database, arrange the signal-to-noise ratio of the IQ signal, the bit error rate of the IQ signal, the spectral flatness of the IQ signal, and the delay jitter of the IQ signal in the phase sequence, and use the corresponding weight factors to correct 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 spectral flatness of the IQ signal, and the delay jitter of the IQ signal at each phase sequence point, and couple and average the results of each correction process to obtain the difference evaluation coefficient between the real-time value and the standard value of the IQ signal.

[0063] 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 as follows:

[0064] ;

[0065] ;

[0066] In the formula, represents 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 affected by space debris, represents the number of the phase monitoring point, c, represents the total number of phase monitoring points, represents the th signal-to-noise ratio of the IQ signal at the phase monitoring point, represents the signal-to-noise ratio of the standard IQ signal, represents the weight factor of the signal-to-noise ratio of the IQ signal, represents the th bit error rate of the IQ signal at the phase monitoring point, represents the weight factor of the bit error rate of the IQ signal, Indicates the bit error rate of the standard IQ signal, Indicates the spectrum flatness of the IQ signal under the weight factor of the spectrum flatness of the IQ signal, Indicates the spectrum flatness of the standard IQ signal, Indicates the delay jitter of the IQ signal under the weight factor of the delay jitter of the IQ signal, Indicates the delay jitter of the standard IQ signal.

[0067] When the system is running, obtain the mapping table of weight factors through the database, and quickly extract the corresponding weight factors according to the signal-to-noise ratio, bit error rate, spectrum flatness, and delay jitter of the current 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, bit error rate, spectrum flatness, and delay jitter of the IQ signal into their corresponding weight factors. Under this mechanism, whether it is to achieve an exact one-to-one 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.

[0068] The signal-to-noise ratio can be obtained by measuring the signal power and noise power and then calculating their ratio.

[0069] The bit error rate can be obtained by simulating or transmitting a known bit sequence in an actual communication system and then detecting the number of bit errors at the receiving end.

[0070] The spectrum flatness refers to the consistency of the signal amplitude within the entire frequency band. Use a spectrum analyzer to scan the entire frequency band of the signal and measure the amplitudes at different frequency points.

[0071] The delay jitter refers to the degree of change in the delay during the signal transmission process. Use a time measurement device (such as a time interval analyzer) to measure the fluctuation of the signal arrival time. For example, if a signal arrives once every 50 milliseconds, but is delayed or advanced, it can be called delay jitter.

[0072] 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 usually. Poor spectrum flatness causes the power of the signal to decrease in some frequency bands, thus affecting the signal-to-noise ratio. Delay jitter causes the signal to be out of sync at the receiving end, affecting signal synchronization and correct decoding, thus increasing the bit error rate. Delay jitter is caused by system non-linearity, which also affects the spectrum flatness.

[0073] The higher the signal-to-noise ratio, the better the quality of the IQ signal usually is, and the smaller the difference evaluation coefficient between the real-time value and the standard value. The higher the bit error rate, the larger the difference evaluation coefficient between the real-time value and the standard value. Poor spectral flatness will cause the amplitudes 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 cause inaccurate signal timing and also increase the difference evaluation coefficient between the real-time value and the standard value.

[0074] Furthermore, the specific process of comparing the difference evaluation coefficient between the real-time value and the standard value of the IQ signal with a threshold is as follows: Obtain the difference evaluation thresholds between different components of the IQ signal from the database, compare the difference evaluation coefficient between the real-time value and the standard value of the IQ signal with the difference evaluation thresholds 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, optimize the IQ signal of the low-earth 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, issue an instruction to repair the link of the low-earth orbit satellite.

[0075] In this embodiment, first, the system extracts the difference evaluation thresholds 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. Then, 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-earth orbit satellite in real time. This coefficient is a comprehensive index that includes parameters such as signal-to-noise ratio, bit error rate, spectral 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 an optimization program, including measures such as adjusting the transmission power, changing the modulation and demodulation method, optimizing the filter settings, or reconfiguring the signal, 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 are link failures or potential problems, the system will issue an instruction to repair the link of the low-earth orbit satellite, which involves operations such as link reconfiguration, fault detection, location, and repair. The implementation of the entire technical solution aims to ensure that the IQ signal of the low-earth orbit satellite is always in the best working state and guarantee the stability and reliability of satellite communication.

[0076] Adjust the transmission power: First, monitor the output level of the current transmission power of the LEO satellite. Evaluate the coefficient based on the difference between the real-time value and the standard value of the IQ signal and the communication link status. If the real-time value of the IQ signal is less than the standard value, increase the transmission power; if the real-time value of the IQ signal is greater than or equal to the standard value, decrease the transmission power. Adjust the transmission power through the power amplifier (PA) on the satellite. If power increase is needed, increase the gain of the PA; if power reduction is needed, decrease the gain. After adjustment, monitor the change in transmission power through the ground station or other satellites, and evaluate whether the IQ signal quality has improved. If the evaluation coefficient of the difference between the real-time value and the standard value of the IQ signal is still greater than the evaluation threshold of the difference between the real-time value and the standard value of the IQ signal, then change the modulation and demodulation method.

[0077] Change the modulation and demodulation method: Evaluate whether the currently used modulation method (such as BPSK, QPSK, 16-QAM, etc.) is suitable for the current communication environment. Select a more suitable modulation method according to the channel conditions and communication requirements. For example, if the signal-to-noise ratio is lower than the predetermined threshold of 20 dB, it is necessary to switch to a more robust modulation method. Update the configuration on the satellite's modem, including the modulation method and corresponding demodulation parameters. After changing the modulation method, conduct a link test to ensure that the signal can be correctly transmitted and received. If the evaluation coefficient of the difference between the real-time value and the standard value of the IQ signal is still greater than the evaluation threshold of the difference between the real-time value and the standard value of the IQ signal, then optimize the filter settings.

[0078] Optimize the filter settings: Check the bandwidth, cut-off frequency, and filtering effect of the current filter. Adjust the filter parameters such as bandwidth, cut-off frequency, and roll-off coefficient according to the quality of the IQ signal to reduce interference and signal distortion. If necessary, design a new filter to meet specific communication requirements. Verify the performance of the filter through signal analysis tools to ensure that the signal quality is improved. If the evaluation coefficient of the difference between the real-time value and the standard value of the IQ signal is still greater than the evaluation threshold of the difference between the real-time value and the standard value of the IQ signal, then use the reconfigured signal processing algorithm and reconfigure the reverse signal.

[0079] Reconfigure the signal processing algorithm: Analyze the performance of the current signal processing algorithm, including bit error rate, signal synchronization, and channel coding efficiency, etc. Select a more suitable signal processing algorithm or design a new algorithm according to the communication requirements and environmental changes. Update the algorithm configuration on the satellite's signal processing unit, including encoding, decoding, synchronization, and equalization, etc. Verify the performance of the new algorithm through simulation and actual communication tests to ensure that the signal quality meets the communication standards. If the evaluation coefficient of the difference between the real-time value and the standard value of the IQ signal is still greater than the evaluation threshold of the difference between the real-time value and the standard value of the IQ signal, then send an alarm to the satellite ground station.

[0080] Furthermore, the specific process of issuing an instruction to repair the link of the LEO 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 an instruction to the LEO 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 a communication test.

[0081] In this embodiment, the IQ signal data of the LEO satellite is monitored and collected in real time, including key parameters such as signal-to-noise ratio, bit error rate, spectral flatness, and delay jitter. The difference evaluation coefficient between the real-time value and the standard value of the IQ signal is calculated, and the difference evaluation coefficient between the real-time value and the standard value of the IQ signal is compared with a preset threshold to determine whether there is a performance degradation or a 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, a targeted link repair strategy is formulated, the link repair strategy is converted into a specific instruction sequence, and the instruction is sent to the LEO satellite through the uplink of the ground control station. After executing the link repair instruction, the IQ signal data is collected again, the new difference evaluation coefficient between the real-time value and the standard value of the IQ signal is calculated, the effect of the link repair operation is evaluated, the difference evaluation coefficients between the real-time value and the standard value of the IQ signal before and after the repair are compared, the improvement of the link performance is verified, a series of communication tests are performed, such as signal transmission test, bit error rate test, link stability test, the test results are analyzed, and it is determined whether the link has returned to the 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.

[0082] Signal transmission test: Generate a known signal (such as a sine wave, square wave, or specific modulation signal) as the test signal, send the test signal through the communication link. 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 transmitted signal to check for distortion, attenuation, or other changes.

[0083] Bit error rate test: The transmitting end generates a known bit sequence, which can be a pseudo-random sequence or other standard test sequences. Send the test sequence through the communication link. Receive the data at the receiving end and store it. Compare the received data with the original transmitted data sequence, calculate the bit error rate, and repeat the test under different conditions (such as different signal strengths, noise levels, etc.) to evaluate the change of the bit error rate with conditions.

[0084] Link stability test: Continuously transmit specially designed test data on the link, continuously monitor multiple parameters of the link in real time, such as signal strength, bit error rate, delay, jitter, etc., record the change of the link performance over time, and analyze the fluctuation of the link performance.

[0085] The link repair strategy includes controlling the satellite antenna pointing through software instructions and quickly switching to the backup link. Quickly switching to the backup link means constructing the shortest non-intersecting paths of multiple links as alternatives and dynamically switching the optimal path in combination with the priority mechanism (delay and packet loss rate). If the delay is higher than the preset value, switch to the route with a delay lower than the preset value. If the packet loss rate is higher than the preset value, switch to the route with a packet loss rate lower than the preset value to improve the fault tolerance ability.

[0086] Those skilled in the art should understand that the embodiments of the present invention can be provided as a method, a system, or a computer program product. Therefore, the present invention can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Moreover, the present invention can 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.

[0087] The present invention is described with reference to the flowcharts and / or block diagrams of methods, apparatuses (systems), and computer program products according to the embodiments of the present invention. It should be understood that each process and / or block in the flowchart and / or block diagram, and the combination of processes and / or blocks in the flowchart and / or block diagram, can be realized by computer program instructions. These computer program instructions can be provided to the processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing devices to generate a machine, so that the instructions executed by the processor of the computer or other programmable data processing devices generate means for realizing the functions specified in one process Figure 1 one process or multiple processes and / or blocks Figure 1 one block or multiple blocks.

[0088] These computer program instructions can also be stored in a computer-readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer-readable memory generate a manufactured article including instruction means, and the instruction means realizes the functions specified in one process Figure 1 one process or multiple processes and / or blocks Figure 1 one block or multiple blocks.

[0089] These computer program instructions can also be loaded onto a computer or other programmable data processing device, so that a series of operation steps are executed on the computer or other programmable device to generate a computer-implemented process. Thus, the instructions executed on the computer or other programmable device provide steps for realizing the functions specified in one process Figure 1 one process or multiple processes and / or blocks Figure 1 one block or multiple blocks.

[0090] Although the preferred embodiments of the present invention have been described, additional changes and modifications can be made to these embodiments by those skilled in the art once they learn the basic creative concept. Therefore, the appended claims are intended to be construed to include the preferred embodiments as well as all changes and modifications that fall within the scope of the present invention.

[0091] Obviously, those skilled in the art can make various changes and deformations to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and deformations of the present invention fall within the scope of the claims of the present invention and their equivalent technologies, the present invention is also intended to include these modifications and deformations.

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 thresholds 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 based on the comparison results. 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 changes in received signal power attenuation; 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 are random link failures based on the comparison results and optimize the intersatellite links of low-orbit satellites. The intersatellite link network load balancing related data include single-satellite bandwidth utilization, traffic peak ratio and congestion trigger threshold; 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 result. The 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.

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 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 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: 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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