Digital twinning method and device of satellite optical system

Abstract

The embodiment of the invention provides a digital twinning method and device for a satellite optical system, and the method comprises the steps that a telemetering instruction is received by an interface layer in the satellite optical system, a virtual electric control box is a core logic layer in the satellite optical system, and a virtual camera is a unit model layer in the satellite optical system. The interface layer and the core logic layer receive the telemetering instruction and respond to the telemetering instruction with the unit model layer, so that a simulation result responding to the telemetering instruction in the satellite optical system is obtained. By adopting the layered architecture, the interface layer focuses on data interaction, the core logic layer is responsible for instruction processing and logic operation, and the unit model layer focuses on imaging simulation, so that the stability and reliability of the system are enhanced, and a stable and reliable virtual platform support is provided for testing and verification of the satellite optical system.

Description

Technical Field

[0001] This invention relates to the field of optical imaging technology, and in particular to a digital twin method and apparatus for a satellite optical system. Background Technology

[0002] The satellite involved in this invention is an Earth observation satellite capable of detecting visible light signals, and its core payload is a low-light imaging system.

[0003] Digital twins are a technological framework that maps real-world physical entities, systems, or processes to virtual space using digital technology. Through data acquisition, modeling, simulation, and analysis, it constructs a highly accurate "digital mirror" of the physical object in a virtual environment. This dynamic simulation model reflects the real-time state, behavior, and performance of the physical system, enabling full lifecycle monitoring, prediction, and optimization of the physical object. Current research on digital twin technology in the application of low-light optical payloads is relatively limited. Therefore, there is an urgent need to provide a digital twin method for optical payload applications, specifically a digital twin method for satellite optical systems. Summary of the Invention

[0004] The purpose of this invention is to provide a digital twin method and apparatus for satellite optical systems, thereby providing a stable and reliable virtual platform for the testing and verification of satellite optical systems. The specific technical solution is as follows:

[0005] In a first aspect, embodiments of the present invention provide a digital twin method for a satellite optical system, the method comprising:

[0006] A virtual control box and a virtual camera are generated, wherein the virtual control box is used to simulate the physical control box in the satellite optical system, and the virtual camera is used to simulate the physical camera in the satellite optical system;

[0007] In response to telemetry commands for the satellite optical system, the virtual control box and the virtual camera are driven to respond to the telemetry commands;

[0008] The results of the responses from the virtual control box and the virtual camera are obtained and used as the simulation results of the satellite optical system's response to the telemetry command.

[0009] In one possible implementation, the method further includes:

[0010] In the process of driving the virtual camera to respond to the telemetry command, abnormal operating conditions are introduced into the process by using a time synchronization mechanism and / or fault injection. The abnormal operating conditions include one or more of the following: timing deviation, component failure, and communication interruption.

[0011] In one possible implementation, driving the virtual control box and the virtual camera to respond to the telemetry command in response to the telemetry command for the satellite optical system includes:

[0012] The telemetry control interface of the satellite optical system is shown.

[0013] In response to a telemetry command input to the telemetry control interface, the virtual electrical control box and the virtual camera are driven to respond to the telemetry command.

[0014] In one possible implementation, the virtual camera includes a first imaging unit, a second imaging unit, a focusing mechanism, and a calibration mechanism;

[0015] The first imaging unit is used to simulate the physical camera acquiring first image data;

[0016] The second imaging unit is used to simulate the physical camera acquiring second image data;

[0017] The focusing mechanism is used to simulate the focusing process of the physical camera;

[0018] The calibration mechanism is used to simulate the calibration process of the physical camera.

[0019] In one possible implementation, the first imaging unit and the second imaging unit maintain FPGA power state, CMOS power state and imaging state.

[0020] The first imaging unit simulates the physical camera acquiring second image data, including:

[0021] The first imaging unit simulates the physical camera in the target state to acquire first image data;

[0022] The second imaging unit simulates the physical camera acquiring second image data, including:

[0023] The second imaging unit simulates the physical camera acquiring second image data under the target state;

[0024] The target state is that the FPGA power supply of the physical camera is in the FPGA power supply state, the CMOS power supply is in the CMOS power supply state, and the physical camera is in the imaging state.

[0025] In one possible implementation, the telemetry control interface is pre-subscribed to a telemetry channel, and the method further includes:

[0026] After obtaining the response results from the virtual electrical control box and the virtual camera, the obtained results are published to the telemetry channel so that the telemetry control interface can obtain and display the results.

[0027] In one possible implementation, driving the virtual control box and the virtual camera to respond to the telemetry command in response to the telemetry command for the satellite optical system includes:

[0028] In response to telemetry commands for the satellite optical system, the virtual control box is driven to parse the telemetry commands to obtain execution commands for the virtual control box and the virtual camera;

[0029] The execution instructions are written into the virtual electrical control box and the virtual camera respectively, so as to drive the virtual electrical control box and the virtual camera to respond to the telemetry instructions.

[0030] Secondly, embodiments of the present invention provide a digital twin device for a satellite optical system, the device comprising:

[0031] A generation module is used to generate a virtual electrical control box and a virtual camera. The virtual electrical control box is used to simulate the physical electrical control box in the satellite optical system, and the virtual camera is used to simulate the physical camera in the satellite optical system.

[0032] A drive module is used to drive the virtual control box and the virtual camera to respond to telemetry commands for the satellite optical system.

[0033] The acquisition module is used to acquire the response results of the virtual electrical control box and the virtual camera, as the simulation result of the satellite optical system responding to the telemetry command.

[0034] In one possible implementation, the device further includes:

[0035] The injection module is used to introduce abnormal operating conditions into the process of driving the virtual camera to respond to the telemetry command by using a time synchronization mechanism and / or fault injection. The abnormal operating conditions include one or more of the following: timing deviation, component failure, and communication interruption.

[0036] In one possible implementation, the driving module includes:

[0037] The first driving submodule is used to display the telemetry control interface of the satellite optical system;

[0038] The second driving submodule is used to drive the virtual electrical control box and the virtual camera to respond to the telemetry command input to the telemetry control interface.

[0039] In one possible implementation, the virtual camera includes a first imaging unit, a second imaging unit, a focusing mechanism, and a calibration mechanism;

[0040] The first imaging unit is used to simulate the physical camera acquiring first image data;

[0041] The second imaging unit is used to simulate the physical camera acquiring second image data;

[0042] The focusing mechanism is used to simulate the focusing process of the physical camera;

[0043] The calibration mechanism is used to simulate the calibration process of the physical camera.

[0044] In one possible implementation, the first imaging unit and the second imaging unit maintain FPGA power state, CMOS power state and imaging state.

[0045] The first imaging unit simulates the physical camera acquiring second image data, including:

[0046] The first imaging unit simulates the physical camera in the target state to acquire first image data;

[0047] The second imaging unit simulates the physical camera acquiring second image data, including:

[0048] The second imaging unit simulates the physical camera acquiring second image data under the target state;

[0049] The target state is that the FPGA power supply of the physical camera is in the FPGA power supply state, the CMOS power supply is in the CMOS power supply state, and the physical camera is in the imaging state.

[0050] In one possible implementation, the telemetry control interface is pre-subscribed to a telemetry channel, and the device further includes:

[0051] The display module is used to publish the obtained results to the telemetry channel after obtaining the response results from the virtual electrical control box and the virtual camera, so that the telemetry control interface can obtain and display the results.

[0052] In one possible implementation, the driving module includes:

[0053] The third driving submodule is used to respond to telemetry commands for the satellite optical system, drive the virtual control box to parse the telemetry commands, and obtain execution commands for the virtual control box and the virtual camera;

[0054] The fourth driving submodule is used to write the execution instructions into the virtual electrical control box and the virtual camera respectively, so as to drive the virtual electrical control box and the virtual camera to respond to the telemetry instructions.

[0055] Thirdly, embodiments of the present invention provide an electronic device, including:

[0056] Memory, used to store computer programs;

[0057] The processor, when executing a program stored in memory, implements any of the gas enhancement methods described above.

[0058] Fourthly, embodiments of the present invention provide a computer-readable storage medium storing a computer program, which, when executed by a processor, implements the digital twin method for any of the satellite optical systems described above.

[0059] Fifthly, embodiments of the present invention also provide a computer program product containing instructions that, when run on a computer, cause the computer to execute the digital twin method for any of the satellite optical systems described above.

[0060] Beneficial effects of the embodiments of the present invention:

[0061] This invention provides a digital twin method and apparatus for a satellite optical system. The satellite optical system adopts a layered software architecture. Receiving telemetry commands is the step executed by the interface layer in the satellite optical system. A virtual control box simulates the physical control box in the satellite optical system, representing the core logic layer of the virtual control box. A virtual camera simulates the physical camera in the satellite optical system, representing the unit model layer. The interface layer receives telemetry commands, and the core logic layer and unit model layer respond to the telemetry commands, thereby obtaining the simulation results of the satellite optical system responding to the telemetry commands. This layered architecture ensures that each layer has a clear and singular scope of responsibility. The interface layer focuses on data interaction, the core logic layer is responsible for command processing and logical operations, and the unit model layer focuses on imaging simulation. This allows developers to conduct targeted testing for each layer, promptly identify and resolve problems, and improve testing efficiency. In terms of maintenance, when a system failure occurs, the level at which the problem occurs can be quickly located, enabling targeted repairs and optimizations, effectively reducing subsequent maintenance costs. Moreover, this layered architecture has good scalability. If new functions or components need to be added in the future, they can be extended and integrated at the corresponding layer without large-scale modifications to the entire system. This enhances the stability and reliability of the system and provides a stable and reliable virtual platform for the testing and verification of satellite optical systems.

[0062] Of course, implementing any product or method of the present invention does not necessarily require achieving all of the advantages described above at the same time. Attached Figure Description

[0063] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other embodiments can be obtained based on these drawings.

[0064] Figure 1 This is a schematic diagram of a first process for a digital twin method for a satellite optical system provided in an embodiment of the present invention;

[0065] Figure 2 This is a first schematic diagram of the software architecture of a satellite optical system provided in an embodiment of the present invention;

[0066] Figure 3 A schematic diagram of the composition of a satellite optical system provided in an embodiment of the present invention;

[0067] Figure 4 This is a second flowchart illustrating the digital twin method for a satellite optical system provided in an embodiment of the present invention.

[0068] Figure 5 This is a schematic diagram of a service timing diagram provided in an embodiment of the present invention;

[0069] Figure 6 A schematic diagram of the third process for a digital twin method of a satellite optical system provided in an embodiment of the present invention;

[0070] Figure 7 This is a second schematic diagram of the satellite optical system software architecture provided in an embodiment of the present invention;

[0071] Figure 8 A schematic diagram of the structure of a digital twin device for a satellite optical system provided in an embodiment of the present invention;

[0072] Figure 9 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present invention. Detailed Implementation

[0073] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art based on the present invention are within the scope of protection of the present invention.

[0074] This invention provides a digital twin method for a satellite optical system, see [link to relevant documentation]. Figure 1 , Figure 1 A first flowchart illustrating a digital twin method for a satellite optical system provided in an embodiment of the present invention includes:

[0075] S101, generate a virtual electrical control box and a virtual camera. The virtual electrical control box is used to simulate the physical electrical control box in the satellite optical system, and the virtual camera is used to simulate the physical camera in the satellite optical system.

[0076] S102, in response to telemetry commands for the satellite optical system, drives the virtual control box and virtual camera to respond to the telemetry commands;

[0077] S103, obtain the response results of the virtual control box and virtual camera, as the simulation results of the satellite optical system responding to telemetry commands.

[0078] Applying the above embodiments, the satellite optical system adopts a layered software architecture. Receiving telemetry commands is the step executed by the interface layer in the satellite optical system. The virtual control box simulates the physical control box in the satellite optical system, representing the core logic layer. The virtual camera simulates the physical camera in the satellite optical system, representing the unit model layer. The interface layer receives telemetry commands, and the core logic layer and unit model layer respond to these commands, thus obtaining the simulation results of the satellite optical system in response to the telemetry commands. This layered architecture ensures that each layer has a clear and singular scope of responsibility. The interface layer focuses on data interaction, the core logic layer handles command processing and logical operations, and the unit model layer focuses on imaging simulation. This allows developers to conduct targeted testing at each layer, promptly identify and resolve problems, and improve testing efficiency. In terms of maintenance, when a system failure occurs, the problematic layer can be quickly located for targeted repair and optimization, effectively reducing subsequent maintenance costs. Moreover, this layered architecture has good scalability. If new functions or components need to be added in the future, they can be extended and integrated at the corresponding layer without large-scale modifications to the entire system. This enhances the stability and reliability of the system and provides a stable and reliable virtual platform for the testing and verification of satellite optical systems.

[0079] To more clearly illustrate the digital twin method for satellite optical systems provided in this embodiment of the invention, the software architecture of the satellite optical system will be described first. (See [link to relevant documentation]). Figure 2 , Figure 2 This is a first schematic diagram of the software architecture of a satellite optical system provided in an embodiment of the present invention. The satellite optical system includes an external simulation environment and a digital twin model. The external simulation environment includes a simulation main control platform and a satellite platform model. The digital twin model includes an interface layer, a core logic layer, and a unit model layer. The interface layer includes an imaging subsystem, which is in the form of a Dynamic Link Library (DLL). The core logic layer includes a virtual electronic control box and a line frequency calculator. The unit model layer includes a first imaging unit and a second imaging unit (the first and second imaging units will be described below and will not be repeated here).

[0080] Steps S101-S103 described above can be executed by the remote control module (TeleCtrl) in the aforementioned simulation master control platform, or by other modules or structures with execution capabilities in the satellite optical system. For ease of description, this paper uses the execution of steps S101-S103 by the remote control module as an example to illustrate the digital twin method for the satellite optical system provided in this embodiment of the invention. The principle is the same for cases where the execution subject is a processor; the only difference is that the remote control module in the following embodiments is replaced by other modules or structures with execution capabilities, which will not be repeated here.

[0081] The following will explain the aforementioned steps S101-S103:

[0082] In step S101, using computer software or specific simulation tools, the remote control module creates a virtual electrical control box in a virtual environment that functions similarly to the physical electrical control box actually existing in the satellite optical system. This virtual electrical control box possesses similar electrical control logic, interfaces, and operational characteristics to the real electrical control box at the software level, and can simulate various behaviors and functions of the real electrical control box in the satellite optical system, such as receiving and processing different signals and issuing corresponding control commands.

[0083] Similarly, using computer simulation technology, a model of the actual physical camera in a satellite optical system is constructed in virtual space. This model can include cameras such as infrared cameras and multispectral cameras. This virtual camera has similar optical imaging characteristics, parameter settings, and image acquisition functions to a real camera. It can simulate the imaging process of a real camera on a target scene during satellite operation in a virtual environment, including light reception and image generation.

[0084] By creating virtual control boxes and virtual cameras, it becomes possible to study and evaluate the performance, functionality, and response characteristics of satellite optical systems without the need for actual physical equipment.

[0085] In step S102, the telemetry command is a command input to the satellite optical system. It can be input by the user in real time according to the needs, or it can be preset for the satellite optical system. No specific limitation is made here.

[0086] This telemetry command is used to acquire various status information and parameter data of the satellite optical system, or to remotely control and operate the satellite optical system, including operation control commands (OC commands), telemetry request commands, remote control commands, and time synchronization commands. For example, a telemetry command may request the acquisition of the current imaging parameters of the virtual camera, the power status of the virtual control box, or to adjust the imaging mode of the virtual camera.

[0087] It is understood that the digital twin method for satellite optical systems provided in this application aims to simulate the target scene imaging process of a real satellite camera during its entire on-orbit operation in a virtual simulation environment, achieving a 1:1 digital mapping and simulation of the imaging behavior of the real satellite optical system. Based on this, when telemetry commands are applied to remotely control and operate the digital twin satellite optical system, the command execution logic should conform to the on-orbit operation patterns of the real satellite. It should control the digital twin system to follow the predetermined trajectory of the real satellite system, simulating the shooting angle, attitude orientation, field of view, and imaging sequence of the real satellite system in actual image acquisition tasks. This ensures that the spatial position of the shooting angle, attitude deflection angle, and relative azimuth of the target scene in the imaging simulation process are consistent with the on-orbit operation state of the real satellite system. This guarantees the authenticity, validity, and reference value of the digital twin imaging results, enabling the prediction of the performance of the real satellite optical system under different conditions, thereby achieving more accurate design and better performance.

[0088] Upon receiving a telemetry command, the remote control module will drive the virtual electrical control box and virtual camera to perform corresponding actions based on the specific content of the telemetry command and through appropriate software algorithms and logic.

[0089] Specifically, the virtual control box adjusts its internal state, processes signals, and issues corresponding control signals according to the instructions; the virtual camera changes its imaging parameters and operating mode according to the instructions, simulating the actual response process of real equipment when receiving similar instructions. For example, if a telemetry instruction requires adjusting the exposure time of the virtual camera, the virtual camera will correspondingly change its exposure time parameters in the virtual environment and generate simulated image data that conforms to the new parameters.

[0090] In step S103, after the virtual electrical control box and the virtual camera complete their response to the telemetry command, the remote control module obtains the results of the response from the virtual electrical control box and the virtual camera.

[0091] Specifically, for a virtual control box, the response results may include its internal state change data, control signals issued, etc.; for a virtual camera, the response results may include its generated simulated image data and related imaging parameter change information, etc.

[0092] The remote control module organizes and analyzes the acquired data and information, using it as a simulation result of the satellite optical system's response to telemetry commands.

[0093] The simulation results can be used to evaluate the performance, functionality, and potential problems of a satellite optical system when receiving different telemetry commands, providing a reference for the design optimization, testing, and actual operation of the satellite optical system. For example, by analyzing the quality of simulated images generated by the virtual camera, the imaging effect of the camera under different parameter settings can be evaluated, thereby allowing for the adjustment and optimization of the actual parameters of the camera in the satellite optical system.

[0094] As mentioned above, in one possible embodiment, the virtual camera may include cameras such as infrared cameras and multispectral cameras.

[0095] In another possible embodiment, the virtual camera includes a first imaging unit, a second imaging unit, a focusing mechanism, and a calibration mechanism. The first imaging unit and the second imaging unit are two different imaging units. Specifically, the first imaging unit is a visible light imaging unit and the second imaging unit is a low-light imaging unit, or the first imaging unit is a low-light imaging unit and the second imaging unit is a visible light imaging unit.

[0096] Taking the first imaging unit as a visible light imaging unit and the second imaging unit as a low-light imaging unit as an example, see [link to relevant documentation]. Figure 3 , Figure 3 This is a schematic diagram illustrating the composition of a satellite optical system provided in an embodiment of the present invention. The satellite optical system includes a satellite platform subsystem and a camera payload subsystem. The satellite platform subsystem is the aforementioned external simulation environment, which includes the aforementioned simulation control platform and a satellite platform model. Figure 3 The satellite platform is the satellite platform subsystem, and the camera payload is the camera payload subsystem.

[0097] The visible light imaging unit is used to simulate a physical camera to acquire visible light image data;

[0098] Low-light imaging unit, used to simulate a physical camera to acquire low-light image data;

[0099] A focusing mechanism used to simulate the focusing process of a physical camera;

[0100] A calibration mechanism used to simulate the calibration process of a physical camera.

[0101] Figure 3 The image data in the image is the result of the response of the first imaging unit and the second imaging unit. The visible light image data is the first image data, and the low-light image data is the second image data. Figure 3 The interaction between the satellite platform and the camera payload based on telemetry commands, as well as the interaction between the virtual control box and the first imaging unit, the line frequency calculator, the second imaging unit, the focusing mechanism, and the calibration mechanism based on telemetry commands, constitute the response of the virtual control box and the virtual camera to telemetry commands.

[0102] Figure 3 The LineFreqCalc module is responsible for calculating the precise line frequencies required by the virtual camera based on the input satellite attitude, orbital parameters, and line-of-sight pointing, using a lookup table method. Its data source loads multidimensional lookup table data from a specified Excel file during the simInit phase and stores it in m_conditionMap, ensuring the accuracy and real-time performance of the line frequency calculation results. The simInit phase is the initialization phase, the Excel file is a spreadsheet file, and m_conditionMap is a data storage table.

[0103] Using the above embodiments, the virtual camera is equipped with a first imaging unit and a second imaging unit, which can respectively simulate the acquisition of first and second image data by a physical camera, simulating the imaging effect of a physical camera. This provides more realistic data for simulation research in various scenarios, improving the realism and comprehensiveness of the simulation. Through the setting of focusing and calibration mechanisms, the virtual camera not only simulates the physical camera in terms of imaging data but also completely simulates the focusing and calibration process of a physical camera. The simulation of the focusing process ensures that the virtual camera can adjust its focus like a physical camera to obtain a clear image under different distances and scenarios; the simulation of the calibration process ensures the accuracy and consistency of imaging, enabling the virtual camera to operate reliably like a real physical camera in various application scenarios, better meeting practical application needs.

[0104] To further enhance the realism and comprehensiveness of the simulation, the aforementioned first and second imaging units maintain FPGA power states, CMOS power states, and imaging states. Based on this, when the first imaging unit simulates a physical camera acquiring second image data, specifically, the first imaging unit simulates a physical camera in the target state acquiring first image data. Similarly, when the second imaging unit simulates a physical camera acquiring second image data, specifically, the second imaging unit simulates a physical camera in the target state acquiring second image data.

[0105] The target state is that the FPGA power supply of the physical camera is in FPGA power supply state, the CMOS power supply is in CMOS power supply state, and the physical camera is in imaging state.

[0106] The FPGA (Field Programmable Gate Array) power status reflects the relevant parameters for powering the FPGA chip, such as whether the voltage is stable and whether the power supply is normal. This is related to the normal operation of the FPGA and the image processing functions implemented based on the FPGA. The CMOS power status reflects the power supply status of the CMOS image sensor. The CMOS sensor is one of the core components of camera imaging, and its power status affects the sensor's light sensitivity, noise level, etc. The imaging status covers information such as what imaging mode the camera is currently in and whether an imaging operation is in progress.

[0107] Specifically, the `write422` method uses the built-in instruction parsing mapping table (`m_analyzerMap`) to process internal instructions from the virtual control box, dynamically changing its own state based on the instruction content. The `read422` method generates telemetry data packets conforming to the protocol format based on the current state, for the upper layer to read. When entering imaging mode, the camera starts an independent thread, combines the current line frequency and imaging parameters, calls utility functions in the data processing tool to generate simulated image data, and pushes it into a circular queue for use in subsequent image processing flows.

[0108] By applying the above embodiments, the FPGA power state, CMOS power state, and imaging state are maintained in the first and second imaging units, allowing the virtual camera to simulate the physical camera down to the camera's critical internal operating states. This refined simulation method can more realistically reflect the working characteristics of the physical camera under different states, such as imaging noise and color deviation that may occur under different power states, as well as the adaptability to different scenes under different imaging states. This provides a realistic simulation environment for camera performance evaluation and algorithm testing, further enhancing the realism and comprehensiveness of the simulation.

[0109] To more realistically simulate the complex environment of physical cameras in real-world applications, abnormal operating conditions can be introduced into the process of driving the virtual camera to respond to telemetry commands using time synchronization mechanisms and fault injection. These abnormal operating conditions include one or more of the following: timing deviations, component failures, and communication interruptions.

[0110] Time synchronization mechanisms in satellite optical systems enable various components or modules to operate according to a unified time standard. However, introducing abnormal operating conditions through the time synchronization mechanism disrupts the originally precise time synchronization, causing inconsistencies between different components. For example, in a virtual camera, the image acquisition module and data processing module should ideally work together in a strict time sequence. Introducing an anomaly through the time synchronization mechanism might cause the image acquisition module to acquire an image, but the data processing module to fail to begin processing it within the expected time, resulting in a timing deviation and affecting the normal operation of the entire satellite optical system.

[0111] Fault injection is a method of actively introducing faults into a satellite optical system. By simulating various possible fault scenarios, it tests the fault tolerance and recovery capabilities of the satellite optical system in the event of a fault. In the process of driving a virtual camera to respond to telemetry commands, fault injection can be performed on different components of the virtual camera or on communication links. For example, a fault can be injected into a critical component of the virtual camera (such as a sensor or memory) to cause it to malfunction; or a fault can be injected into the communication link to simulate a communication interruption.

[0112] Timing deviation refers to an error in the timing relationship between various components or operations of the satellite optical system, resulting in execution not following the predetermined time sequence. Component failure refers to the malfunction of a component in the virtual camera (such as a sensor, processor, or memory) due to fault injection or other reasons. Component failure may prevent the virtual camera from performing certain specific functions; for example, sensor failure may prevent the acquisition of image data, and processor failure may prevent the processing of acquired data. Communication interruption refers to a failure in the communication link between the virtual camera and external devices (such as control terminals or data storage devices), resulting in the inability to transmit data normally. Communication interruption may prevent the virtual camera from receiving telemetry commands or transmitting acquired data, affecting the overall coordination and data interaction of the satellite optical system.

[0113] Applying the above embodiments, in real-world applications, physical cameras operate in complex and ever-changing environments, potentially encountering various anomalies. By introducing abnormal operating conditions such as timing deviations, component failures, and communication interruptions, these complex environments can be simulated more realistically, comprehensively testing the reliability and stability of the satellite optical system under different abnormal conditions. The abnormal operating conditions cover a variety of types, encompassing all possible failure scenarios that a virtual camera might encounter. The timing deviations introduced by the time synchronization mechanism can test the satellite optical system's ability to handle time errors; component failures caused by fault injection can assess the system's ability to handle critical component failures; and communication interruption simulations can verify the system's ability to handle communication failures. This comprehensive testing allows for a more realistic simulation of the satellite optical system's handling capabilities under various failure conditions, improving the realism and comprehensiveness of the simulation.

[0114] As mentioned earlier, telemetry commands are input to the satellite optical system. They can be input by the user in real time according to needs, or they can be pre-set for the satellite optical system.

[0115] When telemetry commands are input by the user in real time based on demand, in one possible embodiment, the user can input telemetry commands through a telemetry control interface. For details, see [link to relevant documentation]. Figure 4 , Figure 4A second flowchart illustrating the digital twin method for a satellite optical system provided in this embodiment of the invention includes:

[0116] S101 generates a virtual electrical control box and a virtual camera. The virtual electrical control box is used to simulate the physical electrical control box in the satellite optical system, and the virtual camera is used to simulate the physical camera in the satellite optical system.

[0117] S1021 shows the telemetry control interface of the satellite optical system.

[0118] S1022, in response to telemetry commands input to the telemetry control interface, drives the virtual electrical control box and virtual camera to respond to the telemetry commands.

[0119] S103, obtain the response results of the virtual control box and virtual camera, as the simulation results of the satellite optical system responding to telemetry commands.

[0120] Steps S1021 and S1022 are detailed steps of the aforementioned step S102. Steps S101 and S103 have been explained in the preceding text and will not be repeated here.

[0121] In steps S1021 and S1022, the telemetry control interface of the satellite optical system, also known as the GUI (Graphical User Interface), is the graphical interface in the aforementioned satellite platform model. The user inputs telemetry commands into the displayed graphical interface to drive the virtual control box and virtual camera to respond to the telemetry commands.

[0122] For details, see Figure 5 , Figure 5 This is a schematic diagram of the service timing diagram provided in an embodiment of the present invention. Taking the telemetry command as the "start imaging" command as an example, the user can input the "start imaging" command by clicking the command button in the telemetry control interface. After the telemetry control interface encapsulates the configuration parameters, it transmits the command to the remote control module through the send_cmd_to_power_control_box() interface. Figure 5 (Not shown in the image), so that the remote control module calls the writeRS422() interface of the imaging subsystem to inject commands in the RS422 protocol format, realizing standardized communication with the digital twin model, and driving the virtual power control box and virtual camera to respond to the commands. The send_cmd_to_power_control_box() interface is used to send commands to the virtual power control box and synchronously obtain the execution results or status.

[0123] The following section explains how to drive the virtual control box and virtual camera to respond to this command. (See also...) Figure 6 , Figure 6 A third flowchart illustrating the digital twin method for a satellite optical system provided in this embodiment of the invention includes:

[0124] S101 generates a virtual electrical control box and a virtual camera. The virtual electrical control box is used to simulate the physical electrical control box in the satellite optical system, and the virtual camera is used to simulate the physical camera in the satellite optical system.

[0125] S1023, in response to telemetry commands for the satellite optical system, drives the virtual control box to parse the telemetry commands and obtain execution commands for the virtual control box and the virtual camera.

[0126] S1024, write the execution instructions to the virtual control box and the virtual camera respectively, so as to drive the virtual control box and the virtual camera to respond to the telemetry instructions.

[0127] S103, obtain the response results of the virtual control box and virtual camera, as the simulation results of the satellite optical system responding to telemetry commands.

[0128] Steps S1023 and S1024 are detailed steps of the aforementioned step S102. Steps S101 and S103 have been explained in the preceding text and will not be repeated here.

[0129] In steps S1023 and S1024, the aforementioned method still applies. Figure 5 As shown, after calling the `writeRS422()` interface of the imaging subsystem to inject commands in simulated RS422 protocol format, the imaging subsystem, acting as the interface layer, receives and parses the RS422 data. It then forwards the original commands to the virtual control box in the core logic layer via the `send_cmd()` method. The remote control module drives the virtual control box to parse the commands, obtaining execution instructions for both the virtual control box and the virtual camera. Figure 5 Internal commands, such as sensor enable and exposure settings, are generated within the virtual control box. Specifically, the virtual control box calls a command generator to parse satellite commands and generate internal commands. These internal commands are then sent to the target virtual camera via the write421() interface. The virtual camera parses the internal commands, changes its state, and starts the imaging thread.

[0130] Applying the above embodiments, when responding to telemetry commands, the virtual control box is first driven to parse them. This can transform complex telemetry commands that may contain multiple types of information into specific execution commands for the virtual control box and the virtual camera. Through the parsing of the virtual control box, commands corresponding to different devices can be parsed out, and the parsed execution commands are written to the virtual control box and the virtual camera respectively. This avoids errors caused by command confusion, ensures that each device receives accurate commands that match its own function, and improves the accuracy of system response.

[0131] Based on the aforementioned telemetry commands input by the user through the telemetry control interface, after obtaining the response results from the virtual electrical control box and the virtual camera, the telemetry control interface can also display the response results. Specifically, the telemetry control interface has pre-subscribed to a telemetry channel. After obtaining the response results from the virtual electrical control box and the virtual camera, the remote control module publishes the obtained results to the telemetry channel so that the telemetry control interface can obtain and display the results.

[0132] This subscription relationship is typically implemented based on specific communication protocols and messaging mechanisms to ensure that the telemetry control interface can receive information from the telemetry channel in a timely and accurate manner. After the virtual control box and virtual camera respond to telemetry commands, they generate corresponding response results. These results include key data such as device status information (e.g., whether the virtual camera has successfully adjusted its shooting parameters, whether the power supply status of the virtual control box is normal, etc.) and operation execution status (whether the command was successfully executed, whether any errors occurred during execution, etc.). After obtaining these results, the remote control module publishes them to the aforementioned telemetry channel according to pre-set rules and communication protocols, enabling the telemetry control interface to access them. Once the results are obtained, the telemetry control interface presents them to the user in an intuitive and easy-to-understand manner, according to a pre-designed display method. For example, it may display the changes in various parameters of the virtual camera in the form of charts, or inform the user of the operating status of the virtual control box through text prompts, allowing the user to quickly understand the system's operating status.

[0133] By applying the above embodiments, the telemetry control interface can quickly acquire and display the response results of the virtual control box and virtual camera by promptly publishing them to the telemetry channel. This allows operators to monitor the system's operating status in real time, promptly detect whether the equipment has executed instructions as expected, and avoid affecting the progress and accuracy of the simulation process due to abnormal equipment status.

[0134] To more clearly illustrate the digital twin method for satellite optical systems provided by this invention, the aforementioned digital twin method will be described below in conjunction with the overall software architecture of the satellite optical system. See [link to documentation]. Figure 7 , Figure 7This is a second schematic diagram of the satellite optical system software architecture provided in an embodiment of the present invention. Figure 7 The front-end is used to simulate the functions of the satellite platform model in the satellite optical system. A graphical user interface (GUI) is built using the Qt framework, specifically the aforementioned telemetry control interface, which is responsible for sending telemetry commands and visualizing the response results. The Qt framework is a program development framework.

[0135] The satellite optical system uses main.cpp as its program entry point, initializes the Qt application environment, and starts the main control window systemInit. This main control window inherits from DpcSystemDemo and is responsible for building and managing the telemetry control interface. The satellite optical system dynamically integrates multiple functional modules by loading configuration files. The "remote control and telemetry" function is hosted by the CtrlTeleWidget container, whose core component, DigiCamWgt, implements an extensible, dockable window architecture based on ads:CDockManager, supporting plug-in management and flexible configuration of the interface layout.

[0136] In terms of interaction design, the front-end remote control module dynamically generates remote control command buttons based on the configuration (i.e., Figure 7 The command / telemetry component (as shown in the diagram) triggers a parameter configuration dialog box built by DigParams (also known as the window and view management module in the diagram). After the user completes the parameter input, it is encapsulated into a standard command and sent to the control and communication layer, realizing a closed-loop control process of "operation-configuration-issuance". The response result is visualized through the command / telemetry component. This component is based on a model-view architecture and works in conjunction with the TelemetryManager data management module to map the real-time response result to the TeleTableModel, ensuring the timeliness and accuracy of the response result display.

[0137] The control and communication layer acts as a bridge between the front-end and back-end business logic layers. It translates user actions on the front-end (such as clicking a button) into calls to the back-end business logic layer's interface, and periodically retrieves response results and status data from the back-end business logic layer, updating the front-end telemetry control interface. The core module of the control and communication layer is the aforementioned remote control module, which is a singleton class with a unique instance in the system (i.e., the remote control module singleton in the diagram). It is responsible for issuing commands (implemented through interaction with the command forwarding module), processing telemetry data (implemented through interaction with the telemetry polling thread), distributing data, and managing the lifecycle of underlying components (implemented through interaction with the back-end dynamic link library lifecycle management).

[0138] In terms of command issuance, the remote control module provides standardized interfaces such as send_cmd_to_power_control_box and send_cmd_to_vlcam for the front-end remote control module to call. After receiving the encapsulated command from the front end, the remote control module forwards the command to the virtual power control box and the virtual camera by calling the underlying communication interfaces in the imaging subsystem (such as write2RS422 and write2LVDS), thereby realizing precise control of the virtual power control box and the virtual camera.

[0139] In terms of telemetry data processing, the remote control module starts an independent thread, proc_tele, to poll the telemetry data interfaces of the imaging subsystem (such as readRS422Data and readLVDSData) at fixed intervals (e.g., 250ms) to ensure the real-time performance and stability of data acquisition. After acquiring the raw binary telemetry data (including the aforementioned telemetry commands and response results), the remote control module calls the updateTelemetryDataOf() method of the global telemetry manager, TelemetryManager, to complete the data parsing and updating, thereby realizing the unified injection of data into the globally shared model.

[0140] The front-end view components, such as TeleTableUi, retrieve the latest data from TelemetryManager through a subscription mechanism and automatically refresh the display, ensuring the dynamic responsiveness of the human-computer interaction interface. Furthermore, the remote control module is responsible for the creation, initialization, and destruction of ImagingSubSystem instances, achieving complete lifecycle management of the underlying hardware driver modules and improving system resource utilization and operational reliability.

[0141] The backend business logic layer and control and communication layer are used to simulate the functions of the digital twin model in the satellite optical system. The backend business logic layer, acting as a simulation agent for the imaging subsystem, undertakes the complete simulation task of the satellite imaging link behavior. Encapsulated as a dynamic link library, the backend business logic layer provides a unified interface layer (Facade) that implements the SubSystemBase interface, conforming to the standard specifications defined by the simulation framework, ensuring seamless integration and invocation by upper-layer systems. Its main functional interfaces include: simInit, used to initialize the entire subsystem, create objects such as the virtual control box and virtual cameras, and load the multi-dimensional Excel lookup tables required for line frequency calculation; write2RS422, responsible for receiving and sending telemetry commands to the virtual control box, serving as the main communication channel for telemetry commands; readRS422Data, providing the telemetry data interface for the virtual control box; and write2LVDS and readLVDSData, simulating the LVDS bus communication mechanism to realize internal command issuance and single-machine telemetry data acquisition. Internally, the imaging subsystem integrates key components such as a virtual electronic control box, a first imaging unit, a second imaging unit, and a line frequency calculator, which work together to complete complex logic such as instruction parsing, status management, and data generation.

[0142] The virtual control box, acting as the "central control unit" of the imaging subsystem, is responsible for receiving telemetry commands from the imaging subsystem. It parses and transforms high-level abstract commands by calling the CommandGenerator, generating low-level execution commands for specific virtual camera hardware, and forwards these commands to the corresponding camera instances via the write422 method. Simultaneously, it collects response results from each camera using the get_telemetry method, aggregates them into complete telemetry frames, and returns them to the imaging subsystem. Furthermore, the virtual control box also houses a line frequency calculator instance to support line frequency calculation tasks.

[0143] CommandGenerator, acting as the system's "command translator," is primarily responsible for mapping general telemetry commands at the satellite level into specific hardware operation commands. Its implementation is based on an unordered mapping table, std::unordered_map.<uint16_t,GeneratorFunc> (m_genFuncMap) establishes a mapping relationship between function codes and corresponding telemetry instruction generation functions. Based on the instruction type, it is divided into two categories of processing logic: unit instructions (such as camera power on / off, imaging start / stop, function codes 0x9111, 0x9133) are processed directly by simple functions; annotation instructions (such as setting imaging parameters, modifying line frequency, configuring CMOS, etc., function codes 0x0202, 0x0205) will update the ImagingParams structure and generate corresponding internal configuration instructions to achieve dynamic adjustment of camera operating parameters.

[0144] The first and second imaging units simulate the hardware behavior of visible light and low-light cameras, respectively. Internally, they maintain key state variables such as FPGA power state, CMOS power state, and imaging state (m_running) to reflect the operating characteristics of the real device. The `write422` method processes internal commands from the virtual control box through a built-in instruction parsing map (m_analyzerMap), dynamically changing its own state based on the command content. The `read422` method generates telemetry data packets conforming to the protocol format based on the current state for the upper layer to read. When entering imaging state, the camera starts an independent thread, combines the current line frequency and imaging parameters, calls utility functions in `DataProcessingUtils` to generate simulated image data, and pushes it into a circular queue for use in subsequent image processing flows.

[0145] Corresponding to the aforementioned digital twin method for satellite optical systems, this embodiment of the invention also provides a digital twin device for satellite optical systems, see [link to relevant documentation]. Figure 8 , Figure 8 A schematic diagram of the structure of a digital twin device for a satellite optical system provided in an embodiment of the present invention includes:

[0146] The generation module 801 is used to generate a virtual electrical control box and a virtual camera. The virtual electrical control box is used to simulate the physical electrical control box in the satellite optical system, and the virtual camera is used to simulate the physical camera in the satellite optical system.

[0147] The drive module 802 is used to drive the virtual control box and the virtual camera to respond to the telemetry command in response to the telemetry command for the satellite optical system;

[0148] The acquisition module 803 is used to acquire the response results of the virtual electrical control box and the virtual camera, as the simulation result of the satellite optical system responding to the telemetry command.

[0149] Applying the above embodiments, the satellite optical system adopts a layered software architecture. Receiving telemetry commands is the step executed by the interface layer in the satellite optical system. The virtual control box simulates the physical control box in the satellite optical system, representing the core logic layer. The virtual camera simulates the physical camera in the satellite optical system, representing the unit model layer. The interface layer receives telemetry commands, and the core logic layer and unit model layer respond to these commands, thus obtaining the simulation results of the satellite optical system in response to the telemetry commands. This layered architecture ensures that each layer has a clear and singular scope of responsibility. The interface layer focuses on data interaction, the core logic layer handles command processing and logical operations, and the unit model layer focuses on imaging simulation. This allows developers to conduct targeted testing at each layer, promptly identify and resolve problems, and improve testing efficiency. In terms of maintenance, when a system failure occurs, the problematic layer can be quickly located for targeted repair and optimization, effectively reducing subsequent maintenance costs. Moreover, this layered architecture has good scalability. If new functions or components need to be added in the future, they can be extended and integrated at the corresponding layer without large-scale modifications to the entire system. This enhances the stability and reliability of the system and provides a stable and reliable virtual platform for the testing and verification of satellite optical systems.

[0150] In one possible implementation, the device further includes:

[0151] The injection module is used to introduce abnormal operating conditions into the process of driving the virtual camera to respond to the telemetry command by using a time synchronization mechanism and / or fault injection. The abnormal operating conditions include one or more of the following: timing deviation, component failure, and communication interruption.

[0152] In one possible implementation, the driving module includes:

[0153] The first driving submodule is used to display the telemetry control interface of the satellite optical system;

[0154] The second driving submodule is used to drive the virtual electrical control box and the virtual camera to respond to the telemetry command input to the telemetry control interface.

[0155] In one possible implementation, the virtual camera includes a first imaging unit, a second imaging unit, a focusing mechanism, and a calibration mechanism;

[0156] The first imaging unit is used to simulate the physical camera acquiring first image data;

[0157] The second imaging unit is used to simulate the physical camera acquiring second image data;

[0158] The focusing mechanism is used to simulate the focusing process of the physical camera;

[0159] The calibration mechanism is used to simulate the calibration process of the physical camera.

[0160] In one possible implementation, the first imaging unit and the second imaging unit maintain FPGA power state, CMOS power state and imaging state.

[0161] The first imaging unit simulates the physical camera acquiring second image data, including:

[0162] The first imaging unit simulates the physical camera in the target state to acquire first image data;

[0163] The second imaging unit simulates the physical camera acquiring second image data, including:

[0164] The second imaging unit simulates the physical camera acquiring second image data under the target state;

[0165] The target state is that the FPGA power supply of the physical camera is in the FPGA power supply state, the CMOS power supply is in the CMOS power supply state, and the physical camera is in the imaging state.

[0166] In one possible implementation, the telemetry control interface is pre-subscribed to a telemetry channel, and the device further includes:

[0167] The display module is used to publish the obtained results to the telemetry channel after obtaining the response results from the virtual electrical control box and the virtual camera, so that the telemetry control interface can obtain and display the results.

[0168] In one possible implementation, the driving module includes:

[0169] The third driving submodule is used to respond to telemetry commands for the satellite optical system, drive the virtual control box to parse the telemetry commands, and obtain execution commands for the virtual control box and the virtual camera;

[0170] The fourth driving submodule is used to write the execution instructions into the virtual electrical control box and the virtual camera respectively, so as to drive the virtual electrical control box and the virtual camera to respond to the telemetry instructions.

[0171] This invention also provides an electronic device, such as... Figure 9As shown, it includes a processor 901, a communication interface 902, a memory 903, and a communication bus 904, wherein the processor 901, the communication interface 902, and the memory 903 communicate with each other through the communication bus 904.

[0172] Memory 903 is used to store computer programs;

[0173] When processor 901 executes a program stored in memory 903, it performs the following steps:

[0174] A virtual control box and a virtual camera are generated, wherein the virtual control box is used to simulate the physical control box in the satellite optical system, and the virtual camera is used to simulate the physical camera in the satellite optical system;

[0175] In response to telemetry commands for the satellite optical system, the virtual control box and the virtual camera are driven to respond to the telemetry commands;

[0176] The results of the responses from the virtual control box and the virtual camera are obtained and used as the simulation results of the satellite optical system's response to the telemetry command.

[0177] The communication bus mentioned in the above electronic devices can be a Peripheral Component Interconnect (PCI) bus or an Extended Industry Standard Architecture (EISA) bus, etc. This communication bus can be divided into address bus, data bus, control bus, etc. For ease of illustration, only one thick line is used to represent it in the diagram, but this does not mean that there is only one bus or one type of bus.

[0178] The communication interface is used for communication between the aforementioned electronic devices and other devices.

[0179] The memory may include random access memory (RAM) or non-volatile memory (NVM), such as at least one disk storage device. Optionally, the memory may also be at least one storage device located remotely from the aforementioned processor.

[0180] The processors mentioned above can be general-purpose processors, including central processing units (CPUs), network processors (NPs), etc.; they can also be digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components.

[0181] In another embodiment of the present invention, a computer-readable storage medium is also provided, which stores a computer program that, when executed by a processor, implements the steps of the digital twin method for any of the above-described satellite optical systems.

[0182] In another embodiment of the present invention, a computer program product containing instructions is also provided, which, when run on a computer, causes the computer to execute the digital twin method of any of the satellite optical systems described above.

[0183] In the above embodiments, implementation can be achieved, in whole or in part, through software, hardware, firmware, or any combination thereof. When implemented in software, it can be implemented, in whole or in part, as a computer program product. The computer program product includes one or more computer instructions. When the computer program instructions are loaded and executed on a computer, all or part of the processes or functions described in the embodiments of the present invention are generated. The computer can be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device. The computer instructions can be stored in a computer-readable storage medium or transmitted from one computer-readable storage medium to another. For example, the computer instructions can be transmitted from one website, computer, server, or data center to another website, computer, server, or data center via wired (e.g., coaxial cable, fiber optic, digital subscriber line (DSL)) or wireless (e.g., infrared, wireless, microwave, etc.) means. The computer-readable storage medium can be any available medium accessible to a computer or a data storage device such as a server or data center that integrates one or more available media. The available medium can be a magnetic medium (e.g., floppy disk, hard disk, magnetic tape), an optical medium (e.g., DVD), or a semiconductor medium (e.g., solid-state disk (SSD)).

[0184] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0185] The various embodiments in this specification are described in a related manner. Similar or identical parts between embodiments can be referred to mutually. Each embodiment focuses on describing the differences from other embodiments. In particular, the system embodiments are basically similar to the method embodiments, so the description is relatively simple; relevant parts can be referred to the descriptions of the method embodiments.

[0186] The above description is merely a preferred embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention are included within the scope of protection of the present invention.

Claims

1. A digital twin method for a satellite optical system, characterized in that, The method includes: A virtual control box and a virtual camera are generated, wherein the virtual control box is used to simulate the physical control box in the satellite optical system, and the virtual camera is used to simulate the physical camera in the satellite optical system; In response to telemetry commands for the satellite optical system, the virtual control box and the virtual camera are driven to respond to the telemetry commands; The results of the responses from the virtual control box and the virtual camera are obtained and used as the simulation results of the satellite optical system's response to the telemetry command.

2. The method according to claim 1, characterized in that, The method further includes: In the process of driving the virtual camera to respond to the telemetry command, abnormal operating conditions are introduced into the process by using a time synchronization mechanism and / or fault injection. The abnormal operating conditions include one or more of the following: timing deviation, component failure, and communication interruption.

3. The method according to claim 1, characterized in that, The step of driving the virtual control box and the virtual camera to respond to telemetry commands for the satellite optical system includes: The telemetry control interface of the satellite optical system is shown. In response to a telemetry command input to the telemetry control interface, the virtual electrical control box and the virtual camera are driven to respond to the telemetry command.

4. The method according to claim 1, characterized in that, The virtual camera includes a first imaging unit, a second imaging unit, a focusing mechanism, and a calibration mechanism; The first imaging unit is used to simulate the physical camera acquiring first image data; The second imaging unit is used to simulate the physical camera acquiring second image data; The focusing mechanism is used to simulate the focusing process of the physical camera; The calibration mechanism is used to simulate the calibration process of the physical camera.

5. The method according to claim 4, characterized in that, The first imaging unit and the second imaging unit maintain the FPGA power state, the CMOS power state, and the imaging state. The first imaging unit simulates the physical camera acquiring second image data, including: The first imaging unit simulates the physical camera in the target state to acquire first image data; The second imaging unit simulates the physical camera acquiring second image data, including: The second imaging unit simulates the physical camera acquiring second image data under the target state; The target state is that the FPGA power supply of the physical camera is in the FPGA power supply state, the CMOS power supply is in the CMOS power supply state, and the physical camera is in the imaging state.

6. The method according to claim 3, characterized in that, The telemetry control interface has pre-subscribed to telemetry channels, and the method further includes: After obtaining the response results from the virtual electrical control box and the virtual camera, the obtained results are published to the telemetry channel so that the telemetry control interface can obtain and display the results.

7. The method according to claim 1, characterized in that, The step of driving the virtual control box and the virtual camera to respond to telemetry commands for the satellite optical system includes: In response to telemetry commands for the satellite optical system, the virtual control box is driven to parse the telemetry commands to obtain execution commands for the virtual control box and the virtual camera; The execution instructions are written into the virtual electrical control box and the virtual camera respectively, so as to drive the virtual electrical control box and the virtual camera to respond to the telemetry instructions.

8. A digital twin device for a satellite optical system, characterized in that, The device includes: A generation module is used to generate a virtual electrical control box and a virtual camera. The virtual electrical control box is used to simulate the physical electrical control box in the satellite optical system, and the virtual camera is used to simulate the physical camera in the satellite optical system. A drive module is used to drive the virtual control box and the virtual camera to respond to telemetry commands for the satellite optical system. The acquisition module is used to acquire the response results of the virtual electrical control box and the virtual camera, as the simulation result of the satellite optical system responding to the telemetry command.

9. An electronic device, characterized in that, It includes a processor, a communication interface, a memory, and a communication bus, wherein the processor, the communication interface, and the memory communicate with each other through the communication bus; Memory, used to store computer programs; A processor, when executing a program stored in memory, implements the steps of the method described in any one of claims 1-7.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program that, when executed by a processor, implements the steps of the method described in any one of claims 1-7.

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