A digital accompanying flight system and method for multi-satellite formation networking flight mission

Abstract

The present invention provides a digital flight companion system and method for multi-satellite formation networking flight missions, which includes: a digital satellite twin model construction subsystem, a satellite state deduction and prediction subsystem, a digital flight companion comparison subsystem, a mission evaluation and analysis subsystem, a comprehensive display subsystem, and a system operation support environment. Through this digital flight companion system, digital verification of flight plans for single-satellite independent flight, multi-scenario intersatellite formation, and networking flight missions, as well as digital flight companionship in orbit, can be achieved. Digital technology support is provided for ground operations in multiple stages before, during, and after satellite missions, thereby improving the implementation efficiency of satellite missions. In this way, the adequacy and coverage of the digital flight companion system's testing and solution verification can be improved, thereby ensuring the safety, stability, and quality and efficiency of satellite operations before and on orbit.

Description

Technical Field

[0001] The present invention relates to the field of satellite engineering technology, and in particular to a digital accompanying flight system and method for a multi-satellite formation networking flight mission. Background Art

[0002] With the continuous advancement of aerospace technology and capabilities, deep space exploration missions, such as those using the Moon as a frontier, are underway at full speed. With the growing understanding and utilization of deep space resources and their value, and the continuous breakthroughs and updates in exploration methods and technologies, multi-scenario, multi-mission exploration and flight methods will be required to meet more space application goals and technology verification requirements.

[0003] Currently, satellite engineering development and operation face numerous challenges. First, new technologies and solutions, such as deep-space orbit design and optimization, autonomous control, deep-space exploration communications, and novel scientific payloads, are rapidly iterating and being implemented. This leads to an increasing number of exploratory technologies being applied to satellite missions, requiring no prior knowledge and resulting in high trial-and-error costs. Second, satellites operate in complex on-orbit modes and face numerous mission constraints. The time, cost, and conditions for engineering development and testing are limited, making it difficult to conduct full-process system testing across multiple scenarios and constraints.

[0004] In addition to the aforementioned issues, the coordinated work of formation and networking is even more complex for multi-satellite formation and networking flight missions. Furthermore, with the advancement of spacecraft digitalization, existing engineering development technologies propose the possibility of conducting digital flight missions based on operational models and digital operating environments. Through the interaction of ground-to-space data, relevant mission data can be collected to support spacecraft health assessments, and digital flight mission systems can be used to support fault diagnosis and solution verification. However, the existing digital flight mission system's testing and solution verification is inadequate and incomplete, making it impossible to guarantee the safety, stability, and operation of satellites before and during missions. Summary of the Invention

[0005] The technical problem to be solved by the present invention is that the existing digital flight companion system has low sufficiency and coverage in testing and solution verification, resulting in the inability to ensure the safety, stability and operation of satellites before and in orbit.

[0006] To solve the above technical problems, the present invention provides a digital accompanying flight system and method for a multi-satellite formation networking flight mission, which specifically adopts the following technical solutions:

[0007] In the first aspect, the present invention provides a digital flight companion system for multi-satellite formation networking flight missions, including: a digital satellite twin model construction subsystem, a satellite status deduction and prediction subsystem, a digital flight companion comparison subsystem, a mission evaluation and analysis subsystem, an integrated display subsystem, and a system operation support environment.

[0008] The digital satellite twin model construction subsystem is used to construct a multi-satellite twin digital model based on the development and design data of a multi-satellite formation. The multi-satellite twin digital model includes a digital model corresponding to each satellite in the multi-satellite formation. The satellite state deduction and prediction subsystem is used to call the multi-satellite twin digital model based on the simulation scenario engineering file data of the satellite flight mission scenario to perform satellite state simulation of the multi-satellite formation and generate satellite state simulation data. The digital flight comparison subsystem is used to obtain multi-satellite telemetry data of the multi-satellite formation, update the model state of the multi-satellite twin digital model according to a preset update strategy, perform flight simulation of the multi-satellite formation, and generate flight simulation data. The flight simulation data is then correlated and compared with the multi-satellite formation's on-orbit telemetry data to generate flight comparison results. The flight comparison results are used to diagnose anomalies in the multi-satellite formation or to perform model corrections on the multi-satellite twin digital model. The mission evaluation and analysis subsystem is used to verify the correctness of the multi-satellite formation's flight mission execution process based on satellite status simulation data and accompanying flight simulation data, based on preset flight program execution conditions, preset flight program interpretation conditions, and preset mission constraints. It also evaluates and analyzes the performance of the multi-satellite formation's flight mission execution, generating execution process verification results and execution performance analysis results. The integrated display subsystem is used to display one or more of the following in a preset display format: multi-satellite twin digital models, the satellite status simulation process, the accompanying flight simulation process, satellite status simulation data, accompanying flight simulation data, accompanying flight comparison results, execution process verification results, and execution performance analysis results. The system operation support environment is used to provide a support environment for the operation, system configuration, and data interaction of the digital satellite twin model construction subsystem, satellite status deduction and prediction subsystem, digital accompanying flight comparison subsystem, mission evaluation and analysis subsystem, and integrated display subsystem.

[0009] In combination with the first aspect, in an optional implementation method, the above-mentioned digital satellite twin model construction subsystem is also used to encapsulate multiple satellite twin digital models and simulate operation according to the multi-source heterogeneous model interface protocol provided by the system operation support environment.

[0010] In combination with the first aspect, in an optional implementation method, the above-mentioned multi-satellite twin digital model has one or more of the following data interfaces: initial parameter interface, input data interface, output data interface, remote control injection interface, telemetry injection interface, and fault injection interface.

[0011] In combination with the first aspect, in an optional implementation method, the digital model corresponding to each satellite includes one or more of the following models: an integrated electronic model, an energy model, a measurement and control model, a thruster model, an actuator model, a sensor model, a mechanism model, a carrier tube unit model, and a computing unit model.

[0012] In combination with the first aspect, in an optional implementation method, the above-mentioned satellite state deduction and prediction subsystem is specifically used for: when the simulation assumption engineering file data is received from the mission scenario configuration, it is used for the deduction and simulation of the mission scenario of the multi-satellite formation; when the simulation assumption engineering file data is received from the digital companion flight, it is used for the predicted state simulation of the multi-satellite formation.

[0013] In combination with the first aspect, in an optional implementation method, the above-mentioned digital accompanying flight comparison subsystem includes: an accompanying flight data parsing and matching module, an accompanying flight data comparison module, and an accompanying flight data analysis module. Among them, the accompanying flight data parsing and matching module is used to parse the accompanying flight simulation data and the on-orbit telemetry data of the multi-satellite formation, perform spatiotemporal data matching and classification processing, and obtain matching data. The accompanying flight data comparison module is used to perform the same reference comparison on the matching data through error calculation and error statistics methods to generate a digital accompanying flight state comparison result. The accompanying flight data analysis module is used to determine the abnormal feature results based on the digital accompanying flight state comparison results through a single parameter method or a multi-parameter correlation analysis method to generate an accompanying flight comparison result.

[0014] In conjunction with the first aspect, in one optional implementation, the preset update strategy includes one of the following strategies: an immediate update strategy, a timed update strategy, an entry-exit tracking and control zone update strategy, and a maneuverable update strategy. The entry-exit tracking and control zone update strategy is based on the tracking and control arc, with updates occurring upon entry and exit; the maneuverable update strategy is based on the tracking and control arc, with updates occurring upon entry and exit; and the maneuverable update strategy is based on updates occurring in response to an update instruction.

[0015] In conjunction with the first aspect, in one optional implementation, the mission evaluation and analysis subsystem includes an execution process interpretation module and an execution effect analysis module. The execution process interpretation module is configured to determine a process interpretation event table based on preset flight program execution conditions and preset flight program interpretation conditions; and to generate execution process verification results by interpreting each item in the process interpretation event table based on satellite state simulation data and accompanying flight simulation data. The execution effect analysis module is configured to perform evaluation and analysis based on the satellite state simulation data and accompanying flight simulation data using a performance evaluation factor model to generate execution effect analysis results.

[0016] In combination with the first aspect, in an optional implementation method, the above-mentioned performance evaluation factor model includes one or more of the following models: Earth-Moon shadow model, energy balance model, network link analysis model, Sun-Moon geometric characteristics model, orbit characteristics model, attitude characteristics model.

[0017] The digital flight companion system for multi-satellite formation networked flight missions provided by the present invention can construct digital twin models of multiple satellites at the individual, subsystem, and system levels through a digital satellite twin model construction subsystem. This model replicates onboard information, control, and functional flows, interacting with semi-physical and engineering development to enhance the adequacy and coverage of satellite system testing and solution verification. The system is designed to support various operational modes, including simulation and digital flight companions, for different stages of mission development and operation. Before a mission, the satellite state prediction subsystem can rapidly simulate the satellite flight process, state, and result data through ultra-real-time simulation. This controllable process facilitates the simulation, analysis, and verification of both normal and fault response plans. During on-orbit operations, the digital flight companion comparison subsystem synchronizes its flight operations with the physical entity, providing digital technical support for on-orbit operational status tracking and analysis, status prediction, risk prediction, and auxiliary fault diagnosis. The mission assessment and analysis subsystem can perform mission assessment and analysis based on various application modes, improving the safety, stability, and efficiency of satellite operations both before and during missions. In summary, the accompanying flight system can effectively improve the adequacy and coverage of the testing and solution verification of the digital accompanying flight system, and improve the safety, stability, and efficiency of satellite operations before and in orbit.

[0018] In a second aspect, the present invention provides a digital accompanying flight method for a multi-satellite formation networking flight mission, comprising: first, constructing a multi-satellite twin digital model based on the research and design data of the multi-satellite formation, the multi-satellite twin digital model including: a digital model corresponding to each satellite in the multi-satellite formation; then, calling the multi-satellite twin digital model based on the simulation assumption engineering file data of the satellite flight mission scenario to perform satellite state simulation of the multi-satellite formation and generate satellite state simulation data. Acquire multi-satellite telemetry data of the multi-satellite formation, update the model state of the multi-satellite twin digital model according to a preset update strategy, perform accompanying flight simulation of the multi-satellite formation, and generate accompanying flight simulation data; and associate and compare the accompanying flight simulation data with the on-orbit telemetry data of the multi-satellite formation to generate accompanying flight comparison results, which are used to perform abnormal diagnosis of the multi-satellite formation or perform model correction on the multi-satellite twin digital model. Next, based on the satellite state simulation data and accompanying flight simulation data, and based on the preset flight program execution conditions, preset flight program interpretation conditions, and preset mission constraints, the correctness of the multi-satellite formation flight mission execution process is verified. The performance of the multi-satellite formation flight mission is evaluated and analyzed, generating execution process verification results and execution performance analysis results. Finally, one or more of the following is displayed in a preset display format: the multi-satellite twin digital model, the satellite state simulation process, the accompanying flight simulation process, satellite state simulation data, accompanying flight simulation data, accompanying flight comparison results, execution process verification results, and execution performance analysis results. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 A schematic structural diagram of a digital accompanying flight system for a multi-satellite formation networking flight mission provided by an embodiment of the present invention;

[0020] Figure 2 A flowchart of the operation mode of a digital accompanying flight system for a multi-satellite formation networking flight mission provided by an embodiment of the present invention;

[0021] Figure 3 An information flow diagram of a digital accompanying flight mode provided by an embodiment of the present invention;

[0022] Figure 4 A schematic flow chart of a digital accompanying flight method for a multi-satellite formation networking flight mission provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0023] The following embodiments are described in detail, with examples illustrated in the accompanying drawings. When the following description refers to the drawings, identical numerals in different figures represent identical or similar elements unless otherwise indicated. The embodiments described in the following embodiments are not intended to represent all possible implementations consistent with the present application. They are merely examples of systems and methods consistent with certain aspects of the present application, as detailed in the claims.

[0024] As people continue to understand and utilize deep space resources and their value, the demand for satellite space applications and technology verification is increasing and evolving. During satellite development and operation, the application of new technologies and solutions presents risks associated with a lack of prior knowledge and high trial-and-error costs. On-orbit operation is complex, mission constraints are numerous, and the time, cost, and resources for engineering development and testing are limited. Relying solely on engineering development and semi-physical testing makes it difficult to achieve comprehensive and comprehensive system testing throughout the entire satellite process. Furthermore, on-orbit satellite operations are constrained by orbital constraints and measurement and control resources, making it difficult for ground personnel to fully understand the satellite's on-orbit operating status at all times.

[0025] For multi-satellite formation and networking flight missions, the coordination of formation and networking becomes more complex. Furthermore, with the advancement of spacecraft digitalization, digital flight support can be implemented based on operational models and a digital operating environment. Through ground-to-space data exchange, relevant mission data can be collected to support spacecraft health assessments. The digital flight support system can also support fault diagnosis and solution verification. However, the adequacy and coverage of existing digital flight support system testing and solution verification are low, making it impossible to ensure the safety, stability, and operation of satellites before and during missions.

[0026] In order to solve the above problems, the embodiment of the present application provides a digital flight companion system and method for multi-satellite formation networking flight missions. Specifically, the system includes: a digital satellite twin model construction subsystem, a satellite status deduction and prediction subsystem, a digital flight companion comparison subsystem, a mission evaluation and analysis subsystem, a comprehensive display subsystem, and a system operation support environment. Through this digital flight companion system, digital verification of flight plans for single-satellite independent flight, multi-scenario intersatellite formation and networking flight missions, and digital flight companionship in orbit can be achieved, providing digital technical support for ground operations from multiple stages before, during and after the mission, thereby improving the efficiency of mission implementation. In this way, the adequacy and coverage of the testing and solution verification of the digital flight companion system can be improved, so as to ensure the safety, stability, and quality and efficiency of satellite operations before and on orbit.

[0027] The following describes the solution provided by the embodiments of the present application in conjunction with the accompanying drawings.

[0028] For details, see Figure 1 , which is a structural diagram of a digital accompanying flight system for a multi-satellite formation networking flight mission provided by an embodiment of the present invention, such as Figure 1 As shown, the digital flight companion system 100 for the multi-satellite formation networking flight mission provided by the present invention includes: a digital satellite twin model construction subsystem 101, a satellite status deduction and prediction subsystem 102, a digital flight companion comparison subsystem 103, a mission evaluation and analysis subsystem 104, an integrated display subsystem 105 and a system operation support environment 106.

[0029] In an embodiment of the present invention, the system architecture of the digital accompanying flight system 100 (hereinafter referred to as the accompanying flight system) for the multi-satellite formation networking flight mission can be divided into: a support layer, a model layer, an application layer, and a display layer. Among them, the system operation support environment 106 is in the support layer, which can provide the system's environmental support functions for the deployment of other subsystems, the basic framework of the operation solution platform, system configuration, data interaction, and operation management. The digital satellite twin model construction subsystem 101 is in the model layer. The multi-satellite twin digital model constructed by the digital satellite twin model construction subsystem 101 can be used to improve the application benefits of the accompanying flight system. The digital satellite twin model construction subsystem 101 can provide model support for the satellite state deduction and prediction subsystem 102, the digital accompanying flight comparison subsystem 103, and the mission evaluation and analysis subsystem 104, respectively, to realize the output of model satellite state simulation data. In addition, the accuracy of the multi-satellite twin digital model can be completed by iteratively updating the model with the digital accompanying flight comparison subsystem 103 to ensure that the multi-satellite twin digital model continues to play a role. The satellite status prediction subsystem 102, the digital flight comparison subsystem 103, and the mission assessment and analysis subsystem 104 are located at the application layer and are primarily used to coordinate the assessment and analysis of various mission scenarios, modes, and application tasks. The satellite status prediction subsystem 102 and the digital flight comparison subsystem 103 provide analytical support for the mission assessment and analysis subsystem 104. The integrated display subsystem 105 is located at the top layer and belongs to the presentation layer. It primarily provides display support, enabling intuitive demonstrations of various digital models, processes, and performance, enhancing the comprehensive demonstration capabilities of on-orbit operations and improving on-orbit operational and analytical capabilities.

[0030] Among them, the digital satellite twin model construction subsystem 101 can be used to construct a multi-satellite twin digital model based on the research and design data of the multi-satellite formation. The multi-satellite twin digital model includes: a digital model corresponding to each satellite in the multi-satellite formation.

[0031] Specifically, the multi-satellite twin digital model of the digital satellite twin model construction subsystem 101 can be constructed according to the single-machine model based on the research and design data of the multi-satellite formation by the digital satellite twin model construction subsystem 101, and is integrated at the single-machine, subsystem, and system levels. The information flow, control flow, and functional chain design of the twin satellite work support satellite mission-level simulation.

[0032] In some embodiments, the digital satellite twin model construction subsystem 101 is also used to encapsulate multiple satellite twin digital models and simulate operations according to the multi-source heterogeneous model interface protocol provided by the system operation support environment 106.

[0033] In some embodiments, the multi-satellite twin digital model has one or more of the following data interfaces: initial parameter interface, input data interface, output data interface, remote control injection interface, telemetry injection interface, and fault injection interface.

[0034] Specifically, when the companion flight system is applied as a digital verification or status prediction mode, the system operation support environment 106 can assign initial parameters to the corresponding satellite digital model in the multi-satellite twin digital model through the initial parameter interface, and perform mission scenario deduction based on this initial parameter. The input data interface and the output data interface are interfaces for data and information communication between the digital models corresponding to each satellite in the multi-satellite twin digital model. The remote control injection interface is the interface for the parallel satellite system to receive uplink remote control data and injection data. The telemetry injection interface is used to receive on-orbit telemetry data and update the current working status of the satellite digital model to realize status update in the digital companion flight mode. The fault injection interface responds to the triggering of the fault signal to simulate or reproduce the fault state.

[0035] In some embodiments, in order to combine the processes and functions required to execute formation networking application tasks of multiple satellites, the digital model corresponding to each satellite includes one or more of the following models: integrated electronic model, energy model, measurement and control model, propulsion model, actuator model, sensor model, mechanism model, carrier tube unit model, and computing unit model.

[0036] The integrated electronics model primarily implements integrated satellite management and control, providing essential operational support for energy, measurement and control (T&C), orbit calculation, attitude and orbit control, and other aspects. Exemplarily, the integrated electronics model may include a T&C management module, an energy management module, a satellite operations management module, an orbit calculation module, a power distribution management module, and a payload management module. The energy model primarily implements energy supply and distribution for a multi-satellite formation and, for example, may include a solar array model, a battery model, and a load model. The T&C model can simulate uplink and downlink data transmission. The propulsion model can be configured to include electric or chemical propulsion models based on actual applications. Actuator models may include reaction flywheel models and magnetic torque models. Sensor models may include fiber optic gyroscope models, star sensor models, inertial measurement unit models, accelerometer models, simulated solar sensors, and magnetometer models. The mechanism model primarily replicates the satellite's SADA solar array drive mechanism control or antenna rotation mechanism control. The computing unit model supports intersatellite network link maintenance and link switching. The carrier-based unit model can be used to support satellite-to-ground and inter-satellite communication data transmission and management.

[0037] In this embodiment of the present invention, the multi-satellite twin digital model can be assembled based on specific application scenarios or objects, and its relationship to the digital model can be set to set the model state. Function, performance, and mission testing can be performed between multiple satellite systems, within a single satellite system, and within a single satellite subsystem. This application does not specifically limit the internal structure of the multi-satellite twin digital model.

[0038] The satellite state deduction and prediction subsystem 102 can be used to call a multi-satellite twin digital model based on the simulation scenario engineering file data of the satellite flight mission scenario to perform satellite state simulation of a multi-satellite formation and generate satellite state simulation data.

[0039] In some embodiments, the satellite state prediction subsystem 102 can be used to simulate a multi-satellite formation mission scenario when the simulation scenario engineering file data is received from a mission scenario configuration. When the simulation scenario engineering file data is received from a digital companion flight, the subsystem can be used to simulate the predicted state of the multi-satellite formation, i.e., predict the state of the current satellites over a period of time in the future.

[0040] Specifically, the satellite state prediction and prediction subsystem 102 can perform ultra-real-time simulations of normal flight plans and fault response plans, verifying their correctness and rationality. When the satellite state prediction and prediction subsystem 102 is implementing fault response plans, the simulation scenario engineering file data can represent the mission scenario before the fault occurs. The system operation support environment 106 can then inject fault simulations into the multi-satellite twin digital models selected by the satellite state prediction and prediction subsystem 102, reproducing the fault scenario and conducting subsequent fault response plan analysis and verification.

[0041] The digital flight comparison subsystem 103 can be used to obtain multi-satellite telemetry data from a multi-satellite formation and update the model state of the multi-satellite twin digital model using a preset update strategy to perform flight simulation of the multi-satellite formation and generate flight simulation data. The flight simulation data is then correlated and compared with the multi-satellite formation's on-orbit telemetry data to generate flight comparison results. The flight comparison results can be used to diagnose anomalies in the multi-satellite formation or to calibrate the multi-satellite twin digital model.

[0042] Specifically, the digital flight comparison subsystem 103 can acquire multi-satellite telemetry data and, based on this data, update the model state of the multi-satellite twin digital model using a preset update strategy, generating flight simulation data in real time. Furthermore, the real-time flight simulation data can be parallel correlated with the satellite's on-orbit telemetry data, enabling real-time comparison of ground and space status, providing support for anomaly diagnosis and model correction for on-orbit satellites.

[0043] In some embodiments, the preset update strategy can be set based on the satellite's orbit type, system operating speed, or specific application requirements. Specifically, the preset update strategy can include one of the following strategies: an immediate update strategy, a timed update strategy, an entry-exit tracking and control area update strategy, and a maneuver update strategy.

[0044] The instant update strategy refers to updating upon receiving multi-satellite telemetry data with matching timing. The equal-time interval update strategy updates at equal intervals, assuming continuous access to multi-satellite telemetry data. The entry-exit tracking and control area update strategy updates once upon entering and exiting the tracking and control arc. The mobile update strategy updates once in response to an update instruction, i.e., manually updates based on user needs. In this way, embodiments of the present invention can provide a more accurate situation display for non-tracking and control arcs, better assisting ground operations in timely tracking of status and rapid fault diagnosis.

[0045] In some embodiments, as Figure 1 As shown, when the digital flight comparison subsystem 103 is used for in-orbit satellite anomaly diagnosis and model correction, the digital flight comparison subsystem 103 specifically includes: a flight data parsing and matching module 1031, a flight data comparison module 1032 and a flight data analysis module 1032.

[0046] Among them, the accompanying flight data analysis and matching module 1031 can be used to analyze the accompanying flight simulation data and the on-orbit telemetry data of the multi-satellite formation, perform spatiotemporal data matching and classification processing, and obtain matching data for subsequent accompanying flight data comparison and analysis.

[0047] The accompanying flight data comparison module 1032 can be used to perform a same-reference comparison on the matching data through error calculation and error statistics methods to generate a digital accompanying flight status comparison result.

[0048] The accompanying flight data analysis module 1033 can be used to determine abnormal feature results based on the digital accompanying flight status comparison results through a single parameter method or a multi-parameter correlation analysis method to generate an accompanying flight comparison result.

[0049] Specifically, the accompanying flight data analysis module 1033 can diagnose abnormal characteristics of the accompanying flight data and generate accompanying flight comparison results by adopting a single-parameter method with empirical formulas, 3sigma thresholds, etc. as the main mathematical and statistical methods, or by mining the correlation between parameters and constructing a multi-parameter correlation analysis method, so as to timely detect abnormalities in the satellite working status or warn of satellite digital model corrections.

[0050] In this embodiment of the present invention, the digital flight comparison subsystem 103 can promptly detect satellite status anomalies based on digital flight data comparison. This is unlike the difficulty of identifying, for example, localized damage to solar panels using empirical thresholding methods based solely on telemetry data. By comparing and analyzing flight simulation data with on-orbit satellite telemetry data, this embodiment of the present invention eliminates discrepancies caused by varying operating conditions, highlights anomalies, and improves the ability to identify satellite operating status anomalies.

[0051] The mission evaluation and analysis subsystem 104 can be used to verify the correctness of the flight mission execution process of the multi-satellite formation based on the satellite status simulation data and the accompanying flight simulation data, based on the preset flight program execution conditions, the preset flight program interpretation conditions and the preset mission constraints, and to evaluate and analyze the flight mission execution effect of the multi-satellite formation, and generate execution process verification results and execution effect analysis results.

[0052] In some embodiments, as Figure 1 When the mission evaluation and analysis subsystem 104 evaluates and analyzes the execution effect of the flight mission of the multi-satellite formation, the mission evaluation and analysis subsystem 104 may specifically include: an execution process interpretation module 1041 and an execution effect analysis module 1042.

[0053] The execution process interpretation module 1041 can be used to determine a process interpretation event table based on preset flight program execution conditions and preset flight program interpretation conditions. Then, based on the satellite status simulation data and the accompanying flight simulation data, the process interpretation event table is interpreted item by item to generate an execution process verification result.

[0054] The execution effect analysis module 1042 can be used to perform evaluation and analysis based on the satellite status simulation data and the accompanying flight simulation data through the effectiveness evaluation factor model to generate an execution effect analysis result.

[0055] In some embodiments, the performance evaluation factor models can include one or more of the following: an Earth-Moon shadow model, an energy balance model, a network link analysis model, a Sun-Moon geometry model, an orbital characteristics model, and an attitude characteristics model. Thus, the performance evaluation factor models can be used to effectively evaluate and analyze the performance of individual satellites and multi-satellite collaborative missions.

[0056] The integrated display subsystem 105 can be used to display one or more of the following in a preset display format: multi-satellite twin digital models, the process of satellite status simulation, the process of accompanying flight simulation, satellite status simulation data, accompanying flight simulation data, accompanying flight comparison results, execution process verification results, and execution effect analysis results.

[0057] Specifically, the integrated display subsystem 105 can utilize preset display formats, such as two-dimensional, three-dimensional, and graphical interfaces, to provide intuitive demonstrations of digital models, processes, and performance. This provides a means of visually perceiving spatial context, deeply understanding spatial motion relationships, and rapidly verifying satellite performance, providing a means of displaying macro-situations and various phases and scenarios.

[0058] In this embodiment of the present invention, the integrated display subsystem 105 can display the flight process, flight status, and space motion relationships of satellite status prediction and digital flight support. It can also display satellite status and mission effectiveness analysis results for digital flight support and mission assessment analysis. Preset display formats include, for example, two-dimensional display, three-dimensional display, and information panel display.

[0059] The system operation support environment 106 can be used to provide a support environment for the operation, system configuration and data interaction of the digital satellite twin model construction subsystem 101, the satellite status deduction and prediction subsystem 102, the digital flight comparison subsystem 103, the mission evaluation and analysis subsystem 104 and the integrated display subsystem 105.

[0060] Specifically, the system operation support environment 106 can be used to provide a unified modeling, control, and distributed simulation solution platform and environment to support system operation, mode switching, data interaction, resource management, etc. The system operation support environment 106 can implement functions such as distributed simulation, digital flight operation, mission scenario management, data access, and fault simulation injection.

[0061] In some embodiments, the system operation support environment 106 can implement data access functionality through a remote control and telemetry uplink and downlink data receiving and processing module. The remote control and telemetry uplink and downlink data receiving and processing module can receive uplink remote control data and generated downlink telemetry data for synchronous applications of in-orbit satellites distributed by external systems, and process them based on internal system usage and storage.

[0062] In some embodiments, the system operation support environment 106 can configure and manage scenarios through a scenario configuration module, thereby enabling mode switching. Specifically, the modes that the system operation support environment 106 can switch to include: scheduling the simulation mode operated by the satellite state deduction and prediction subsystem 102, scheduling the digital flight companion mode and state prediction mode jointly operated by the digital flight companion comparison subsystem 103 and the satellite state deduction and prediction subsystem 102.

[0063] For example, Figure 2 The operation mode flow chart of the digital accompanying flight system for multi-satellite formation networking flight mission provided by the embodiment of the present invention is as follows: Figure 2As shown, the system operation support environment 106 can implement mode switching through the scenario configuration module. Among them, the status prediction mode refers to the use of rapid prediction based on the current status of satellites in the multi-satellite formation under the premise of digital flight mode to quickly determine the subsequent status and expected tasks of satellites in the multi-satellite formation.

[0064] In one implementation, the state prediction mode can be divided into two modes, depending on specific application requirements: a state prediction mode with flight control tasks and a state prediction mode without flight control tasks. The state prediction mode with flight control tasks can be used to pre-verify key flight control tasks, verify the correctness and rationality of flight programs, instruction interfaces, and process execution, thereby improving the accuracy of multi-satellite formation mission execution. The state prediction mode without flight control tasks can predict the attitude, orbit, energy, measurement and control, Earth-Moon shadow, and spatial geometry of the multi-satellite formation for a preset period of time in the future, providing support for the safe and stable operation of the multi-satellite formation.

[0065] like Figure 2 As shown, in the digital companion flight mode and the status prediction mode, first, the system operation support environment 106 can perform the initial parameter configuration. Then, the multi-satellite twin digital model is iteratively updated according to the preset time step through the time controller. Exemplarily, the multi-satellite twin digital model includes: a digital model of satellite A, a digital model of satellite B, and a digital model of satellite C. At the same time, the multi-satellite twin digital model is also injected with the parameters to be updated through the telemetry ground-to-space interaction interface when the parameter update requirements are met. The parameters to be updated are the telemetry data of the multi-satellite formation from the real-time data storage. In the companion flight mode, the multi-satellite twin digital model can output the companion flight data to the digital companion flight comparison subsystem 103 and the mission evaluation and analysis subsystem 104.

[0066] In a state prediction mode without a flight control mission, the multi-satellite twin digital model can output first prediction data to the digital flight comparison subsystem 103 and the mission evaluation and analysis subsystem 104 based on first updated simulation scenario file data iterated at a preset time step (e.g., super real-time iteration). In a state prediction mode with a flight control mission, the multi-satellite twin digital model can output second prediction data to the digital flight comparison subsystem 103 and the mission evaluation and analysis subsystem 104 based on second updated simulation scenario file data iterated at a preset time step (e.g., super real-time iteration). The second updated simulation scenario file data can be data injected from a real-time data storage in response to a remote control command.

[0067] In the simulation deduction mode, the satellite status deduction and prediction subsystem 102 can inject data into the multi-satellite twin digital model according to the remote control command to simulate the sending and command plan injection of data. The multi-satellite twin digital model outputs deduction data, such as satellite status simulation data, to the digital companion flight comparison subsystem 103 and the mission evaluation and analysis subsystem 104.

[0068] Furthermore, the digital flight comparison subsystem 103 and the mission evaluation and analysis subsystem 104 can perform flight simulation based on the flight data, the first predicted data, the second predicted data, the deduced data, and the engineering parameter data output from the real-time data storage, generating flight comparison results. Furthermore, the system can verify the correctness of the multi-satellite formation's flight mission execution process and evaluate and analyze the performance of the multi-satellite formation's flight mission, generating execution process verification results and execution performance analysis results.

[0069] like Figure 2 As shown, illustratively, the digital flight comparison subsystem 103 and the mission evaluation and analysis subsystem 104 can realize scenario simulation, digital flight, flight comparison, flight mission verification, link performance analysis, energy analysis and comprehensive performance analysis, etc.

[0070] Finally, the flight companion comparison results, execution process verification results, and execution effect analysis results determined by the digital flight companion comparison subsystem 103 and the task evaluation and analysis subsystem 104 can be displayed in two-dimensional visualization through the comprehensive display subsystem 105.

[0071] In some embodiments, Figure 3 The information flow diagram of the digital accompanying flight mode provided by the embodiment of the present invention is as follows: Figure 3 As shown, in the digital flight mode, the telemetry data downlinked from the multi-satellite physical business system is used as the initial setting state to promote and dynamically update the model state of the multi-satellite twin digital model, dynamically respond to the uplink remote control command injection data, and maintain digital flight with synchronization of satellite and ground mission states. Based on this, the data flight comparison carried out by the digital flight comparison subsystem 103 can be carried out, and the performance evaluation can be evaluated using the mission evaluation and analysis subsystem 104. The process information flow and effect evaluation can be visualized in parallel in the integrated display subsystem 105. This operating mode mainly supports the collaborative evolution of digital models, providing strong technical support for the monitoring, prediction, collaborative optimization, on-orbit test simulation, fault diagnosis and tracing, and maintenance plan demonstration of the device's physical entity.

[0072] For example, Figure 3As shown, the multi-satellite entity service system can receive uplink data through the first uplink data parsing module and inject the uplink parsed data into the multi-satellite entity unit. The multi-satellite entity unit may include: satellite entity unit A, satellite entity unit B, and satellite entity unit C. The multi-satellite entity unit can operate in orbit and output downlink telemetry parsed data.

[0073] At the same time, the digital companion flight system 100 of the multi-satellite formation networking flight mission can receive uplink data through the second uplink data parsing module to realize model driving. The uplink parsing data is injected into the multi-satellite twin digital model. Among them, the multi-satellite twin digital model includes: a digital model of satellite A, a digital model of satellite B, and a digital model of satellite C. In addition, the multi-satellite twin digital model also receives downlink telemetry data from the multi-satellite physical unit to realize model driving. The multi-satellite twin digital model performs multi-satellite simulation deduction and visualization based on the uplink parsing data and downlink telemetry data, and outputs simulation data (for example: satellite status simulation data, companion flight simulation data). Furthermore, the digital companion flight comparison subsystem 103 and the mission evaluation and analysis subsystem 104 can be used to perform status comparison and analysis on the simulation data and downlink telemetry parsing data. Finally, the simulation data and downlink telemetry parsing data can be visualized for task parallelism through the comprehensive display subsystem 105.

[0074] In some embodiments, the task scenario management provided by the system operation support environment 106 may include functions such as configuring the initial state of the task scenario working conditions, digital model relationships, and working condition management. The resource management provided may include database and file system management. The fault simulation injection provided may include fault list configuration and fault interface protocol.

[0075] The digital flight support system for multi-satellite formation networked flight missions provided by the embodiments of the present invention can replicate onboard information, control, and functional flows through the construction of digital twin models of multiple satellites at the individual, subsystem, and system levels. This model interacts with semi-physical and engineering development to enhance the adequacy and coverage of satellite system testing and solution verification. The system features various simulation and digital flight support modes for different stages of mission development and operation. Before a mission, the satellite state prediction subsystem rapidly simulates the satellite flight process, state, and result data through ultra-real-time simulation. This controllable process facilitates the simulation, analysis, and verification of both normal and fault response plans. During on-orbit operations, the digital flight comparison subsystem synchronizes its flight operations with the physical entity, providing digital technical support for on-orbit operational status tracking and analysis, status prediction, risk prediction, and fault diagnosis. The mission assessment and analysis subsystem can perform mission assessment and analysis based on various application modes, improving the safety, stability, and efficiency of satellite operations both before and during missions.

[0076] The embodiment of the present invention also provides a digital accompanying flight method for a multi-satellite formation networking flight mission, which can be applied to Figure 1 The digital accompanying flight system for multi-satellite formation networking flight mission shown in the figure. Specifically, Figure 4 A flow chart of a digital accompanying flight method for a multi-satellite formation networking flight mission provided by an embodiment of the present invention is shown as follows: Figure 4 As shown, the method includes the following steps S101-S105:

[0077] S101. Construct a multi-satellite twin digital model based on the development and design data of the multi-satellite formation.

[0078] Among them, the multi-satellite twin digital model includes: the digital model corresponding to each satellite in the multi-satellite formation.

[0079] S102. Based on the simulation scenario engineering file data of the satellite flight mission scenario, a multi-satellite twin digital model is called to perform satellite state simulation of the multi-satellite formation and generate satellite state simulation data.

[0080] S103. Acquire multi-satellite telemetry data of a multi-satellite formation, update the model state of the multi-satellite twin digital model using a preset update strategy, perform a flight simulation of the multi-satellite formation, and generate flight simulation data; and correlate and compare the flight simulation data with the on-orbit telemetry data of the multi-satellite formation to generate a flight comparison result.

[0081] Among them, the companion flight comparison results can be used to diagnose abnormalities in multi-satellite formations or to calibrate multi-satellite twin digital models.

[0082] S104. Based on the satellite status simulation data and the accompanying flight simulation data, and based on the preset flight program execution conditions, the preset flight program interpretation conditions, and the preset mission constraints, the correctness of the flight mission execution process of the multi-satellite formation is verified, and the execution effect of the flight mission of the multi-satellite formation is evaluated and analyzed to generate the execution process verification results and the execution effect analysis results.

[0083] S105. Display one or more of the following in a preset display format: multi-satellite twin digital models, satellite status simulation process, accompanying flight simulation process, satellite status simulation data, accompanying flight simulation data, accompanying flight comparison results, execution process verification results, and execution effect analysis results.

[0084] Through the description of the above implementation methods, technical personnel in the relevant field can clearly understand that for the convenience and simplicity of description, only the division of the above-mentioned functional modules is used as an example. In actual applications, the above-mentioned functions can be assigned to different functional modules as needed, that is, the internal structure of the device can be divided into different functional modules to complete all or part of the functions described above.

[0085] In the description of the present invention, it should be understood that the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the number of the technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, "plurality" means at least two, for example, two, three, etc., unless otherwise specifically defined.

[0086] In the description of this specification, the reference terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and features of different embodiments or examples without contradiction.

[0087] Similar parts between the embodiments provided in this application can be referenced to each other. The specific implementation methods provided above are only a few examples under the overall concept of this application and do not constitute a limitation on the scope of protection of this application. For those skilled in the art, any other implementation methods expanded based on the scheme of this application without expending creative work shall fall within the scope of protection of this application.

Claims

1. A digital flight companion system for multi-satellite formation networking flight missions, characterized in that: include: Digital satellite twin model construction subsystem, satellite status deduction and prediction subsystem, digital flight comparison subsystem, mission evaluation and analysis subsystem, integrated display subsystem, and system operation support environment; The digital satellite twin model construction subsystem is used to construct a multi-satellite twin digital model based on the development and design data of the multi-satellite formation. The multi-satellite twin digital model includes: a digital model corresponding to each satellite in the multi-satellite formation; The satellite state deduction and prediction subsystem is used to call the multi-satellite twin digital model according to the simulation scenario engineering file data of the satellite flight mission scenario to perform satellite state simulation of the multi-satellite formation and generate satellite state simulation data; The digital flight comparison subsystem is configured to obtain multi-satellite telemetry data of the multi-satellite formation, update the model state of the multi-satellite twin digital model according to a preset update strategy, perform flight simulation of the multi-satellite formation, and generate flight simulation data; and associate and compare the flight simulation data with the on-orbit telemetry data of the multi-satellite formation to generate a flight comparison result, which is used to diagnose abnormalities of the multi-satellite formation or perform model correction on the multi-satellite twin digital model. The mission evaluation and analysis subsystem is configured to verify the correctness of the flight mission execution process of the multi-satellite formation based on the satellite status simulation data and the accompanying flight simulation data, based on preset flight program execution conditions, preset flight program interpretation conditions, and preset mission constraints, and to evaluate and analyze the execution effect of the flight mission of the multi-satellite formation, thereby generating an execution process verification result and an execution effect analysis result. The integrated display subsystem is configured to display one or more of the following in a preset display format: the multi-satellite twin digital model, the satellite state simulation process, the accompanying flight simulation process, the satellite state simulation data, the accompanying flight simulation data, the accompanying flight comparison result, the execution process verification result, and the execution effect analysis result; The system operation support environment is used to provide a support environment for the operation, system configuration and data interaction of the digital satellite twin model construction subsystem, the satellite status deduction and prediction subsystem, the digital flight comparison subsystem, the mission evaluation and analysis subsystem and the integrated display subsystem.

2. The system according to claim 1, wherein: The digital satellite twin model construction subsystem is also used to encapsulate the multi-satellite twin digital model and simulate the operation according to the multi-source heterogeneous model interface protocol provided by the system operation support environment.

3. The system according to claim 1 or 2, characterized in that The multi-satellite twin digital model has one or more of the following data interfaces: Initial parameter interface, input data interface, output data interface, remote control injection interface, telemetry injection interface, fault injection interface.

4. The system according to claim 1, wherein: The digital model corresponding to each satellite includes one or more of the following models: Comprehensive electronic model, energy model, measurement and control model, thruster model, actuator model, sensor model, mechanism model, carrier tube unit model, and computing unit model.

5. The system according to claim 1, wherein: The satellite state deduction and prediction subsystem is specifically used to: When the simulation scenario engineering file data is received from the mission scenario configuration, it is used for the deduction simulation of the mission scenario of the multi-satellite formation; when the simulation scenario engineering file data is received from the digital companion flight, it is used for the predicted state simulation of the multi-satellite formation.

6. The system according to claim 1, wherein: The digital accompanying flight comparison subsystem includes: an accompanying flight data parsing and matching module, an accompanying flight data comparison module and an accompanying flight data analysis module; The accompanying flight data parsing and matching module is used to parse the accompanying flight simulation data and the on-orbit telemetry data of the multi-satellite formation, perform spatiotemporal data matching and classification processing, and obtain matching data; The accompanying flight data comparison module is used to perform the same reference comparison on the matching data through error calculation and error statistics methods to generate a digital accompanying flight status comparison result; The accompanying flight data analysis module is used to determine the abnormal feature results based on the digital accompanying flight status comparison results through a single parameter method or a multi-parameter correlation analysis method to generate the accompanying flight comparison results.

7. The system according to claim 1, wherein: The preset update strategy includes one of the following strategies: immediate update strategy, equal time interval update strategy, entry and exit measurement and control area update strategy, and mobile update strategy; Among them, the update strategy for entering and exiting the measurement and control area is based on the measurement and control arc, and is updated once when entering and exiting the measurement and control arc; the maneuver update strategy is updated once in response to an update instruction.

8. The system according to claim 1, wherein: The task evaluation and analysis subsystem includes: an execution process interpretation module and an execution effect analysis module; The execution process interpretation module is configured to determine a process interpretation event table based on the preset flight program execution conditions and the preset flight program interpretation conditions; and to generate the execution process verification result by interpreting each item in the process interpretation event table based on the satellite status simulation data and the accompanying flight simulation data. The execution effect analysis module is used to perform evaluation and analysis based on the satellite status simulation data and the accompanying flight simulation data through the effectiveness evaluation factor model to generate the execution effect analysis result.

9. The system according to claim 8, characterized in that The effectiveness evaluation factor model includes one or more of the following models: Earth-Moon shadow model, energy balance model, network link analysis model, Sun-Moon geometry model, orbital characteristics model, attitude characteristics model.

10. A digital accompanying flight method for a multi-satellite formation networking flight mission, characterized in that: include: Constructing a multi-satellite twin digital model based on the development and design data of the multi-satellite formation, wherein the multi-satellite twin digital model includes: a digital model corresponding to each satellite in the multi-satellite formation; calling the multi-satellite twin digital model according to the simulation scenario engineering file data of the satellite flight mission scenario to perform satellite state simulation of the multi-satellite formation and generate satellite state simulation data; Acquiring multi-satellite telemetry data of the multi-satellite formation, updating a model state of the multi-satellite twin digital model according to a preset update strategy, so as to perform a flight simulation of the multi-satellite formation and generate flight simulation data; and correlating and comparing the flight simulation data with the on-orbit telemetry data of the multi-satellite formation to generate a flight comparison result, wherein the flight comparison result is used to perform anomaly diagnosis on the multi-satellite formation or to perform model correction on the multi-satellite twin digital model; According to the satellite state simulation data and the accompanying flight simulation data, based on preset flight program execution conditions, preset flight program interpretation conditions, and preset mission constraints, the correctness of the flight mission execution process of the multi-satellite formation is verified, and the execution effect of the flight mission of the multi-satellite formation is evaluated and analyzed to generate an execution process verification result and an execution effect analysis result; Display one or more of the following in a preset display format: the multi-satellite twin digital model, the satellite state simulation process, the accompanying flight simulation process, the satellite state simulation data, the accompanying flight simulation data, the accompanying flight comparison result, the execution process verification result, and the execution effect analysis result.

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