Automatic handling method, system and device for single fault of remote sensing satellite and storage medium

Abstract

The invention discloses an automatic handling method, system and device for a single fault of a remote sensing satellite and a storage medium, belongs to the technical field of remote sensing satellite ground station measurement, operation and control, and solves the problem that fault handling in the existing process design in the prior art must be operated by a watch keeper and cannot be carried out in a satellite fault discovery circle. Comprising the following steps: S1, after a measurement and control task is started, identifying a satellite code and entering a fault disposal monitoring waiting period; s2, judging whether the waiting period reaches the fault processing end time or not, if the waiting period does not reach the measurement and control circle time corresponding to the step S1, executing the step S3, and otherwise, executing the step S6; s3, the system receives satellite fault information sent by the fault detection system; step S4, after the system identifies the satellite fault type, generating a fault processing instruction, distributing the generated instruction to the measurement and control circle number corresponding to the step S1, and sending the generated instruction to the ground station; s5, the ground station sends the instructions to the corresponding satellites; and step S6, ending the fault disposal process.

Description

Technical Field

[0001] The present invention relates to the field of remote sensing satellite ground station measurement, operation and control technology, and in particular to an automatic handling method, system, equipment and storage medium for a single fault of a remote sensing satellite. Background Art

[0002] With the continuous improvement of remote sensing satellite measurement, operation and control technology, its application goals have higher requirements, the functions achieved are becoming increasingly powerful, and the development of space technology has also been significantly accelerated.

[0003] Once a satellite is launched into orbit, it is in a complex and harsh space environment and is easily affected by various factors, such as space radiation, extreme temperature changes, magnetic storm interference, etc. These factors may cause the performance of satellite components to degrade, malfunction or even fail, seriously affecting the normal operation of the satellite and the execution of its mission. At the same time, because satellites are located in space, they cannot be repaired and replaced as easily as ground equipment, and traditional troubleshooting and repair methods are difficult to implement. Therefore, the development of advanced satellite fault handling technology is crucial to ensuring the long-term stable operation of satellites, extending satellite life, and reducing satellite maintenance costs.

[0004] Conventional satellite fault handling relies on manual operation. If a satellite fault is identified during a remote control and telemetry mission, the on-duty personnel need to notify the satellite project team of the specific abnormal information, and the project team members will provide satellite fault removal instructions and remote control command injection plans. After receiving the instructions, the on-duty personnel will select the next available measurement and control circle to complete the instruction injection. This traditional method is difficult to achieve rapid diagnosis and processing. When the project team members provide feedback on satellite faults, they have generally gone through multiple measurement and control circles, and sometimes it even takes the next day to handle them. As the number of satellites continues to increase, the cost and difficulty of manual operation are also increasing.

[0005] Therefore, with the increasing complexity of satellite systems, traditional fault handling methods based on expert knowledge are gradually unable to meet the needs, and it is necessary to develop more intelligent fault handling technologies. Summary of the invention

[0006] The present invention solves the problem that in the existing process design of the prior art, fault handling must be performed by the operator on duty, and the satellite fault cannot be handled in the same cycle as it is discovered.

[0007] The present invention provides an automatic handling method for a single fault of a remote sensing satellite, comprising the following steps:

[0008] Step S1, after the measurement and control task starts, identify the satellite code and enter the fault handling monitoring waiting period;

[0009] Step S2, determining whether the waiting period has reached the end time of the fault handling, if it has not reached the measurement and control circle time corresponding to step S1, then executing step S3, otherwise executing step S6;

[0010] Step S3, the system receives satellite fault information sent by the fault detection system;

[0011] Step S4, after the system identifies the satellite fault type, it generates a fault handling instruction, assigns the generated instruction to the measurement and control circle corresponding to step S1, and sends the generated instruction to the ground station;

[0012] Step S5, the ground station sends the command to the corresponding satellite;

[0013] Step S6, end the fault handling process.

[0014] Furthermore, in one embodiment of the present invention, in step S3, the system receives satellite fault information sent by the fault detection system and queues the corresponding satellite.

[0015] Furthermore, in one embodiment of the present invention, in step S3, the system receives satellite fault information sent by the fault detection system, adds the corresponding satellite to the queue, and sends a fault handling notification reply to the fault detection system.

[0016] Furthermore, in one embodiment of the present invention, in the step S5, after the ground station sends the instruction to the corresponding satellite, it sends a handling completion notification to the fault detection system.

[0017] Further, in one embodiment of the present invention, in the step S5, after the ground station sends the instruction to the corresponding satellite, it sends a handling completion notification to the fault detection system and monitors the fault handling completion notification;

[0018] If the ground station receives the fault handling completion notification, step S6 is executed, otherwise step S4 is executed.

[0019] The automatic handling system for a single fault of a remote sensing satellite described in the present invention comprises the following modules:

[0020] Module S1, after the measurement and control mission begins, identifies the satellite code and enters the fault handling monitoring waiting cycle;

[0021] Module S2 determines whether the waiting period reaches the end time of the fault handling. If it does not reach the measurement and control circle time corresponding to module S1, module S3 is executed, otherwise module S6 is executed;

[0022] Module S3, the system receives satellite fault information sent by the fault detection system;

[0023] Module S4: After the system identifies the satellite fault type, it generates fault handling instructions, assigns the generated instructions to the measurement and control circles corresponding to module S1, and sends the generated instructions to the ground station;

[0024] Module S5, the ground station sends the command to the corresponding satellite;

[0025] Module S6, ends the fault handling process.

[0026] An electronic device described in the present invention comprises a processor, a communication interface, a memory and a communication bus, wherein the processor, the communication interface and the memory communicate with each other via the communication bus;

[0027] Memory, used to store computer programs;

[0028] The processor is used to implement any of the method steps described in the above method when executing the program stored in the memory.

[0029] The computer-readable storage medium described in the present invention stores a computer program, and when the computer program is executed by a processor, the method steps of any of the above methods are implemented.

[0030] The present invention solves the problem that in the existing process design of the prior art, fault handling must be performed by the on-duty personnel, and it is impossible to handle the satellite fault in the same cycle as it is discovered. Specific beneficial effects include:

[0031] The present invention discloses an automatic handling method for a single fault of a remote sensing satellite. According to the fault handling constraint rules provided by the satellite project team, a satellite emergency handling model is constructed. When the satellite passes by, satellite telemetry data is acquired and analyzed in real time. The satellite status is diagnosed in mode according to the model rules. When the satellite enters an abnormal state, different emergency measures are taken according to predefined rules to achieve the handling of a single fault of the satellite. The measurement and control operation is automatically executed, and the next handling operation is determined according to the state machine. The design is based on the concept of unmanned operation and measurement and control integration to achieve automated operation management to the greatest extent. The fully autonomous measurement and control function of the Jilin-1 satellite is supported, and the specified abnormalities of the Jilin-1 satellite are automatically handled. Considering the cumulative counting abnormality, the continuous counting state (with cache) received by multiple stations will result in count accumulation and inaccurate judgment, so a judgment is made for a single fault of a single station;

[0032] The automatic handling method for a single fault of a remote sensing satellite described in the present invention is specifically applied to the field of telemetry analysis of a remote sensing satellite ground station and remote sensing satellite remote control command uplink. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The above and / or additional aspects and advantages of the present invention will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0034] Figure 1 This is a diagram of an automatic handling method for a single failure of a remote sensing satellite as described in Implementation Mode Five. DETAILED DESCRIPTION

[0035] The following will clearly and completely describe various embodiments of the present invention in conjunction with the accompanying drawings. The embodiments described with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0036] Implementation method 1: An automatic handling method for a single fault of a remote sensing satellite described in this implementation method includes the following steps:

[0037] Step S1, after the measurement and control task starts, identify the satellite code and enter the fault handling monitoring waiting period;

[0038] Step S2, determining whether the waiting period has reached the end time of the fault handling, if it has not reached the measurement and control circle time corresponding to step S1, then executing step S3, otherwise executing step S6;

[0039] Step S3, the system receives satellite fault information sent by the fault detection system;

[0040] Step S4, after the system identifies the satellite fault type, it generates a fault handling instruction, assigns the generated instruction to the measurement and control circle corresponding to step S1, and sends the generated instruction to the ground station;

[0041] Step S5, the ground station sends the command to the corresponding satellite;

[0042] Step S6, end the fault handling process.

[0043] Since fault handling must be performed by the on-duty personnel in the existing process design, it is impossible to handle the satellite fault in the same cycle as it is discovered. Therefore, the key to solving the problem is to use the system to automatically detect and handle faults, instead of the original on-duty personnel manually identifying the remote sensing satellite fault, contacting the satellite project team to obtain the satellite handling plan, and executing the remote control command sending operation according to the handling plan to solve the satellite fault. In this way, the fault handling strategy can be immediately started in the same cycle as the satellite fault occurs, and the handling operation can be completed according to the fault plan, which improves the speed of problem handling, greatly reduces the adverse consequences caused by long-term satellite abnormalities, reduces manual operations in the overall process, improves the operating efficiency of the overall system, and avoids the impact of manual misoperation.

[0044] In order to solve the above technical problems, this embodiment designs an automatic handling method for a single fault of a remote sensing satellite, comprising the following steps:

[0045] Step S1, first determine the planned time of the measurement and control task. Before the task time arrives, the system will automatically complete the ground station preparation work, including antenna presetting, macro distribution of various equipment parameters, etc. After the measurement and control task starts, identify the satellite code and enter the fault handling monitoring waiting period, receive satellite telemetry data in real time, and monitor whether the fault detection system identifies the corresponding satellite fault in the plan, and the system status enters Status0;

[0046] Step S2, determine whether the waiting period has reached the end time of the fault handling. If it has not reached the measurement and control circle time, continue the fault handling monitoring step S3 to determine whether the satellite fault monitoring system has identified the abnormality in the plan through telemetry. If it has reached the latest sending time of the corresponding measurement and control circle sending instruction in S1, jump to step S6, end the handling operation of this circle, and continue to execute the regular business of the ground station;

[0047] Step S3, after receiving the satellite fault information transmitted by the fault detection system, the system status enters Status1;

[0048] Step S4, the system obtains the satellite fault to be processed from the processing queue, identifies the fault type according to the fault identification detection, automatically completes the generation of fault processing instructions according to the fault processing instruction generation rules, and distributes the generated instructions to the corresponding measurement and control circles in step S1, and sends the generated instructions to the ground station;

[0049] Step S5, handle according to the fault plan, the ground station sends the corresponding remote control command to the satellite according to the emergency remote control command sending process, and the system status is initialized to Status0;

[0050] Step S6: When the latest sending time of the measurement and control circle to send instructions is reached, the system will end the fault handling process and switch to the normal business remote control process of the ground station.

[0051] It should be noted that the system described in this embodiment is the overall control end of the satellite fault handling system.

[0052] Therefore, the satellite system has a complex structure, diverse functions, and various failure modes. Relying on an automatic handling method for a single failure of a remote sensing satellite as described in this embodiment, human intervention can be minimized as much as possible, which can not only reduce the time consumption of handling by relying on expert knowledge, but also avoid the risks brought by manual operation errors.

[0053] Implementation method 2: This implementation method further limits the automatic handling method for a single fault of a remote sensing satellite described in implementation method 1. In step S3, the system receives satellite fault information sent by the fault detection system and adds the corresponding satellite to the queue.

[0054] The automatic handling method for a single fault of a remote sensing satellite described in this embodiment includes the following steps:

[0055] Step S1, first determine the planned time of the measurement and control task. Before the task time arrives, the system will automatically complete the ground station preparation work, including antenna presetting, macro distribution of various equipment parameters, etc. After the measurement and control task starts, identify the satellite code and enter the fault handling monitoring waiting period, receive satellite telemetry data in real time, and monitor whether the fault detection system identifies the corresponding satellite fault in the plan, and the system status enters Status0;

[0056] Step S2, determine whether the waiting period has reached the end time of the fault handling. If it has not reached the measurement and control circle time, continue the fault handling monitoring step S3 to determine whether the satellite fault monitoring system has identified the abnormality in the plan through telemetry. If it has reached the latest sending time of the corresponding measurement and control circle sending instruction in S1, jump to step S6, end the handling operation of this circle, and continue to execute the regular business of the ground station;

[0057] Step S3, after receiving the satellite fault information transmitted by the fault detection system, the system status enters Status1, and the corresponding satellite fault is added to the processing queue waiting for system scanning;

[0058] Step S4, the system obtains the satellite fault to be processed from the processing queue, identifies the fault type according to the fault identification detection, automatically completes the generation of fault processing instructions according to the fault processing instruction generation rules, and distributes the generated instructions to the corresponding measurement and control circles in step S1, and sends the generated instructions to the ground station;

[0059] Step S5, handle according to the fault plan, the ground station sends the corresponding remote control command to the satellite according to the emergency remote control command sending process, and the system status is initialized to Status0;

[0060] Step S6: When the latest sending time of the measurement and control circle to send instructions is reached, the system will end the fault handling process and switch to the normal business remote control process of the ground station.

[0061] It should be noted that the system described in this embodiment is the overall control end of the satellite fault handling system.

[0062] This implementation achieves accurate identification and detection of satellite failures by locating the corresponding satellite failures in a disposal queue.

[0063] Implementation method three: This implementation method is a further limitation of the automatic handling method for a single fault of a remote sensing satellite described in implementation method two. In step S3, the system receives satellite fault information sent by the fault detection system, adds the corresponding satellite to the queue, and sends a fault handling notification reply to the fault detection system.

[0064] The automatic handling method for a single fault of a remote sensing satellite described in this embodiment includes the following steps:

[0065] Step S1, first determine the planned time of the measurement and control task. Before the task time arrives, the system will automatically complete the ground station preparation work, including antenna presetting, macro distribution of various equipment parameters, etc. After the measurement and control task starts, identify the satellite code and enter the fault handling monitoring waiting period, receive satellite telemetry data in real time, and monitor whether the fault detection system identifies the corresponding satellite fault in the plan, and the system status enters Status0;

[0066] Step S2, determine whether the waiting period has reached the end time of the fault handling. If it has not reached the measurement and control circle time, continue the fault handling monitoring step S3 to determine whether the satellite fault monitoring system has identified the abnormality in the plan through telemetry. If it has reached the latest sending time of the corresponding measurement and control circle sending instruction in S1, jump to step S6, end the handling operation of this circle, and continue to execute the regular business of the ground station;

[0067] Step S3, after receiving the satellite fault information transmitted by the fault detection system, the system status enters Status1, and the corresponding satellite fault is added to the handling queue to wait for system scanning, and at the same time, a fault handling notification reply is sent to the fault detection system;

[0068] Step S4, the system obtains the satellite fault to be processed from the processing queue, identifies the fault type according to the fault identification detection, automatically completes the generation of fault processing instructions according to the fault processing instruction generation rules, and distributes the generated instructions to the corresponding measurement and control circles in step S1, and sends the generated instructions to the ground station;

[0069] Step S5, handle according to the fault plan, the ground station sends the corresponding remote control command to the satellite according to the emergency remote control command sending process, and the system status is initialized to Status0;

[0070] Step S6: When the latest sending time of the measurement and control circle is reached, the system will end the fault handling process and enter the normal business remote control process of the ground station.

[0071] It should be noted that the system described in this embodiment is the overall control end of the satellite fault handling system.

[0072] In this embodiment, the system sends a fault handling notification reply to the fault detection system to ensure that the system accurately receives the fault handling notification sent by the fault detection system.

[0073] Implementation method 4: This implementation method is a further limitation of the automatic handling method for a single fault of a remote sensing satellite described in implementation method 3. In step S5, after the ground station sends the instruction to the corresponding satellite, it sends a handling completion notification to the fault detection system.

[0074] The automatic handling method for a single fault of a remote sensing satellite described in this embodiment includes the following steps:

[0075] Step S1, first determine the planned time of the measurement and control task. Before the task time arrives, the system will automatically complete the ground station preparation work, including antenna presetting, macro distribution of various equipment parameters, etc. After the measurement and control task starts, identify the satellite code and enter the fault handling monitoring waiting period, receive satellite telemetry data in real time, and monitor whether the fault detection system identifies the corresponding satellite fault in the plan, and the system status enters Status0;

[0076] Step S2, determine whether the waiting period has reached the end time of the fault handling. If it has not reached the measurement and control circle time, continue the fault handling monitoring step S3 to determine whether the satellite fault monitoring system has identified the abnormality in the plan through telemetry. If it has reached the latest sending time of the corresponding measurement and control circle sending instruction in S1, jump to step S8, end the handling operation of this circle, and continue to execute the regular business of the ground station;

[0077] Step S3, after receiving the satellite fault information transmitted by the fault detection system, the system status enters Status1, and the corresponding satellite fault is added to the handling queue to wait for system scanning, and at the same time, a fault handling notification reply is sent to the fault detection system;

[0078] Step S4, the system obtains the satellite fault to be processed from the processing queue, identifies the fault type according to the fault identification detection, automatically completes the generation of fault processing instructions according to the fault processing instruction generation rules, and distributes the generated instructions to the corresponding measurement and control circles in step S1, and sends the generated instructions to the ground station;

[0079] Step S5, handle according to the fault plan, the ground station sends the corresponding remote control command to the satellite according to the emergency remote control command sending process, and determines the command sending status based on real-time telemetry. When the satellite center command count increases by 1 and the center error command technology does not change, the command uplink is successful. After all fault handling commands are sent, the fault handling command is sent, and the system status enters Status3;

[0080] Step S6, sending a handling completion notification to the fault detection system, and the system enters Status 4;

[0081] Step S7, end the fault handling process, and initialize the system status to Status0;

[0082] Step S8: When the latest sending time of the measurement and control circle to send instructions is reached, the system will end the fault handling process and switch to the normal business remote control process of the ground station.

[0083] It should be noted that the system described in this embodiment is the overall control end of the satellite fault handling system.

[0084] In this implementation, the fault detection system instruction waiting time can be ended by sending a notification to the fault detection system through the ground station.

[0085] Embodiment 5: This embodiment further limits the automatic handling method for a single fault of a remote sensing satellite described in embodiment 4. In step S5, after the ground station sends the instruction to the corresponding satellite, it sends a handling completion notification to the fault detection system and monitors the fault handling completion notification;

[0086] If the ground station receives the fault handling completion notification, step S6 is executed, otherwise step S4 is executed.

[0087] In this embodiment, a method for automatically handling a single fault of a remote sensing satellite is described. Figure 1 As shown, the following steps are included:

[0088] Step S1, first determine the planned time of the measurement and control task. Before the task time arrives, the system will automatically complete the ground station preparation work, including antenna presetting, macro distribution of various equipment parameters, etc. After the measurement and control task starts, identify the satellite code and enter the fault handling monitoring waiting period, receive satellite telemetry data in real time, and monitor whether the fault detection system identifies the corresponding satellite fault in the plan, and the system status enters Status0.

[0089] Step S2, determine whether the waiting period has reached the end time of the fault handling. If it has not reached the measurement and control circle time, continue the fault handling monitoring process S3 to determine whether the satellite fault monitoring system has identified the abnormality in the plan through telemetry. If it has reached the latest sending time of the corresponding measurement and control circle sending instruction in S1, jump to step S8, end the handling operation of this circle, and continue to execute the regular business of the ground station;

[0090] Step S3, after receiving the satellite fault information transmitted by the fault detection system, the system status enters Status1, and the corresponding satellite fault is added to the handling queue to wait for system scanning, and at the same time, a fault handling notification reply is sent to the fault detection system;

[0091] Step S4, the system obtains the satellite fault to be processed from the processing queue, identifies the fault type according to the fault identification detection, automatically completes the generation of fault processing instructions according to the fault processing instruction generation rules, and distributes the generated instructions to the corresponding measurement and control circles in step S1;

[0092] Step S5, handle according to the fault plan, the ground station sends the corresponding remote control command to the satellite according to the emergency remote control command sending process, and determines the command sending status based on real-time telemetry. When the satellite center command count increases by 1 and the center error command technology does not change, the command uplink is successful. After all fault handling commands are sent, the fault handling command is sent, and the system status enters Status3;

[0093] Step S6, sending a handling completion notification to the fault detection system, and monitoring the fault handling completion notification, the system enters Status 4;

[0094] Step S7, wait for the satellite to recover according to the time threshold specified in the disposal plan. If a fault disposal end notification is received during this period, it means that the satellite fault has been resolved, and the fault disposal process ends. The system status is initialized to Status0. If no fault disposal end notification is received, it means that the automatic disposal action for this fault has not taken effect. The reason may be that the command was not successfully issued or the satellite received an error code and was not executed. In this case, the fault needs to be put back into the satellite fault disposal queue, jump to step S4, and the system status is updated to Status1;

[0095] Step S8: When the latest sending time of the measurement and control circle to send instructions is reached, the system will end the fault handling process and switch to the normal business remote control process of the ground station.

[0096] It should be noted that the system described in this embodiment is the overall control end of the satellite fault handling system.

[0097] In summary, the existing system design cannot meet the automatic execution mode of this type of task, so the automatic handling technology for remote sensing satellite failures can better ensure the long-term stable operation of the satellite and maximize the effectiveness of the satellite.

[0098] Embodiment 6: The automatic handling system for a single fault of a remote sensing satellite described in this embodiment includes the following modules:

[0099] Module S1, after the measurement and control mission begins, identifies the satellite code and enters the fault handling monitoring waiting cycle;

[0100] Module S2 determines whether the waiting period reaches the end time of the fault handling. If it does not reach the measurement and control circle time corresponding to module S1, module S3 is executed, otherwise module S6 is executed;

[0101] Module S3, the system receives satellite fault information sent by the fault detection system;

[0102] Module S4: After the system identifies the satellite fault type, it generates fault handling instructions, assigns the generated instructions to the measurement and control circles corresponding to module S1, and sends the generated instructions to the ground station;

[0103] Module S5, the ground station sends the command to the corresponding satellite;

[0104] Module S6, ends the fault handling process.

[0105] It should be noted that the system described in this embodiment is the overall control end of the satellite fault handling system.

[0106] Embodiment 7: An electronic device described in this embodiment 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;

[0107] Memory, used to store computer programs;

[0108] The processor is used to implement the method steps described in any one of implementation modes 1 to 5 when executing the program stored in the memory.

[0109] Implementation method eight: A computer-readable storage medium described in this implementation method stores a computer program, and when the computer program is executed by a processor, the method steps described in any one of implementation methods one to five are implemented.

[0110] The above is a detailed introduction to the automatic handling method, system, device and storage medium for a single fault of a remote sensing satellite proposed in the present invention. Specific examples are used in this article to illustrate the principle and implementation mode of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea. At the same time, for a person skilled in the art, according to the idea of ​​the present invention, there will be changes in the specific implementation mode and application scope. In summary, the content of this specification should not be understood as a limitation on the present invention.

Claims

1. An automatic handling method for a single fault of a remote sensing satellite, characterized in that: The following steps are involved: Step S1, after the measurement and control task starts, identify the satellite code and enter the fault handling monitoring waiting period; Step S2, determining whether the waiting period has reached the end time of the fault handling, if it has not reached the measurement and control circle time corresponding to step S1, then executing step S3, otherwise executing step S6; Step S3, the system receives satellite fault information sent by the fault detection system; Step S4, after the system identifies the satellite fault type, it generates a fault handling instruction, assigns the generated instruction to the measurement and control circle corresponding to step S1, and sends the generated instruction to the ground station; Step S5, the ground station sends the command to the corresponding satellite; Step S6, end the fault handling process.

2. The automatic handling method for a single fault of a remote sensing satellite according to claim 1, characterized in that: In step S3, the system receives satellite fault information sent by the fault detection system and queues the corresponding satellite.

3. The automatic handling method for a single fault of a remote sensing satellite according to claim 2, characterized in that: In step S3, the system receives satellite fault information sent by the fault detection system, adds the corresponding satellite to the queue, and sends a fault handling notification reply to the fault detection system.

4. The automatic handling method for a single fault of a remote sensing satellite according to claim 3 is characterized in that: In step S5, after the ground station sends the instruction to the corresponding satellite, it sends a handling completion notification to the fault detection system.

5. The automatic handling method for a single fault of a remote sensing satellite according to claim 4, characterized in that: In the step S5, after the ground station sends the command to the corresponding satellite, it sends a handling completion notification to the fault detection system and monitors the fault handling completion notification; If the ground station receives the fault handling completion notification, step S6 is executed, otherwise step S4 is executed.

6. An automatic handling system for single faults of remote sensing satellites, characterized in that: Includes the following modules: Module S1, after the measurement and control mission begins, identifies the satellite code and enters the fault handling monitoring waiting cycle; Module S2 determines whether the waiting period reaches the end time of the fault handling. If it does not reach the measurement and control circle time corresponding to module S1, module S3 is executed, otherwise module S6 is executed; Module S3, the system receives satellite fault information sent by the fault detection system; Module S4: After the system identifies the satellite fault type, it generates fault handling instructions, assigns the generated instructions to the measurement and control circles corresponding to module S1, and sends the generated instructions to the ground station; Module S5, the ground station sends the command to the corresponding satellite; Module S6, ends the fault handling process.

7. 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, for implementing the method steps described in any one of claims 1 to 5 when executing a program stored in a memory.

8. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the method steps described in any one of claims 1 to 5 are implemented.

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