A satellite damage reconstruction phase adjustment method, device, equipment and medium

Abstract

This invention provides a phase adjustment method, apparatus, device, and medium for satellite damage reconstruction, relating to the field of satellite technology. The method includes: initializing a preset simulation platform based on the basic information of the on-orbit constellation, and mapping the operational status data of the on-orbit constellation to the preset simulation platform; when an on-orbit satellite is detected to meet preset damage conditions, marking the corresponding on-orbit satellite as a damaged satellite and setting the corresponding satellite model as a damaged satellite model; obtaining the simulation phase set of each satellite model after removing the damaged satellite model, and determining a target adjustment phase set based on the simulation phase of any satellite model in the simulation phase set; sequentially adjusting the phase of at least some of the satellite models until the constellation model meets the preset operational conditions, and controlling the on-orbit satellites according to the current phase interval. This invention achieves efficient local optimization and feasibility closed-loop verification of phase reconstruction after satellite damage, comprehensively ensuring the reliability of on-orbit constellation operation.

Description

Technical Field

[0001] This invention relates to the field of satellite technology, and more specifically, to a phase adjustment method, apparatus, equipment, and medium for satellite damage reconstruction. Background Technology

[0002] With the rapid development of aerospace technology, satellites are being used more and more widely in various fields. As a key part of space systems, satellite constellations rely on the coordinated operation of multiple satellites to achieve important functions such as communication, navigation, weather monitoring, and Earth observation.

[0003] Satellites operating in the complex space environment are susceptible to damage from high-energy particle radiation and micrometeoroid impacts, affecting the overall functionality of the constellation. However, current phase adjustment methods for satellite damage reconstruction have significant limitations, making it difficult to ensure the reliability of satellite constellation operation. Summary of the Invention

[0004] The problem addressed by this invention is how to improve the reliability of satellite constellation operation.

[0005] To address the above problems, this invention provides a phase adjustment method for satellite damage reconstruction, comprising: The preset simulation platform is initialized based on the acquired basic information of the on-orbit constellation, and the acquired operational status data of the on-orbit constellation is mapped to the preset simulation platform according to the preset simulation step size; wherein, the basic information includes the mission cycle, and the preset simulation platform is used to perform operational simulation on the constellation model corresponding to the on-orbit constellation; When the telemetry data of the acquired on-orbit constellation is used to detect that an on-orbit satellite in the on-orbit constellation meets the preset damage conditions, the corresponding on-orbit satellite is marked as a damaged satellite, and the satellite model corresponding to the damaged satellite in the constellation model is set as a damaged satellite model using the preset simulation platform. The simulation phase set corresponding to each satellite model after removing the damaged satellite model is obtained using the preset simulation platform, and the target adjustment phase set corresponding to each satellite model is determined based on the simulation phase of any satellite model in the simulation phase set; Based on the target adjustment phase set, the phase of at least some of the satellite models is adjusted sequentially through the preset simulation platform until the constellation model meets the preset operating conditions. Then, the on-orbit satellite is controlled according to the current phase interval between each of the satellite models.

[0006] Optionally, the telemetry data includes multiple preset monitoring parameters; the step of marking the corresponding on-orbit satellite as a damaged satellite when the on-orbit satellite in the on-orbit constellation is detected based on the acquired telemetry data of the on-orbit constellation and meets preset damage conditions includes: When the preset monitoring parameter exceeds the corresponding preset threshold range, the preset monitoring parameter is used as a suspected fault parameter, and the first trend feature corresponding to the suspected fault parameter is determined. When the first trend feature meets the preset abnormal conditions corresponding to the suspected fault parameters, the fault type of the damaged satellite is determined based on the suspected fault parameters; A fault score is determined based on the suspected fault parameters, the first trend feature, and the fault type. When the fault score is greater than a preset score threshold, the on-orbit satellite corresponding to the suspected fault parameters is recorded as the damaged satellite.

[0007] Optionally, determining the fault type of the damaged satellite based on the suspected fault parameters includes: Obtain each coupling parameter pre-associated with the suspected fault parameter, and determine the second trend feature corresponding to each coupling parameter respectively; When the second trend feature and the first trend feature meet the fault conditions corresponding to the preset satellite function, the fault type is determined based on the preset satellite function.

[0008] Optionally, determining the target adjustment phase set corresponding to all satellite models based on the simulated phase of any of the satellite models in the simulated phase set includes: Based on the simulated phase set, the phase corresponding to the gap region between two satellite models adjacent to the damaged satellite model is determined, and the gap phase is obtained; Using the simulated phase of any of the satellite models as a reference, the ideal simulated phase of each satellite model is determined according to the ideal phase interval, thus obtaining the ideal simulated phase set; wherein, the ideal phase interval is determined according to the number of satellite models; The ideal simulation phases corresponding to two satellite models adjacent to the damaged satellite model in the ideal simulation phase set are corrected using a phase correction amount; wherein, the phase correction amount is determined based on the gap phase; the phase interval between the two corrected ideal simulation phases is smaller than the phase interval between the two uncorrected ideal simulation phases; The target adjustment phase set is obtained based on the corrected ideal simulation phase set.

[0009] Optionally, the step of adjusting the phase set based on the target sequentially through the preset simulation platform to adjust the phase of at least some of the satellite models until the constellation model meets the preset operating conditions, and then controlling the on-orbit satellites according to the determined current phase interval between each of the satellite models, includes: The adjustment step includes setting at least two satellite models closest to the gap region as to be adjusted, and generating an adjustment command based on the target adjustment phase corresponding to the satellite models in the to-be-adjusted state in the target adjustment phase set; The adjustment command is sent to the preset simulation platform so that the preset simulation platform can perform a simulation of the constellation model after responding to the adjustment command. When the constellation model meets the preset operating conditions, the on-orbit satellite is controlled according to the current phase interval; If the constellation model does not meet the preset operating conditions, return to the adjustment steps until the preset termination conditions are met.

[0010] Optionally, before sequentially adjusting the phase of at least a portion of the satellite model based on the target adjustment phase set through the preset simulation platform, the method further includes: Obtain the target coverage area corresponding to the damaged satellite, and use the preset simulation platform to determine the historical coverage performance index of the constellation model for the target coverage area before the damaged satellite was marked.

[0011] Optionally, after sending the adjustment command to the preset simulation platform to cause the preset simulation platform to perform a simulation of the constellation model controlled by the adjustment command, the method further includes: Determine the current coverage performance index of the constellation model for the target coverage area; Obtain the current simulation phase corresponding to each of the satellite models, determine the current phase interval between each of the satellite models based on the current simulation phase, and determine the phase difference between each current phase interval and the ideal phase interval respectively; When all the phase differences are within a preset range, and the ratio of the current coverage performance index to the historical coverage performance index is greater than a preset threshold, the constellation model is indicated to meet the preset operating conditions.

[0012] In this invention, the pre-set simulation platform is initialized based on fundamental information about the on-orbit constellation, such as mission cycles, and operational status data is mapped at preset step sizes. This ensures that the constellation model is synchronized with the actual on-orbit constellation state, providing a reliable digital twin environment for subsequent phase adjustment simulations and reliability verification of the target adjustment phase set. Based on this, acquiring telemetry data from the on-orbit constellation allows for accurate understanding of its actual operation, enabling timely identification of damaged on-orbit satellites. When telemetry data detects that an on-orbit satellite meets preset damage conditions, the corresponding satellite is marked as damaged, and its corresponding satellite model is simultaneously set as the damaged satellite model in the pre-set simulation platform. This facilitates state synchronization between physical and simulation spaces, ensuring the accuracy and timeliness of the constellation model. After identifying a damaged on-orbit satellite, the pre-set simulation platform is used to obtain the simulation phase set corresponding to all satellite models, reflecting the current actual position distribution of the on-orbit satellites. Based on this, using the simulated phase of any satellite model in the simulated phase set as a benchmark, a target adjustment phase set corresponding to all satellite models is determined. Based on this target adjustment phase set, the phases of at least some satellite models are sequentially adjusted through a preset simulation platform. This facilitates gradual, local optimization of the satellite model phases within a simulated environment. After each adjustment, it is determined whether the constellation model meets the preset operating conditions to verify the feasibility of the phase adjustment. When the constellation model meets the preset operating conditions, it indicates that the constellation model can meet the requirements after the current phase adjustment. At this point, the on-orbit satellites are controlled according to the determined current phase interval between each satellite model. This ensures the reliability of on-orbit satellite phase adjustment while minimizing the number of on-orbit satellites requiring phase adjustment, thus saving energy consumption.

[0013] The present invention also provides a phase adjustment device for satellite damage reconstruction, comprising: The mapping module is used to initialize the preset simulation platform based on the acquired basic information of the on-orbit constellation, and to map the acquired operational status data of the on-orbit constellation to the preset simulation platform according to the preset simulation step size; wherein, the basic information includes the mission cycle, and the preset simulation platform is used to perform operational simulation on the constellation model corresponding to the on-orbit constellation; The detection module is used to mark the corresponding on-orbit satellite as a damaged satellite when the on-orbit satellite in the on-orbit constellation is detected to meet the preset damage conditions based on the acquired telemetry data of the on-orbit constellation, and to use the preset simulation platform to set the satellite model corresponding to the damaged satellite in the constellation model as the damaged satellite model. The determination module is used to obtain the simulation phase set corresponding to each of the satellite models after removing the damaged satellite models using the preset simulation platform, and to determine the target adjustment phase set corresponding to each of the satellite models based on the simulation phase of any of the satellite models in the simulation phase set; The control module is used to adjust the phase of at least some of the satellite models sequentially through the preset simulation platform based on the target adjustment phase set until the constellation model meets the preset operating conditions, and then control the on-orbit satellites according to the determined current phase interval between each of the satellite models.

[0014] The phase adjustment device for satellite damage reconstruction provided by this invention has essentially the same advantages as the phase adjustment method for satellite damage reconstruction compared to the prior art, and will not be repeated here.

[0015] The present invention also provides an electronic device, including a memory and a processor; The memory is used to store computer programs; The processor is used to implement the phase adjustment method for satellite damage reconstruction as described above when executing the computer program.

[0016] The electronic device provided by this invention and the phase adjustment method for satellite damage reconstruction have essentially the same advantages as the prior art, and will not be elaborated further here.

[0017] The present invention also provides a computer-readable storage medium storing a computer program, which, when executed by a processor, implements the phase adjustment method for satellite damage reconstruction as described above.

[0018] The advantages of the computer-readable storage medium provided by this invention and the phase adjustment method for satellite damage reconstruction are basically the same as those of the prior art, and will not be repeated here. Attached Figure Description

[0019] Figure 1 This is a schematic flowchart of the phase adjustment method for satellite damage reconstruction according to an embodiment of the present invention; Figure 2 This is a schematic diagram of the phase adjustment device for satellite damage reconstruction according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the structure of an electronic device according to an embodiment of the present invention. Detailed Implementation

[0020] To make the above-mentioned objects, features, and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. Although some embodiments of the present invention are shown in the drawings, it should be understood that the present invention can be implemented in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the present invention. It should be understood that the accompanying drawings and embodiments of the present invention are for illustrative purposes only and are not intended to limit the scope of protection of the present invention.

[0021] It should be understood that the various steps described in the method embodiments of the present invention may be performed in different orders and / or in parallel. Furthermore, the method embodiments may include additional steps and / or omit the steps shown. The scope of the present invention is not limited in this respect.

[0022] The term "comprising" and its variations as used herein are open-ended, meaning "including but not limited to". The term "based on" means "at least partially based on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments"; the term "optionally" means "optional embodiments". Definitions of other terms will be given in the following description. It should be noted that the concepts of "first", "second", etc., mentioned in this invention are used only to distinguish different devices, modules, or units, and are not intended to limit the order of functions performed by these devices, modules, or units or their interdependencies.

[0023] It should be noted that the terms "a" and "a plurality of" used in this invention are illustrative rather than restrictive. Those skilled in the art should understand that, unless otherwise expressly indicated in the context, they should be understood as "one or more".

[0024] The existing phase adjustment response speed after satellite failure is slow, making it impossible to quickly initiate the phase adjustment process the instant the satellite is damaged. Furthermore, high latency in front-end and back-end data interaction prevents timely filling of mission gaps caused by failed satellites, impacting the overall service continuity of the constellation. Simultaneously, existing back-end (such as control platform) orbit adjustment methods after satellite damage typically rely on complex calculations, resulting in insufficient adjustment accuracy and response delays. These methods cannot meet the requirements for efficient and reliable phase adjustment after satellite reconstruction, thus compromising the reliability of satellite operation.

[0025] To address the problems existing in the aforementioned related technologies, embodiments of the present invention provide a phase adjustment method, apparatus, device, and medium for satellite damage reconstruction.

[0026] like Figure 1 As shown in the figure, an embodiment of the present invention provides a phase adjustment method for satellite damage reconstruction, which includes the following steps: S1: Initialize the preset simulation platform based on the acquired basic information of the on-orbit constellation, and map the acquired operational status data of the on-orbit constellation to the preset simulation platform according to the preset simulation step size; wherein, the basic information includes the mission cycle, and the preset simulation platform is used to perform operational simulation on the constellation model corresponding to the on-orbit constellation.

[0027] Specifically, in this embodiment, the on-orbit constellation refers to a complex satellite system constructed collaboratively by multiple on-orbit satellites through inter-satellite links. Each satellite unit works closely together to complete specific space missions such as communication, navigation, remote sensing, or Earth observation. The constellation model in this embodiment refers to a digital model of the on-orbit constellation, which can be pre-established in a preset simulation platform using a reference coordinate system (such as a geocentric inertial coordinate system) to describe the satellites' three-dimensional position distribution, motion state, and other parameters. The basic information in this embodiment may include data such as the mission cycle, orbital parameters, and operational rules of the on-orbit constellation. The mission cycle represents the standard time required to complete one full mission cycle. The preset simulation platform in this embodiment refers to a comprehensive software environment that performs full lifecycle operational simulations on the corresponding constellation model of the on-orbit constellation, simulating the satellite's orbital dynamics evolution, data transmission links, and other dynamic behaviors. The operational status data in this embodiment may include real-time telemetry information such as the position, velocity, attitude angle, and payload operating status of each satellite within the on-orbit constellation, comprehensively reflecting the actual operational status of the satellites in orbit.

[0028] In one embodiment, after acquiring basic information about the on-orbit constellation (such as mission cycle and initial orbital elements) and operational status data (such as the TLE (Two-Line Element Number) and phase distribution data of all on-orbit satellites within the constellation), the basic information can be sent to a preset simulation platform to perform initialization configuration operations. This establishes the spatial reference and time scale for the simulation, laying the foundation for subsequent dynamic simulations. Afterward, the acquired operational status data can be cleaned and converted into a format parseable by the preset simulation platform. Referring to pre-configured communication interface parameters (such as data transmission protocol, interaction frequency, and state synchronization threshold) within the preset simulation platform, the operational status data of the on-orbit constellation is synchronized to the platform in real time according to a preset simulation step size, ensuring that the constellation model can accurately simulate the actual operational status of the on-orbit constellation. Taking a preset simulation step size of 1 minute as an example, every minute of simulation progress, the latest acquired operational status data such as phase, velocity vector, and attitude of the on-orbit satellites can be input to the preset simulation platform, triggering updates to the relevant state parameters of each satellite model. This achieves high-precision and continuous mapping of the operational status data, ensuring the reliability of the simulation results.

[0029] S2: When the telemetry data of the acquired on-orbit constellation detects that an on-orbit satellite in the on-orbit constellation meets the preset damage conditions, the corresponding on-orbit satellite is marked as a damaged satellite, and the satellite model corresponding to the damaged satellite in the constellation model is set as the damaged satellite model using the preset simulation platform.

[0030] Specifically, the telemetry data referred to in this embodiment refers to various monitoring data transmitted back to the ground in real time from the on-orbit satellite, which may include the satellite's operating status, equipment parameters, environmental data, etc., for real-time monitoring of the satellite's operation. The preset damage conditions referred to in this embodiment refer to pre-set criteria for judging whether a satellite is damaged, such as failure of key satellite equipment, attitude control failure, communication link failure, etc. The damaged satellite referred to in this embodiment refers to an on-orbit satellite that meets the preset damage conditions and is determined to be unable to perform its mission normally. The satellite model referred to in this embodiment is a component of the constellation model, representing a virtual object in the preset simulation platform used to digitally model the on-orbit satellite, simulating the operation of the corresponding on-orbit satellite. Its operating state can be switched to a damaged state through the preset simulation platform, thus setting it as a damaged satellite model.

[0031] In one embodiment, real-time analysis of the acquired telemetry data of the on-orbit constellation can be performed, such as comparing various indicators in the telemetry data with preset damage conditions. When the telemetry data of an on-orbit satellite meets the preset damage conditions (e.g., parameters exceeding a preset threshold range), the on-orbit satellite can be marked as a damaged satellite. Simultaneously, in a preset simulation platform, the satellite model corresponding to the damaged satellite is set as the damaged satellite model. For example, if a fault signal is detected in the telemetry data of a satellite's attitude control system, and it exceeds a preset repairable range, the satellite can be determined to meet the damage conditions, marked as a damaged satellite, and the corresponding satellite model can be set as the damaged satellite model in the simulation platform.

[0032] S3: Use a preset simulation platform to obtain the simulation phase set corresponding to each satellite model after removing the damaged satellite model, and use the simulation phase of any satellite model in the simulation phase set as a reference to determine the target adjustment phase set corresponding to each satellite model.

[0033] Specifically, in this embodiment, the simulated phase set refers to the set of phases of all satellite models simulated by the preset simulation platform at a certain moment, simulating the relative positional relationship of the satellite models in orbit, and belongs to absolute phase parameters. The target adjustment phase set in this embodiment refers to the set of phases determined based on the simulated phase of a certain satellite model in the simulated phase set to meet preset operating conditions, and belongs to relative phase parameters. It should be understood that in this embodiment, after setting the satellite model corresponding to the damaged satellite as the damaged satellite model, the damaged satellite model can be removed from the satellite models. Subsequent satellite models will not include the damaged satellite model; that is, the simulated phase set corresponding to all subsequently obtained satellite models will not include the simulated phase of the damaged satellite model, and the target adjustment phase set corresponding to all subsequently determined satellite models will not include the target adjustment phase corresponding to the damaged satellite model.

[0034] In one embodiment, a simulated phase set is formed by using a pre-defined simulation platform to obtain the simulated phases of each satellite model at a certain moment after removing damaged satellite models. Based on this, the simulated phase of any satellite model in the simulated phase set can be selected as the reference phase. Then, according to the constellation's mission requirements, orbital characteristics, and the coordination relationships between satellites, the phase intervals that other satellite models need to adjust relative to the reference phase are determined, thus obtaining the target adjustment phase set for each satellite model. For example, with the goal of uniformly distributing all satellite models except for damaged ones, the ideal phase interval between each satellite model is determined, and combined with the reference phase and the corresponding ideal phase interval, the target adjustment phase for each satellite model is determined, thus obtaining the target adjustment phase set.

[0035] S4: Based on the target adjustment phase set, adjust the phase of at least some satellite models sequentially through a preset simulation platform until the constellation model meets the preset operating conditions, and control the on-orbit satellites according to the current phase interval between each satellite model.

[0036] Specifically, in this embodiment, the preset operating conditions refer to pre-set standards for determining whether the constellation model can operate normally and complete its tasks, such as the deviation between the current simulated phase of the satellite model and the corresponding target adjustment phase being less than a preset threshold. The phase interval referred to in this embodiment represents the phase difference between each satellite model when the constellation model meets the preset operating conditions, which can be determined based on the current simulated phase of each satellite model.

[0037] In one embodiment, the phases of at least a portion of the satellite models can be adjusted sequentially using a preset simulation platform based on a target adjustment phase set (e.g., adjusting the phases of two satellite models at a time). After each adjustment, the constellation model is simulated using the preset simulation platform to determine whether it meets preset operating conditions. If not, the phases of the satellite models are adjusted and simulated again until the constellation model meets the preset operating conditions. When the preset operating conditions are met, the phase interval between each satellite model can be determined based on the current simulated phase of each on-orbit satellite. Furthermore, these phase intervals can be converted into control commands for the actual on-orbit satellites. For example, based on the phase intervals and the current actual phases of the on-orbit satellites, a target phase for the on-orbit satellites is determined, and a phase adjustment command is generated based on the target phase and sent to the on-orbit satellites to control the corresponding on-orbit satellites to adjust their phases, thereby achieving stable constellation operation.

[0038] It should be understood that in this embodiment, during the process of sequentially adjusting the phase of at least some satellite models, phase adjustment of the remaining satellite models can be stopped as long as the constellation model meets the preset operating conditions. After adjustment, the phase interval between each satellite model will at least partially change. In practice, when controlling the on-orbit satellites according to the current phase interval, it is only necessary to selectively adjust the on-orbit satellites whose phase intervals have changed, thereby achieving phase adjustment after satellite damage reconstruction through local phase optimization at a relatively low cost.

[0039] In this embodiment, the preset simulation platform is initialized based on basic information about the on-orbit constellation, such as mission cycles, and operational status data is mapped at preset step sizes. This helps ensure that the constellation model is synchronized with the actual on-orbit constellation state, providing a reliable digital twin environment for subsequent phase adjustment simulations and reliability verification of the target adjustment phase set. Based on this, acquiring telemetry data from the on-orbit constellation helps to accurately grasp the actual operational status of the constellation, thereby enabling timely identification of damaged on-orbit satellites. When on-orbit satellites in the constellation are detected to meet preset damage conditions based on telemetry data, the corresponding on-orbit satellite is marked as a damaged satellite, and its corresponding satellite model is simultaneously set as the damaged satellite model in the preset simulation platform. This helps to synchronize the state of physical space and simulation space, ensuring the accuracy and timeliness of the constellation model. After identifying a damaged on-orbit satellite, the preset simulation platform is used to obtain the simulation phase set corresponding to all satellite models, which helps to reflect the actual position distribution of the current on-orbit satellites. Based on this, using the simulated phase of any satellite model in the simulated phase set as a benchmark, a target adjustment phase set corresponding to all satellite models is determined. Based on this target adjustment phase set, the phases of at least some satellite models are sequentially adjusted through a preset simulation platform. This facilitates gradual, local optimization of the satellite model phases within a simulated environment. After each adjustment, it is determined whether the constellation model meets the preset operating conditions to verify the feasibility of the phase adjustment. When the constellation model meets the preset operating conditions, it indicates that the constellation model can meet the requirements after the current phase adjustment. At this point, the on-orbit satellites are controlled according to the determined current phase interval between each satellite model. This ensures the reliability of on-orbit satellite phase adjustment while minimizing the number of on-orbit satellites requiring phase adjustment, thereby saving energy consumption.

[0040] Thus, this embodiment maps the satellite models in the preset simulation platform to their on-orbit states according to a preset simulation step size. Damaged satellites are detected and their states are synchronized based on telemetry data. After marking the damaged satellites, the simulation platform is used to obtain the simulation phase set of each satellite model. The target adjustment phase set is determined based on the simulation phase of any satellite model. Then, through simulation, at least some satellite models are adjusted sequentially to check if the constellation model meets the preset operating conditions. Only after ensuring the feasibility of phase adjustment is the on-orbit constellation controlled to perform phase adjustment based on the determined current phase interval. This achieves efficient local optimization and feasibility closed-loop verification of phase reconstruction after satellite damage, thereby comprehensively ensuring the reliability of the on-orbit constellation operation.

[0041] Optionally, the telemetry data includes multiple preset monitoring parameters; when the telemetry data of the acquired on-orbit constellation detects that an on-orbit satellite in the constellation meets preset damage conditions, the corresponding on-orbit satellite is marked as a damaged satellite, including: When the preset monitoring parameters exceed the corresponding preset threshold range, the preset monitoring parameters are used as suspected fault parameters, and the first trend feature corresponding to the suspected fault parameters is determined. When the first trend feature meets the preset abnormal conditions corresponding to the suspected fault parameters, the fault type of the damaged satellite is determined based on the suspected fault parameters. A fault score is determined based on suspected fault parameters, first trend characteristics, and fault type. When the fault score is greater than a preset score threshold, the on-orbit satellite corresponding to the suspected fault parameters is recorded as a damaged satellite.

[0042] Specifically, in this embodiment, the preset monitoring parameters refer to specific parameters pre-set for monitoring the status of on-orbit satellites. The preset threshold range refers to the upper and lower limits of the normal range set for each preset monitoring parameter. When a preset monitoring parameter exceeds this range, it indicates a possible anomaly in the on-orbit satellite. For example, the angular velocity of an on-orbit satellite reflects the rate of its attitude change; a normal threshold for its angular velocity can be set to ±0.01° / s. When the actual monitored angular velocity exceeds this threshold range, it indicates that the on-orbit satellite may have been subjected to external interference or that its attitude control system is malfunctioning, and it can be marked as a suspected fault parameter. The first trend characteristic in this embodiment refers to the trend characteristics of the suspected fault parameter over time, such as rising, falling, or fluctuating trends, and the rate of change. The preset anomaly condition in this embodiment refers to the pre-set conditions for each suspected fault parameter to determine whether it truly constitutes an anomaly; these can be set manually in advance. For example, for a certain preset monitoring parameter, the preset anomaly condition could be a continuous increase within a preset time period. The coupling parameter in this embodiment refers to other parameters that are physically or logically related to the suspected fault parameter, and can be set in advance according to the functions of the on-orbit satellite.

[0043] In one embodiment, preset monitoring parameters in the acquired telemetry data can be monitored in real time. When a preset monitoring parameter is detected to exceed its corresponding preset threshold range, the parameter is first marked as a suspected fault parameter. Based on this, a first trend characteristic can be determined by analyzing the data of the suspected fault parameter over a certain period of time (e.g., using mathematical methods such as data fitting and differentiation). For example, if the satellite's battery voltage is detected to be greater than a preset threshold, battery voltage data over five minutes is collected, and the slope of the voltage change is calculated through linear fitting, which is used as the first trend characteristic. Based on this, the determined first trend characteristic can be compared with the preset anomaly conditions corresponding to the suspected fault parameter. If the first trend characteristic meets the preset anomaly conditions, it indicates that the suspected fault parameter may indeed cause a fault, and the fault type of the damaged satellite can be determined based on the suspected fault parameter. For example, if the suspected fault parameter is battery voltage, and its first trend characteristic meets the preset anomaly conditions (e.g., the battery voltage continuously increases within a preset time period), the fault type can be determined as a battery circuit fault. Furthermore, a fault score can be determined based on the suspected fault parameter, the first trend characteristic, and the fault type. For example, a fault score can be calculated using methods such as weighted summation, based on the degree to which suspected fault parameters exceed a preset threshold, the severity of the first trend characteristic (such as the magnitude of the rate of change), and the severity of the fault type (e.g., assigning different severity weights to different fault types based on historical fault data and experience). The obtained fault score is then compared with a preset score threshold. When the fault score exceeds the preset score threshold, the satellite is determined to have a severe fault, reaching the level of damage, and the on-orbit satellite corresponding to the suspected fault parameter is marked as a damaged satellite.

[0044] In this embodiment, by analyzing and judging preset monitoring parameters, first trend characteristics, fault types, and fault scores layer by layer, it is possible to more accurately determine whether a satellite is damaged, avoiding misjudgments or omissions caused by judging based on a single parameter or simple conditions. This helps to identify satellites that have truly experienced serious faults in a timely and accurate manner.

[0045] Optionally, the fault type of the damaged satellite can be determined based on suspected fault parameters, including: Obtain the pre-associated coupling parameters of the suspected fault parameters, and determine the second trend feature corresponding to each coupling parameter; When the second trend feature and the first trend feature meet the fault conditions corresponding to the preset satellite function, the fault type is determined based on the preset satellite function.

[0046] Specifically, in this embodiment, the coupling parameters refer to other parameters that are physically or logically closely related to the suspected fault parameter, and they collectively reflect the operating status of a certain system or function of the satellite. For example, for the suspected fault parameter of satellite battery voltage, its pre-associated coupling parameters may include charging circuit current, load power, etc. The second trend feature referred to in this embodiment refers to the trend characteristics of the coupling parameter over time, which may also include trends such as rising, falling, and fluctuating, as well as information such as the rate of change.

[0047] In one embodiment, coupling parameters associated with suspected fault parameters can be acquired, and data on these coupling parameters over a certain future period can be analyzed to determine a second trend characteristic for each coupling parameter. Based on this, the second trend characteristics of the coupling parameters can be correlated with the first trend characteristics of the suspected fault parameters. When the second trend characteristics and the first trend characteristics satisfy a pre-defined fault condition associated with a certain preset satellite function, the fault type of the on-orbit satellite can be determined based on the preset satellite function. For example, suppose the suspected fault parameter includes the solar panel output voltage, whose corresponding first trend characteristic is a rise rate of 2V per minute. The coupling parameter includes the solar panel temperature, whose corresponding second trend characteristic is a rise rate of 1°C per minute. If the aforementioned first and second trend characteristics satisfy the power system fault conditions (e.g., the solar panel output voltage rise rate is greater than 1.5V per minute and the solar panel temperature rise rate is greater than 0.5°C per minute for 10 consecutive minutes), then the fault type can be determined to be a power system fault.

[0048] In this embodiment, by acquiring the coupling parameters pre-associated with the suspected fault parameters, determining the second trend characteristics of each coupling parameter, and comparing them with preset anomaly conditions, it is beneficial to deeply explore other anomaly parameters related to the suspected fault parameters and comprehensively understand the relevant factors of satellite faults. Furthermore, by determining the fault type based on the correlation between these parameters and satellite functions, fault type diagnosis becomes more accurate, avoiding the one-sidedness that may arise from relying on a single parameter to determine the fault type.

[0049] Optionally, the target adjustment phase set corresponding to each satellite model is determined based on the simulated phase of any satellite model in the simulated phase set, including: Based on the simulated phase set, the phase corresponding to the gap region between two satellite models adjacent to the damaged satellite model is determined, and the gap phase is obtained. Using the simulated phase of any satellite model as a reference, the ideal simulated phase of each satellite model is determined according to the ideal phase interval, thus obtaining the ideal simulated phase set; wherein, the ideal phase interval is determined according to the number of satellite models; The ideal simulation phases corresponding to two satellite models adjacent to the damaged satellite model in the ideal simulation phase set are corrected using a phase correction amount; wherein, the phase correction amount is determined based on the gap phase; the phase interval between the two corrected ideal simulation phases is smaller than the phase interval between the two uncorrected ideal simulation phases; The target adjustment phase set is obtained based on the corrected ideal simulation phase set.

[0050] Specifically, because the damaged satellite model cannot function properly, there are no operational satellite models in a large area near the damaged satellite model in the constellation model (the damaged satellite model is located within the gap area), and this area is called the gap area. In this embodiment, the gap phase refers to the phase range corresponding to the gap area between two satellite models adjacent to the damaged satellite model. In this embodiment, the ideal simulation phase refers to the phase that each satellite model should achieve, determined according to the ideal phase interval and based on the simulation phase of a certain satellite model. In this embodiment, the ideal simulation phase set refers to the set composed of the ideal simulation phases of each satellite model. In this embodiment, the phase correction amount refers to the phase value determined based on the gap phase, used to adjust the ideal simulation phase of two satellite models adjacent to the damaged satellite model in the ideal simulation phase set. This correction amount allows these two adjacent satellite models to move closer to the gap area to compensate for the phase gap caused by the damaged satellite model.

[0051] In one embodiment, two satellite models directly adjacent to the damaged satellite model can be identified first (e.g., based on pre-associated satellite model numbers). Then, the phase range corresponding to the gap region, i.e., the gap phase, is determined based on the difference between the simulated phases of each satellite model. Based on this, the simulated phase of any satellite model in the simulated phase set can be selected as the reference phase. The ideal phase interval is determined based on the total number of satellite models. Then, starting from the reference phase, the ideal simulated phases of other satellite models are determined sequentially according to the ideal phase intervals. Based on this, the phase correction amount can be determined according to the range of the gap phase. For example, the phase correction amount can be determined based on a preset ratio of the gap phase, thereby correcting the ideal simulated phases corresponding to the two satellite models adjacent to the damaged satellite model in the ideal simulated phase set, so that the phase interval between the two corrected ideal simulated phases is smaller than the phase interval between the two uncorrected ideal simulated phases (i.e., both phases simultaneously move closer to the damaged satellite model).

[0052] Assuming that k satellite models remain besides the damaged ones in this embodiment, the simulated phases in the obtained simulated phase set can be sorted in ascending order to obtain the sorted simulated phase set: Based on this, the interval between two adjacent simulated phases can be calculated separately: ; in, This represents the i-th phase interval. This represents the simulated phase of the i-th satellite model at time t. This represents the simulated phase of the (i+1)th satellite model at time t. The phase interval between the first satellite model and the second satellite model needs to take into account the orbital periodicity, i.e.

[0053] Furthermore, after determining each phase interval, the deviation between each phase interval and the ideal phase interval (e.g., considering the phase interval when all satellite models are evenly distributed before the damaged satellite model is marked) can be obtained. When the deviation exceeds a preset deviation threshold, it can be identified as a gap phase, thereby determining the gap region where the phase interval has abnormally increased due to satellite damage. Based on this, the ideal phase interval corresponding to the remaining satellite model after satellite damage can be re-determined. Using the simulated phase of any satellite model as a reference, the ideal simulated phase of each satellite model is determined. In this embodiment, the ideal simulated phase of the satellite model satisfies: ; in, This represents the ideal simulated phase of the i-th satellite model. This represents the simulated phase of the satellite model used as a reference at time t. This represents the ideal phase interval.

[0054] Assuming the two satellite models adjacent to the damaged satellite model are denoted as the left satellite model and the right satellite model, respectively, the phase correction in this embodiment satisfies: ; in, , This indicates the phase correction amount. This represents the phase difference between the notched phase and the ideal phase interval. Indicates the gap phase; This represents the correction factor. The correction factor can be predetermined based on the maneuverability of the corresponding on-orbit satellite in the satellite model.

[0055] Therefore, the ideal simulation phase of the left and right satellite models in this embodiment can be corrected based on the above correction amounts: ; ; in, This represents the ideal simulated phase of the left-hand satellite model before correction. This represents the ideal simulation phase of the corrected left-side satellite model; This represents the ideal simulated phase of the right-hand satellite model before correction; This represents the ideal simulation phase of the corrected right-side satellite model.

[0056] In this embodiment, determining the phase corresponding to the gap region between two satellite models adjacent to the damaged satellite model based on the simulated phase set facilitates the rapid identification of the gap phase caused by the damaged satellite model. Based on this, a phase correction amount is determined based on the gap phase, and this correction amount is used to correct the ideal simulated phases of the two satellite models adjacent to the damaged satellite model. This ensures that the phase interval between the two corrected ideal simulated phases is smaller than the phase interval between the two uncorrected ideal simulated phases, thereby ensuring that the two adjacent satellite models move closer to the location of the damaged satellite, which is beneficial for quickly filling the coverage gap caused by the damaged satellite. Compared to the method of evenly distributing the phase loss caused by the damaged satellite to every remaining satellite model for filling, this embodiment prioritizes locally adjusting the two satellite models adjacent to the damaged satellite to fill the missing phase, which significantly reduces the energy consumption caused by phase adjustment.

[0057] Optionally, based on the target adjustment phase set, the phase of at least some satellite models is sequentially adjusted through a preset simulation platform until the constellation model meets the preset operating conditions. Then, the on-orbit satellites are controlled according to the determined current phase interval between each satellite model, including: The adjustment steps include setting at least two satellite models closest to the gap region as to be adjusted, and generating adjustment instructions based on the target adjustment phases of the satellite models in the to-be-adjusted state in the target adjustment phase set. The adjustment command is sent to the preset simulation platform so that the preset simulation platform can run the simulation of the constellation model after responding to the adjustment command. When the constellation model meets the preset operating conditions, the satellites in orbit are controlled according to the current phase interval. If the constellation model does not meet the preset operating conditions, return to the adjustment steps until the preset termination conditions are met.

[0058] Specifically, in this embodiment, the "pending adjustment state" refers to the at least two satellite models currently awaiting adjustment that are closest to the gap region. It should be understood that, after one adjustment is completed, if the adjustment step is returned to, the satellite models already set to the pending adjustment state are not considered; instead, the at least two satellite models closest to the current gap region are re-determined from the remaining satellite models. The adjustment command in this embodiment refers to an instruction generated based on the target adjustment phase corresponding to the satellite models in the pending adjustment state within the target adjustment phase set. This instruction is used to control the preset simulation platform to adjust the phase of the satellite models and may include information such as the direction and magnitude of the adjustment. The preset termination condition in this embodiment can be set in advance. For example, the preset termination condition may include reaching the maximum number of iterations and / or the constellation model meeting preset operating conditions.

[0059] In one embodiment, based on the simulated phase of each satellite model, at least two satellite models closest to the gap region can be identified and designated as being in a state awaiting adjustment. Based on this, the target adjustment phase corresponding to the satellite model in the state awaiting adjustment can be obtained from the target adjustment phase set. An adjustment command is generated based on the difference between the target adjustment phase and the current phase, specifying the direction (e.g., clockwise or counterclockwise) and magnitude (e.g., the specific phase change in degrees). The generated adjustment command is then sent to a preset simulation platform. Upon receiving the adjustment command, the preset simulation platform can adjust the phase of the satellite model in the constellation model according to the command content and perform operational simulation on the adjusted constellation model to simulate the constellation's operation under the new phase state. Furthermore, this embodiment can obtain constellation model operational state simulation data through the preset simulation platform and determine whether the constellation model meets preset operational conditions. If so, the on-orbit satellites can be controlled according to the current phase interval (e.g., the adjusted phase interval can be converted into control commands for the actual on-orbit satellites and sent to them to control the corresponding on-orbit satellites to adjust their phases). If not, it means that the actual operational requirements are still not met after this phase adjustment. In this case, it is necessary to return to the adjustment step, re-select the satellite models waiting for adjustment and adjust their phases until the constellation model meets the preset operational conditions.

[0060] In this embodiment, each time the phase of the satellite model is adjusted, the satellite model closest to the gap area is set to the state to be adjusted. This allows for the efficient filling of the phase gap area caused by satellite damage. It effectively utilizes the distribution characteristics of satellites around the damaged satellite model, improves the phase reconstruction efficiency after satellite damage, and also narrows the phase adjustment range, thus ensuring the safety and reliability of satellite operation.

[0061] Optionally, before sequentially adjusting the phase of at least a portion of the satellite models based on the target adjustment phase set through a preset simulation platform, the method further includes: Obtain the target coverage area corresponding to the damaged satellite, and use a preset simulation platform to determine the historical coverage performance indicators of the constellation model of the damaged satellite for the target coverage area before it was marked.

[0062] Specifically, the target coverage area referred to in this embodiment refers to the specific geographical area that the damaged satellite was responsible for covering when it was working normally, such as a specific communication service area in a communication constellation, or a specific observation area in an observation constellation. The historical coverage performance index referred to in this embodiment refers to the quantitative index determined by the constellation model of the target coverage area before the damaged satellite was marked, using a preset simulation platform. The cumulative coverage duration corresponding to each preset observation point in the target coverage area can be determined by using the preset simulation platform within a certain period before the damaged satellite was marked.

[0063] In this embodiment, after detecting that the on-orbit satellite meets the preset damage conditions, the historical coverage performance index of the constellation model for the target coverage area before the damaged satellite is marked can be determined using a preset simulation platform. This provides an accurate reference for determining whether the mission function for the target coverage area can be restored after each subsequent phase adjustment.

[0064] Optionally, after sending the adjustment command to the preset simulation platform so that the preset simulation platform can run the simulation of the constellation model after responding to the adjustment command, the method further includes: Determine the current coverage performance metrics of the constellation model for the target coverage area; Obtain the current simulation phase corresponding to each satellite model, determine the current phase interval between each satellite model based on the current simulation phase, and determine the phase difference between each current phase interval and the ideal phase interval respectively; When all phase differences are within the preset range, and the ratio of the current coverage performance index to the historical coverage performance index is greater than the preset threshold, the constellation model meets the preset operating conditions.

[0065] Specifically, in this embodiment, the current coverage performance index refers to the quantitative index determined for the target coverage area after the constellation model is simulated using a preset simulation platform under the control of response adjustment commands. This index is used to evaluate the current constellation model's coverage performance in that area and corresponds to the previously determined historical coverage performance index. It can also be determined based on the cumulative coverage duration corresponding to each preset observation point in the target coverage area within a certain time period. The current simulation phase in this embodiment refers to the phase corresponding to each satellite model after the constellation model is simulated using a preset simulation platform under the control of response adjustment commands. It reflects the relative positional relationship of the satellite models at the current simulation moment. The phase difference in this embodiment represents the difference between each current phase interval and the ideal phase interval, used to measure the degree of deviation between the current constellation model's phase layout and the ideal state.

[0066] In one embodiment, after each phase adjustment, a preset simulation platform can be used to determine the current coverage performance index of the constellation model for the target coverage area, and obtain the current simulated phase corresponding to each satellite model. Based on the current simulated phase, the current phase interval between each satellite model is determined (e.g., constructing a current simulated phase set, sorting the current simulated phases in the set in ascending order, and determining the difference between every two adjacent current simulated phases). Based on this, it can be determined whether each phase difference is within a preset range (e.g., ±5°), and whether the ratio of the current coverage performance index to the historical coverage performance index is greater than a preset threshold (e.g., 95%). When the above conditions are met simultaneously, the constellation model is determined to meet the preset operating conditions.

[0067] In this embodiment, by determining the current coverage performance indicators and the phase difference between the current phase interval and the ideal phase interval between satellite models, it is beneficial to understand the ability of the remaining satellite models to compensate for the mission gap caused by the damaged satellite models after this phase adjustment, as well as the balance among the current satellite models. A comprehensive evaluation of the constellation model after phase adjustment, focusing on both coverage performance compensation capability and phase interval balance, helps ensure the accuracy and comprehensiveness of the constellation model operation evaluation, thereby ensuring the reliability of subsequent control of on-orbit satellites based on the current phase interval.

[0068] like Figure 2 As shown, an embodiment of the present invention provides a phase adjustment device 200 for satellite damage reconstruction, comprising: The mapping module 210 is used to initialize the preset simulation platform based on the acquired basic information of the on-orbit constellation, and to map the acquired operating status data of the on-orbit constellation to the preset simulation platform according to the preset simulation step size; wherein, the basic information includes the mission cycle, and the preset simulation platform is used to perform running simulation on the constellation model corresponding to the on-orbit constellation. The detection module 220 is used to mark the corresponding on-orbit satellite as a damaged satellite when it is detected based on the acquired telemetry data of the on-orbit constellation that the on-orbit satellite in the on-orbit constellation meets the preset damage conditions, and to use the preset simulation platform to set the satellite model corresponding to the damaged satellite in the constellation model as the damaged satellite model. The determination module 230 is used to obtain the simulation phase set corresponding to each of the satellite models after removing the damaged satellite models using the preset simulation platform, and to determine the target adjustment phase set corresponding to each of the satellite models based on the simulation phase of any of the satellite models in the simulation phase set; The control module 240 is used to adjust the phase of at least some of the satellite models sequentially through the preset simulation platform based on the target adjustment phase set until the constellation model meets the preset operating conditions, and then control the on-orbit satellites according to the determined current phase interval between each of the satellite models.

[0069] The phase adjustment device for satellite damage reconstruction provided in this embodiment and the phase adjustment method for satellite damage reconstruction can produce basically the same technical effects, and will not be described in detail here.

[0070] like Figure 3 As shown, an electronic device 300 provided in this embodiment of the invention includes a memory 310 and a processor 320; the memory 310 is used to store a computer program; the processor 320 is used to implement the phase adjustment method for satellite damage reconstruction as described above when the computer program is executed.

[0071] Alternatively, an electronic device 300 includes a memory 310 and a processor 320 coupled to the memory 310; the memory 310 is configured to store a computer program; and the processor 320 is configured to perform the following operations when the computer program is executed: The preset simulation platform is initialized based on the acquired basic information of the on-orbit constellation, and the acquired operational status data of the on-orbit constellation is mapped to the preset simulation platform according to the preset simulation step size; wherein, the basic information includes the mission cycle, and the preset simulation platform is used to perform operational simulation on the constellation model corresponding to the on-orbit constellation; When the telemetry data of the acquired on-orbit constellation is used to detect that an on-orbit satellite in the on-orbit constellation meets the preset damage conditions, the corresponding on-orbit satellite is marked as a damaged satellite, and the satellite model corresponding to the damaged satellite in the constellation model is set as a damaged satellite model using the preset simulation platform. The simulation phase set corresponding to each satellite model after removing the damaged satellite model is obtained using the preset simulation platform, and the target adjustment phase set corresponding to each satellite model is determined based on the simulation phase of any satellite model in the simulation phase set; Based on the target adjustment phase set, the phase of at least some of the satellite models is adjusted sequentially through the preset simulation platform until the constellation model meets the preset operating conditions. Then, the on-orbit satellite is controlled according to the current phase interval between each of the satellite models.

[0072] The electronic equipment and the phase adjustment method for satellite damage reconstruction provided in this embodiment can produce basically the same technical effects, and will not be described again here.

[0073] This invention provides a computer-readable storage medium storing a computer program. When the computer program is executed by a processor, it implements the phase adjustment method for satellite damage reconstruction as described above.

[0074] Alternatively, a non-volatile computer-readable storage medium storing a computer program that, when executed by a processor, causes the processor to perform the following operations: The preset simulation platform is initialized based on the acquired basic information of the on-orbit constellation, and the acquired operational status data of the on-orbit constellation is mapped to the preset simulation platform according to the preset simulation step size; wherein, the basic information includes the mission cycle, and the preset simulation platform is used to perform operational simulation on the constellation model corresponding to the on-orbit constellation; When the telemetry data of the acquired on-orbit constellation is used to detect that an on-orbit satellite in the on-orbit constellation meets the preset damage conditions, the corresponding on-orbit satellite is marked as a damaged satellite, and the satellite model corresponding to the damaged satellite in the constellation model is set as a damaged satellite model using the preset simulation platform. The simulation phase set corresponding to each satellite model after removing the damaged satellite model is obtained using the preset simulation platform, and the target adjustment phase set corresponding to each satellite model is determined based on the simulation phase of any satellite model in the simulation phase set; Based on the target adjustment phase set, the phase of at least some of the satellite models is adjusted sequentially through the preset simulation platform until the constellation model meets the preset operating conditions. Then, the on-orbit satellite is controlled according to the current phase interval between each of the satellite models.

[0075] The computer-readable storage medium provided in this embodiment and the phase adjustment method for satellite damage reconstruction can produce essentially the same technical effects, and will not be described again here.

[0076] The present invention will now be described an electronic device 300 that can serve as a server or client of the present invention, which is an example of a hardware device that can be applied to various aspects of the present invention. Electronic device 300 is intended to represent various forms of digital electronic computer devices, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. Electronic device 300 can also represent various forms of mobile devices, such as personal digital assistants, cellular phones, smartphones, wearable devices, and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely illustrative and are not intended to limit the implementation of the invention described and / or claimed herein.

[0077] Electronic device 300 includes a computing unit that can perform various appropriate actions and processes based on a computer program stored in read-only memory (ROM) or a computer program loaded from a storage unit into random access memory (RAM). The RAM may also store various programs and data required for device operation. The computing unit, ROM, and RAM are interconnected via a bus. Input / output (I / O) interfaces are also connected to the bus.

[0078] Those skilled in the art will understand that all or part of the processes in the above embodiments can be implemented by a computer program instructing related hardware. The program can be stored in a computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods. The storage medium can be a magnetic disk, optical disk, read-only memory (ROM), or random access memory (RAM), etc. In this application, the units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of the embodiments of the present invention according to actual needs. Furthermore, the functional units in the various embodiments of the present invention can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated units can be implemented in hardware or as software functional units.

[0079] While the present invention has been disclosed above, its scope of protection is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention, and all such changes and modifications will fall within the scope of protection of the present invention.

Claims

1. A phase adjustment method for satellite damage reconstruction, characterized in that, include: The preset simulation platform is initialized based on the acquired basic information of the on-orbit constellation, and the acquired operational status data of the on-orbit constellation is mapped to the preset simulation platform according to the preset simulation step size; wherein, the basic information includes the mission cycle, and the preset simulation platform is used to perform operational simulation on the constellation model corresponding to the on-orbit constellation; When the telemetry data of the acquired on-orbit constellation is used to detect that an on-orbit satellite in the on-orbit constellation meets the preset damage conditions, the corresponding on-orbit satellite is marked as a damaged satellite, and the satellite model corresponding to the damaged satellite in the constellation model is set as a damaged satellite model using the preset simulation platform. The simulation phase set corresponding to each satellite model after removing the damaged satellite model is obtained using the preset simulation platform, and the target adjustment phase set corresponding to each satellite model is determined based on the simulation phase of any satellite model in the simulation phase set; Based on the target adjustment phase set, the phase of at least some of the satellite models is adjusted sequentially through the preset simulation platform until the constellation model meets the preset operating conditions. Then, the on-orbit satellite is controlled according to the current phase interval between each of the satellite models.

2. The phase adjustment method for satellite damage reconstruction according to claim 1, characterized in that, The telemetry data includes multiple preset monitoring parameters; the step of marking the corresponding on-orbit satellite as a damaged satellite when the on-orbit satellite in the on-orbit constellation is detected based on the acquired telemetry data of the on-orbit constellation and meets preset damage conditions includes: When the preset monitoring parameter exceeds the corresponding preset threshold range, the preset monitoring parameter is used as a suspected fault parameter, and the first trend feature corresponding to the suspected fault parameter is determined. When the first trend feature meets the preset abnormal conditions corresponding to the suspected fault parameters, the fault type of the damaged satellite is determined based on the suspected fault parameters; A fault score is determined based on the suspected fault parameters, the first trend feature, and the fault type. When the fault score is greater than a preset score threshold, the on-orbit satellite corresponding to the suspected fault parameters is recorded as the damaged satellite.

3. The phase adjustment method for satellite damage reconstruction according to claim 2, characterized in that, Determining the fault type of the damaged satellite based on the suspected fault parameters includes: Obtain each coupling parameter pre-associated with the suspected fault parameter, and determine the second trend feature corresponding to each coupling parameter respectively; When the second trend feature and the first trend feature meet the fault conditions corresponding to the preset satellite function, the fault type is determined based on the preset satellite function.

4. The phase adjustment method for satellite damage reconstruction according to claim 1, characterized in that, The step of determining the target adjustment phase set corresponding to each satellite model based on the simulated phase of any of the satellite models in the simulated phase set includes: Based on the simulated phase set, the phase corresponding to the gap region between two satellite models adjacent to the damaged satellite model is determined, and the gap phase is obtained; Using the simulated phase of any of the satellite models as a reference, the ideal simulated phase of each satellite model is determined according to the ideal phase interval, thus obtaining the ideal simulated phase set; wherein, the ideal phase interval is determined according to the number of satellite models; The ideal simulation phases corresponding to two satellite models adjacent to the damaged satellite model in the ideal simulation phase set are corrected using a phase correction amount; wherein, the phase correction amount is determined based on the gap phase; the phase interval between the two corrected ideal simulation phases is smaller than the phase interval between the two uncorrected ideal simulation phases; The target adjustment phase set is obtained based on the corrected ideal simulation phase set.

5. The phase adjustment method for satellite damage reconstruction according to claim 4, characterized in that, The step of adjusting the phase set based on the target, sequentially adjusting the phase of at least some of the satellite models through the preset simulation platform until the constellation model meets the preset operating conditions, and then controlling the on-orbit satellites according to the determined current phase interval between each of the satellite models, includes: The adjustment step includes setting at least two satellite models closest to the gap region as to be adjusted, and generating an adjustment command based on the target adjustment phase corresponding to the satellite models in the to-be-adjusted state in the target adjustment phase set; The adjustment command is sent to the preset simulation platform so that the preset simulation platform can perform a simulation of the constellation model after responding to the adjustment command. When the constellation model meets the preset operating conditions, the on-orbit satellite is controlled according to the current phase interval; If the constellation model does not meet the preset operating conditions, return to the adjustment steps until the preset termination conditions are met.

6. The phase adjustment method for satellite damage reconstruction according to claim 5, characterized in that, Before sequentially adjusting the phase of at least a portion of the satellite model based on the target adjustment phase set through the preset simulation platform, the method further includes: Obtain the target coverage area corresponding to the damaged satellite, and use the preset simulation platform to determine the historical coverage performance index of the constellation model for the target coverage area before the damaged satellite was marked.

7. The phase adjustment method for satellite damage reconstruction according to claim 6, characterized in that, After sending the adjustment command to the preset simulation platform to cause the preset simulation platform to perform a simulation of the constellation model after responding to the adjustment command, the method further includes: Determine the current coverage performance index of the constellation model for the target coverage area; Obtain the current simulation phase corresponding to each of the satellite models, determine the current phase interval between each of the satellite models based on the current simulation phase, and determine the phase difference between each current phase interval and the ideal phase interval respectively; When all the phase differences are within a preset range, and the ratio of the current coverage performance index to the historical coverage performance index is greater than a preset threshold, the constellation model is indicated to meet the preset operating conditions.

8. A phase adjustment device for satellite damage reconstruction, characterized in that, include: The mapping module is used to initialize the preset simulation platform based on the acquired basic information of the on-orbit constellation, and to map the acquired operational status data of the on-orbit constellation to the preset simulation platform according to the preset simulation step size; wherein, the basic information includes the mission cycle, and the preset simulation platform is used to perform operational simulation on the constellation model corresponding to the on-orbit constellation; The detection module is used to mark the corresponding on-orbit satellite as a damaged satellite when the on-orbit satellite in the on-orbit constellation is detected to meet the preset damage conditions based on the acquired telemetry data of the on-orbit constellation, and to use the preset simulation platform to set the satellite model corresponding to the damaged satellite in the constellation model as the damaged satellite model. The determination module is used to obtain the simulation phase set corresponding to each of the satellite models after removing the damaged satellite models using the preset simulation platform, and to determine the target adjustment phase set corresponding to each of the satellite models based on the simulation phase of any of the satellite models in the simulation phase set; The control module is used to adjust the phase of at least some of the satellite models sequentially through the preset simulation platform based on the target adjustment phase set until the constellation model meets the preset operating conditions, and then control the on-orbit satellites according to the determined current phase interval between each of the satellite models.

9. An electronic device, characterized in that, Including memory and processor; The memory is used to store computer programs; The processor is configured to implement the phase adjustment method for satellite damage reconstruction as described in any one of claims 1 to 7 when executing the computer program.

10. A computer-readable storage medium, characterized in that, The storage medium stores a computer program, which, when executed by a processor, implements the phase adjustment method for satellite damage reconstruction as described in any one of claims 1 to 7.

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