Monitoring system for spacecraft power distribution system

Abstract

The embodiment of the invention provides a monitoring system for a spacecraft power distribution system. The monitoring system comprises a physical model, a database and a digital model. The physical model is used for detecting the spacecraft power distribution system at a first moment to obtain first information; the first information is operation information of the spacecraft power distribution system at the first moment. The database is used for storing second information. The second information comprises historical operation information of the spacecraft power distribution system. And the physical model is also used for predicting third information based on the first information and the second information. The third information is operation information of the spacecraft power distribution system at the second moment. The second moment is later than the first moment. The digital model is used for determining that a target fault in multiple faults occurs in the spacecraft power distribution system at the second moment on the basis that the first information, the second information and the third information meet a target preset condition in multiple preset conditions, so that whether the spacecraft power distribution system breaks down or not is automatically monitored, and safe operation of the effective load of the spacecraft is guaranteed.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft technology, and in particular to a monitoring system for a spacecraft power distribution system. Background Art

[0002] The spacecraft payload relies on the spacecraft's power distribution system to work. Therefore, monitoring the spacecraft's power distribution system and handling it in a timely manner when a failure occurs in the spacecraft's power distribution system is of great significance to the spacecraft payload's deep space exploration mission.

[0003] Although a series of reliability-related measures have been taken in the design of the spacecraft power distribution system, due to the complexity of deep space exploration missions, the changeable working conditions of the spacecraft power distribution system, and the harsh working environment of the spacecraft power distribution system, various faults may still occur in the spacecraft power distribution system, affecting the safe operation of the spacecraft payload, and may even cause huge economic losses and catastrophic consequences. Therefore, how to monitor the spacecraft power distribution system and detect the faults of the spacecraft power distribution system in time is an urgent problem to be solved.

[0004] At present, the spacecraft power distribution system is often monitored manually (for example, astronauts and ground staff). However, as deep space exploration missions continue to extend to deeper areas of the universe, the time cost of ground-to-space communications has gradually increased to a point where it is intolerable for monitoring the spacecraft power distribution system. Therefore, relying on manual monitoring of the spacecraft power distribution system will cause the failure of the spacecraft power distribution system to be difficult to be discovered in time due to the time delay, affecting the safe operation of the spacecraft payload. Summary of the invention

[0005] The technical problem to be solved by the present invention is to provide a monitoring system for a spacecraft power distribution system, which can automatically monitor whether a fault occurs in the spacecraft power distribution system to ensure the safe operation of the spacecraft payload.

[0006] The technical solution of the present invention to solve the above technical problems is as follows:

[0007] The present invention provides a monitoring system for a spacecraft power distribution system, including a physical model, a database and a digital model. The physical model is used to detect the spacecraft power distribution system at a first moment to obtain first information. The first information is the operating information of the spacecraft power distribution system at the first moment. The operating information includes environmental information of the environment in which the spacecraft power distribution system is located and configuration information of the spacecraft power distribution system. The database is used to store second information. The second information is obtained by detecting the spacecraft power distribution system based on the history of the physical model. The second information includes historical operating information of the spacecraft power distribution system. The time when the physical model obtains the second information is earlier than the first moment. The physical model is also used to predict and obtain third information based on the first information and the second information. The third information is the operating information of the spacecraft power distribution system at the second moment. The second moment is later than the first moment.

[0008] The digital model is used to determine a target fault among multiple faults occurring in the spacecraft power distribution system at a second moment based on the first information, the second information, and the third information satisfying a target preset condition among multiple preset conditions. One of the multiple faults corresponds to at least one preset condition among the multiple preset conditions. The target preset condition corresponds to the target fault.

[0009] Based on the above technical solution, the present invention can also be improved as follows.

[0010] Further, the spacecraft power distribution system includes a plurality of power distributors. The spacecraft includes at least one payload. One power distributor is used to supply power to one payload. The physical model includes a sensor network, and the sensor network includes a plurality of sensors. For any power distributor among the plurality of power distributors, any power distributor corresponds to at least one sensor among the plurality of sensors, and the at least one sensor is used to detect operation information of the any power distributor.

[0011] Further, the environmental information of the environment in which the spacecraft power distribution system is located includes environmental information of the environments in which multiple power distributors are located. The environmental information of the environment in which any power distributor is located includes at least one of the temperature, humidity, and air pressure of the environment in which any power distributor is located. The configuration information of the spacecraft power distribution system includes configuration information of multiple power distributors. The configuration information of any power distributor includes at least one of the input current value, input voltage value, internal resistance value, pressure withstand value, and output power value of any power distributor.

[0012] Furthermore, the physical model also includes an environmental model and a system component model. The first information includes first environmental information and first configuration information. The second information includes second environmental information and second configuration information. The third information includes third environmental information and third configuration information. The sensor network is also used to detect the spacecraft power distribution system at a first moment to obtain the first environmental information and the first configuration information. The environmental model is used to obtain the second environmental information from the database, and to determine the third environmental information based on the first environmental information and the second environmental information. The environmental model is also used to store the determined third environmental information in the database. The system component model is used to obtain the second configuration information from the database, and to determine the third configuration information based on the first configuration information and the second configuration information. The system component model is also used to store the determined third configuration information in the database.

[0013] Furthermore, the digital model includes a top layer and at least one subsystem layer. One subsystem layer corresponds to one distributor. The top layer is used to store multiple preset conditions, and to store the corresponding relationship between each preset condition in the multiple preset conditions and each fault in the multiple faults. For any subsystem layer in at least one subsystem layer, any subsystem layer is used to read multiple preset conditions from the top layer, and to determine whether the first information, the second information, and the third information corresponding to the target distributor meet any preset condition in the multiple preset conditions. The target distributor is the distributor corresponding to any subsystem layer. Any subsystem layer is also used to read the fault corresponding to any preset condition from the top layer, and to predict the fault corresponding to any preset condition as a fault occurring in the target distributor at the second moment.

[0014] Further, any subsystem layer is also used to determine the fault type corresponding to the fault of the target distributor when the fault of the target distributor is predicted to occur at the second moment. Different fault types correspond to different fault handling strategies. Based on the fault type corresponding to the fault of the target distributor, determine the fault handling strategy for the target distributor. Based on the fault handling strategy for the target distributor, handle the target distributor.

[0015] Further, the fault type includes a hardware fault type and a software fault type. The fault corresponding to the hardware fault type includes a fault caused by hardware damage of the corresponding power distributor. The fault corresponding to the software fault type includes a fault caused by the actual operation program of the corresponding power distributor deviating from the preset operation program.

[0016] Further, any power distributor corresponds to at least one standby power distributor among the multiple power distributors. The fault handling strategy for the fault corresponding to the hardware fault type includes switching the power supply device from the first power distributor to the second power distributor. The first power distributor is a power distribution device that has a hardware fault type fault among the multiple power distribution devices determined by prediction. The second power distributor is a standby power distributor corresponding to the second power distributor among the multiple power distribution devices.

[0017] Furthermore, the fault handling strategy for the fault corresponding to the software fault type includes restarting and / or initializing the third power distribution device. The third power distribution device is a power distribution device that has a fault of the software fault type among the multiple power distribution devices determined by prediction.

[0018] Furthermore, the monitoring system provided by the present invention also includes an information display platform, which is used to display the first information and / or the second information and / or the third information; and / or, display the target fault and / or the fault handling strategy corresponding to the target fault; and / or, display the preset condition editing page. The preset condition editing page is used to receive the input preset condition.

[0019] The beneficial effects of the present invention are as follows: the monitoring system provided by the present invention applies the layered concept under the framework including the physical model, database, digital model and information display platform, can realize autonomous health management and fault detection, diagnosis and disposal of the spacecraft power distribution system without relying on manual work, and has a certain self-learning and updating capability. This scheme combines the idea of ​​digital twins, combines the physical model with the digital model, and performs layered management for objects and tasks, so as to realize highly real-time, high-precision and updatable autonomous fault diagnosis and disposal. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 A monitoring system for a spacecraft power distribution system is provided for an embodiment of the present application;

[0021] Figure 2 A method for updating a model in a detection system provided in an embodiment of the present application. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the present application will be described below in conjunction with the drawings in the embodiments of the present application. Among them, in the description of the present application, unless otherwise specified, " / " indicates that the objects associated before and after are in an "or" relationship, for example, A / B can represent A or B; "and / or" in the present application is only a description of the association relationship of the associated objects, indicating that there can be three relationships, for example, A and / or B, which can represent: A exists alone, A and B exist at the same time, and B exists alone, where A and B can be singular or plural. And, in the description of the present application, unless otherwise specified, "multiple" refers to two or more than two. "At least one of the following" or similar expressions refers to any combination of these items, including any combination of single items or plural items. For example, at least one of a, b, or c can represent: a, b, c, ab, ac, bc, or abc, where a, b, c can be single or multiple. In addition, in order to facilitate the clear description of the technical solutions of the embodiments of the present application, in the embodiments of the present application, the words "first", "second" and the like are used to distinguish between the same items or similar items with substantially the same functions and effects. Those skilled in the art will understand that the words "first", "second" and the like do not limit the quantity and execution order, and the words "first", "second" and the like do not necessarily limit the differences. At the same time, in the embodiments of the present application, the words "exemplary" or "for example" are used to indicate examples, illustrations or descriptions. Any embodiment or design described as "exemplary" or "for example" in the embodiments of the present application should not be interpreted as being more preferred or more advantageous than other embodiments or design.

[0023] Figure 1 The present application provides a monitoring system for a spacecraft power distribution system. Figure 1 The monitoring system for the spacecraft power distribution system provided in the embodiment of the present application includes a physical model, a database and a digital model.

[0024] The physical model is used to detect the spacecraft power distribution system at a first moment to obtain first information. The first information is the operation information of the spacecraft power distribution system at the first moment. The operation information includes environmental information of the environment in which the spacecraft power distribution system is located and configuration information of the spacecraft power distribution system.

[0025] In some embodiments, the environmental information of the environment in which the spacecraft power distribution system is located includes environmental information of the environments in which multiple power distributors are located. The environmental information of the environment in which any power distributor is located includes at least one of the temperature, humidity, and air pressure of the environment in which any power distributor is located. The configuration information of the spacecraft power distribution system includes configuration information of multiple power distributors. The configuration information of any power distributor includes at least one of the input current value, input voltage value, internal resistance value, pressure withstand value, and output power value of any power distributor.

[0026] The database is used to store the second information. The second information is obtained based on the physical model history of the spacecraft power distribution system. The second information includes the historical operation information of the spacecraft power distribution system. The physical model obtains the second information earlier than the first moment.

[0027] The physical model is also used to predict and obtain third information based on the first information and the second information. The third information is the operation information of the spacecraft power distribution system at a second moment. The second moment is later than the first moment.

[0028] The digital model is used to determine a target fault among multiple faults occurring in the spacecraft power distribution system at a second moment based on the first information, the second information, and the third information satisfying a target preset condition among multiple preset conditions.

[0029] Wherein, one of the multiple faults corresponds to at least one preset condition of the multiple preset conditions, and the target preset condition corresponds to the target fault.

[0030] It should be noted that those skilled in the art can set preset conditions based on actual scenarios and requirements.

[0031] Exemplarily, the preset conditions that can be set include:

[0032] Preset condition 1: The application power supply 1 is open (after the distribution application power supply 1 is powered on, the current of the external distribution application power supply 1 is less than 0.1A).

[0033] Preset condition 2: The power supply 2 is open (after the power distribution unit power supply 2 is powered on, the current of the power distribution unit power supply 2 outside the cabin is less than 0.1A).

[0034] Preset condition 3: Both application power supplies 1 and 2 are open (after both application power supplies 1 and 2 of the distributor are powered on, the status of the AB machine of the extravehicular distributor is "<0.5V").

[0035] Preset condition 4: After the distributor is powered by power supply 1 and / or power supply 2, -0.07A≤cabin current≤0.07A.

[0036] Preset condition 5: "Experimental cabinet voltage telemetry" <0.5V.

[0037] Preset condition 6: 0.5V≤28VSSPC board of each channel, command power supply output voltage≤26V.

[0038] Among them, if the first information, the second information and the third information meet any one of the preset conditions 1-3, it can be determined that the target fault is an abnormal secondary power supply of the payload cabin external distributor, that is, the payload secondary power supply telemetry is outside the normal range. If the first information, the second information and the third information meet the preset condition 4, it can be determined that the target fault is a power-on failure of the host 01. If the first information, the second information and the third information meet the preset condition 5, it can be determined that the target fault is an abnormal main power supply of the experimental cabinet. If the first information, the second information and the third information meet the preset condition 6, it can be determined that the target fault is a 28V SSPC power distribution failure.

[0039] In some embodiments, after the monitoring system provided in the embodiments of the present application determines the target fault, it can also generate a corresponding decision to handle the fault.

[0040] Exemplarily, if it is determined that the first information, the second information, and the third information meet the above-mentioned preset condition 1, the following decision 1 may be generated:

[0041] 1. Send a power-off command to application power supply 1;

[0042] 2. Wait for 5 minutes;

[0043] 3. Send a power-on command to application power supply 1;

[0044] 4. If the current of application power supply 1 has not been restored, disconnect the main secondary power supply and turn off application power supply 1;

[0045] 5. If the system still has not recovered, take follow-up measures (switch to the backup power board).

[0046] If it is determined that the first information, the second information and the third information meet the above-mentioned preset condition 2, the following decision 2 can be generated:

[0047] 1. Send a power-off command to application power supply 2;

[0048] 2. Wait for 5 minutes;

[0049] 3. Send a power-on command to application power supply 2;

[0050] 4. If the current of application power supply 2 has not been restored, disconnect the backup secondary power supply and turn off application power supply 2.

[0051] 5. If the system still has not recovered, take follow-up measures (switch to the backup power board).

[0052] If it is determined that the first information, the second information and the third information meet the above-mentioned preset condition 3, the following decision 3 can be generated:

[0053] Proceed according to decision 1 and decision 2 in turn.

[0054] If it is determined that the first information, the second information and the third information meet the above-mentioned preset condition 4, the following decision can be generated:

[0055] 1. Send a power-off command;

[0056] 2. Wait for 2 minutes;

[0057] 3. Send power-on command;

[0058] 4. If it still has not recovered, take follow-up measures (switch to the backup relay 01 board).

[0059] If it is determined that the first information, the second information and the third information meet the above-mentioned preset condition 5, the following decision can be generated:

[0060] 1. Inform relevant ground personnel before handling;

[0061] 2. The application platform re-powers the test cabinet. If the "test cabinet voltage telemetry" is: 95V~110V, it proves that the treatment is successful;

[0062] 3. If there is still no output, send a command to switch the 100V power supply interface of the test cabinet to the backup power supply; send a command to the distributor to connect the backup power supply of the test cabinet; "Test cabinet SSPC power supply voltage telemetry": 95V~110V;

[0063] 4. Notify the platform to take measures to restore the 100V main power supply of the laboratory cabinet.

[0064] If it is determined that the first information, the second information and the third information meet the above-mentioned preset condition 6, the following decision can be generated:

[0065] 1. Send a command to connect the backup power supply;

[0066] 2. Wait for 5 seconds;

[0067] 3. Send a command to disconnect the main power supply;

[0068] 4. If the fault still does not recover, take follow-up measures (switch to the spare 28V SSPC board).

[0069] It can be seen that the monitoring system provided in the embodiment of the present application can be applied to the spacecraft power distribution system, and can realize autonomous health management and fault detection, diagnosis, and disposal of the spacecraft power distribution system without relying on manual work, and has a certain self-learning and updating capability. This solution combines physical models and digital models, and performs hierarchical management for objects and tasks to achieve highly real-time, high-precision, and updatable autonomous fault diagnosis and disposal. The monitoring system provided in the embodiment of the present application is different from the traditional spacecraft fault disposal based on telemetry data, and can be expanded to the entire spacecraft system.

[0070] Among them, the monitoring system provided in the embodiment of the present application is combined with digital twin technology, which can integrate relevant information of the spacecraft power distribution system, monitor the status of the spacecraft power distribution system in real time, and conduct a global analysis of the spacecraft power distribution system to detect faults early and improve the reliability and efficiency of the spacecraft power distribution system. In addition, the monitoring system provided in the embodiment of the present application provides a complete process description including system description, system construction, system operation, and system optimization, rather than just a description of the design ideas. The monitoring system provided in the embodiment of the present application provides a health management system architecture applied to a specific space station payload power supply and distribution system, which is operational and practical.

[0071] In some embodiments, the spacecraft power distribution system includes a plurality of power distributors. The spacecraft includes at least one payload. A power distributor is used to power a payload. The physical model includes a sensor network, and the sensor network includes a plurality of sensors. The sensor in the embodiment of the present application can be an intelligent sensor with an integrated microprocessor, which has both information monitoring and information processing functions and has certain self-diagnosis and communication capabilities. The sensor network modeling can be distributed in various levels of the spacecraft power distribution system, including sensor location, value, and self-health status.

[0072] For any of the multiple power distributors, since the basic components of any power distributor may include switches, cables, power distributors, voltage regulators, converters, controller SSPC boards, MOSFET devices, etc., the normal or abnormal state of the power distributor is usually manifested in electrical parameters such as current, voltage, resistance, and power. During the operation of the power distributor, it is necessary to ensure the stability of the voltage and current of the power distributor, including overcurrent protection, surge suppression, etc. It is necessary to protect the safe operation of various devices included in the power distributor, including SPCC boards, voltage regulators, etc. It is necessary to dynamically schedule each power distributor according to the state of the spacecraft power distribution system and the tasks to be performed, such as adjusting the corresponding power distributor to the minimum load when a fault occurs, and allocating electricity to different payloads according to the tasks to be performed. Therefore, at least one sensor among the multiple sensors corresponding to any power distributor can be set, and at least one sensor is used to detect the operating information of any of the power distributors.

[0073] In some embodiments, the physical model also includes an environment model and a system component model. The first information includes first environment information and first configuration information. The second information includes second environment information and second configuration information. The third information includes third environment information and third configuration information.

[0074] Among them, the environmental model is constructed based on the environmental information around the system and can be selected according to needs and complexity. The content of environmental modeling is the operating environment of the payload distributor of the space application system of the space station, and the modeling information can be stored in the database. For example, temperature curves and humidity curves. The system component model is carried out in a hierarchical form. The lower system is abstracted into a black box or module containing input, output, and state as a component of the upper system. The bottom system is the component level. The content of system component modeling is the circuit diagram and the ordinary differential equations of the circuit system. The content of the sensor network is the current and voltage monitoring of the power bus and each load power supply line. The sensor network is also used to detect the spacecraft power distribution system at the first moment to obtain the first environmental information and the first configuration information.

[0075] The environment model is used to obtain the second environment information from the database, and to determine the third environment information based on the first environment information and the second environment information. The environment model is also used to store the determined third environment information in the database.

[0076] The system component model is used to obtain the second configuration information from the database, and determine the third configuration information based on the first configuration information and the second configuration information. The system component model is also used to store the determined third configuration information in the database.

[0077] In some embodiments, the database may store background knowledge and system information of the spacecraft power distribution system. The content in the database may be extracted and formatted from existing files and stored in the database.

[0078] Background knowledge may include environmental information, model initial information (digital model initial information, physical model initial information), basic component information, and other information required in digital twins. Among them, environmental information may include space radiation, temperature, humidity, etc. Model initial information may include load distribution inside and outside the cabin, software functions and interface configuration items, communication protocols, etc. Basic component information may include rated parameters, reliability parameters, etc. The initial health management model is generated according to the on-orbit fault plan, including basic fault information, fault diagnosis and disposal information, fault impact and guarantee information, etc. In the system information, each layer stores the detailed electrical parameter time series value of this layer, obtains the health status and mission information of the lower layer system, calculates the health status and mission information of this layer system and transmits it to the upper layer. For the space station space application system payload distributor, the existing digital achievements of the space station can be fully utilized, and the mathematical model achievements that have been successfully constructed can be used. This type of model has been verified by experiments and real data and has a high degree of credibility.

[0079] System information can be stored in a database based on a hierarchical design. Each layer of system information can include historical data (second information), current data (first information), and future prediction data (third information). Each layer should store sensor information, health status information, tasks existing in the layer, and completion status information. Considering the computing time overhead, two types of status information can be set. One is instant information, which responds quickly but roughly and can be fed back to other levels in a timely manner. The other is precise information, which responds slowly but accurately. The two states are updated and reported according to a certain mechanism. The sensor data of each layer is not synchronized to other layers, but after abstraction and organization, the simplified status information and model results are synchronized to other layers.

[0080] In some embodiments, the digital model includes a top layer and at least one subsystem layer. It can be used to monitor and control the health status and task completion of the entire spacecraft power distribution system in parallel, and continuously run the health status management program. When a new event occurs, a new task is generated, and the event includes dispatching a new task, failing an old task, detecting a fault, etc. The monitoring system provided in the embodiment of the present application performs autonomous operation and disposal of the newly generated task.

[0081] The top layer is the brain of the entire monitoring system, including system definition, scheduling mechanism, communication protocol, and data standard. The functions of the top layer include understanding the information sent by the space station space application system, executing the tasks sent by the space station space application system, distributing tasks according to the power consumption capacity of each load, and feeding back the current status to the space station space application system. Understanding the information sent by the space station and the power system includes information about priorities, such as giving priority to saving data, completing tasks, or maintaining its own safety in the event of a failure. Executing tasks sent by the space station mainly includes monitoring its own health and distributing load power consumption according to the instructions sent by the space station. Distributing tasks to each load includes the specific power consumption capacity of each load in the lower layer. Feedback of the current status to the space station includes the current health status and power distribution of the power distribution system at this layer.

[0082] Each subsystem layer has at least the following four functions: task execution function for this layer, task generation and distribution function for the lower layer, information feedback function for the upper layer, and function of generating new events. Among them, the higher subsystem layer should also have the ability to understand the task. The lowest subsystem layer is the component level. Each system layer has its own fault detection and diagnosis function.

[0083] Specifically, one subsystem layer corresponds to one power distributor. The highest layer is used to store multiple preset conditions, and to store the corresponding relationship between each preset condition in the multiple preset conditions and each fault in the multiple faults. For any subsystem layer in at least one subsystem layer, any subsystem layer is used to read multiple preset conditions from the highest layer, and to determine whether the first information, the second information, and the third information corresponding to the target power distributor satisfy any preset condition in the multiple preset conditions. The target power distributor is the power distributor corresponding to any subsystem layer. Any subsystem layer is also used to read the fault corresponding to any preset condition from the highest layer, and to predict the fault corresponding to any preset condition as a fault occurring in the target power distributor at the second moment.

[0084] That is to say, the fault detection and diagnosis functions of each subsystem layer can be matched with different preset conditions. According to the characteristics of the model and fault mode of this layer, the parameter type is pre-designed, the redundant sensor network of this layer is set, and the initial fault type and handling method are set in the model. This layer continuously reads sensor data, performs fault detection, diagnosis, isolation, and handling based on the set method, and handles subsequent faults in the form of a stack. When an unresolvable event is triggered, it is considered that the system cannot handle the current fault autonomously, triggering an emergency procedure or manual takeover.

[0085] It can be seen that this monitoring system is not a simple expert system, it has a certain learning ability. In some embodiments, this detection system can report the learning content to manual review and iteratively update the fault diagnosis system. The monitoring system continuously collects data of pre-set types and sources, regularly judges, analyzes, and reports sensor data of similar devices that are operating normally and have faults, and uses model methods to screen out k-top significant features. If the confidence rate is greater than the threshold, it is considered that a new fault feature has been discovered, and it can be reported and wait for manual confirmation to be written into the fault diagnosis system.

[0086] In some embodiments, any subsystem layer is also used to determine the fault type corresponding to the fault of the target distributor when a fault occurring at the second moment is predicted. Different fault types correspond to different fault handling strategies. Based on the fault type corresponding to the fault of the target distributor, determine the fault handling strategy for the target distributor. Based on the fault handling strategy for the target distributor, handle the target distributor.

[0087] In some embodiments, the spacecraft power distribution system may encounter hard errors and soft errors during the on-orbit operation phase: hard errors are physical damage to the device caused by hardware damage or defects. Once it occurs, it is difficult to correct remotely. It can generally be restored by switching spare parts. The main task of health management is accurate prediction and timely diagnosis. Soft errors are functional abnormalities or data errors caused by non-physical damage factors such as errors in program operation, software design defects, memory problems, electromagnetic interference, etc., including single-particle latching and flipping. They can be remotely corrected and restored to function through reconstruction, restart, software disposal and other methods. The main task of health management is. Therefore, hard errors and soft errors can be considered and handled separately. In addition to handling sudden failures as much as possible, the important task of health management is to reduce slow-changing failures and extend life by derating, identifying early failures, etc.

[0088] In this case, the fault type can be set to include a hardware fault type and a software fault type. The fault corresponding to the hardware fault type includes a fault caused by hardware damage to the corresponding distributor. The fault corresponding to the software fault type includes a fault caused by the actual running program of the corresponding distributor deviating from the preset running program. In addition, any distributor corresponds to at least one backup distributor among multiple distributors. The fault handling strategy for the fault corresponding to the hardware fault type may include switching the power supply device from the first distributor to the second distributor. The first distributor is a distribution device that has a hardware fault type fault among the multiple distribution devices determined by prediction. The second distributor is a backup distributor corresponding to the second distributor among the multiple distribution devices. The fault handling strategy for the fault corresponding to the software fault type includes restarting and / or initializing the third distributor. The third distributor is a distribution device that has a software fault type fault among the multiple distribution devices determined by prediction.

[0089] In some embodiments, long-life spacecraft including space stations generally use solar panels to generate electricity and lithium-ion batteries to store electricity. Considering the instability of the environment and the complexity of the load, the power supply may be unstable. Based on the monitoring system provided in the embodiment of the present application, the power supply can be dynamically adjusted according to the health status and risks of different load nodes, and more refined data can be fed back to the space station, so that the space station can better detect and handle faults, and more flexibly control the derating ratio and adjust the power supply power.

[0090] Moreover, the faults of the spacecraft power distribution system usually manifest as abnormal output power, increased internal resistance, reduced capacity, overvoltage, overcurrent, etc., and the measurable quantities mainly include output voltage, current, ambient temperature, and ambient radiation. Timely and accurate fault information can help the power supply temporarily shut down or reduce output when an abnormality occurs, temporarily isolate the faulty power supply, and avoid the spread of the fault until the abnormality disappears and the output is increased to normal again.

[0091] Based on the monitoring system provided in the embodiment of the present application, hierarchical power distribution and hierarchical management can be adopted for the spacecraft power distribution system. The system-level distributor controls the bus of each subsystem, and each subsystem-level distributor and power converter distributes and controls power for its own system. This power distribution method is very suitable for using the hierarchical management scheme proposed in the present invention. For faults such as local short circuits in equipment or transmission paths, the electrical parameters and environmental parameters of components, equipment vicinity, and each section of circuit cables can be measured. The power supply and distribution system fault classification can be divided into transient faults and cumulative faults; transient faults are mainly caused by single particle effects, etc., causing large fluctuations in the circuit for a short time, which can be solved by turning off the air switch, while adjusting the load to run the system with the lowest power consumption; cumulative faults are mainly caused by total dose effects and displacement damage, and the environmental radiation can be detected by an integrated radiation detector to assess the degree of damage and then assess the health risk of the device.

[0092] Therefore, by placing sensors at different locations in the payload power distribution box, detecting and recording electrical parameters and environmental parameters, predicting trend diagnosis can be performed based on the fault diagnosis model, discovering problems and assessing their severity, and handling them based on current priorities. The initial fault diagnosis system inputs the fault-prone locations, electrical parameters, and causal relationships of the faults in advance. During operation, the monitoring system can perform time series analysis and correlation analysis on sensors at each layer, and obtain the results to update the fault diagnosis system model.

[0093] In some embodiments, the monitoring system provided by the present invention further includes an information display platform, which is used to display the first information and / or the second information and / or the third information; and / or, to display the target fault and / or the fault handling strategy corresponding to the target fault; and / or, to display a preset condition editing page. The preset condition editing page is used to receive input preset conditions.

[0094] Specifically, the information display platform can display the full-level and component information of the spacecraft power distribution system, display the power of each payload in the lower layer, display the status of each system layer, warn of unhealthy and sub-healthy systems, and display the current tasks and execution status of the space application system of the space station.

[0095] The digital model and physical model included in the monitoring system provided in the embodiment of the present application can be established according to the existing engineering documents, and then optimized in combination with the actual health management needs. The existing engineering documents contain the composition and working principle of the spacecraft power distribution system, the connection topology and interface design, the communication paths and protocols of data and instructions, and the detailed design of each power supply and distribution subsystem and control subsystem, including principles, structures, functions, etc., as well as redundant design. Based on this, tools such as Dymo la can be used to build models, and test simulations of each component can be performed, and the model can be improved in combination with manual inspection. Drawing on the fault plans that have been imported into the knowledge base, the dependencies between elements in the model are completed, which facilitates the construction of a full system health management algorithm.

[0096] Figure 2 The method for updating the model in the detection system provided in the embodiment of the present application. The model includes a physical model and a digital model. For details, see Figure 2 , the embodiment of this application refers to the existing methods of building digital twins at home and abroad, and proposes a method for combining physical models and digital models for space application systems. In the construction and operation process, including the power distribution system, the accumulated system of standard documents such as product design and construction specifications, design instructions, research and development summaries, hazard analysis reports, interface data sheets, communication protocols, etc. are the basis for building a digital system knowledge base. Summarize, organize, code, and model the existing work and document content to generate background information in the knowledge base. Generate initial models of each level of the system based on the results generated by the MBSE (model-based systems engineering) model, and correct and improve the model by combining manual and automatic error correction. According to the existing content such as the on-orbit fault plans of each subsystem of the space station, set the status information, fault diagnosis and disposal methods in the system level. At the same time, set the model at the required level, extract the characteristics of the digital model and health management method of this level, and automatically update and expand the model as needed.

[0097] In some schemes, multiple embodiments of the present application can be combined, and the combined scheme can be implemented. Optionally, some operations in the process of each method embodiment are optionally combined, and / or the order of some operations is optionally changed. In addition, the execution order between the steps of each process is only exemplary and does not constitute a restriction on the execution order between the steps. There can also be other execution orders between the steps. It is not intended to indicate that the execution order is the only order in which these operations can be performed. A person of ordinary skill in the art will think of a variety of ways to reorder the operations described herein. In addition, it should be noted that the process details involved in a certain embodiment of this article are also applicable to other embodiments in a similar manner, or different embodiments can be used in combination.

[0098] In addition, some steps in the method embodiment may be equivalently replaced by other possible steps. Alternatively, some steps in the method embodiment may be optional and may be deleted in certain usage scenarios. Alternatively, other possible steps may be added to the method embodiment. Furthermore, the method embodiments may be implemented separately or in combination.

[0099] Through the description of the above implementation methods, technical personnel in the relevant field can clearly understand that for the convenience and simplicity of description, only the division of the above-mentioned functional modules is used as an example. In actual applications, the above-mentioned functions can be assigned to different functional modules as needed, that is, the internal structure of the system can be divided into different functional modules to complete all or part of the functions described above.

[0100] In the several embodiments provided in the present application, it should be understood that the disclosed systems and methods can be implemented in other ways. For example, the system embodiments described above are only schematic. For example, the division of the modules or units is only a logical function division. There may be other division methods in actual implementation, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of systems or units, which can be electrical, mechanical or other forms.

[0101] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit. The above-mentioned integrated unit may be implemented in the form of hardware or in the form of software functional units.

[0102] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a readable storage medium. Based on this understanding, the technical solution of the embodiment of the present application is essentially or the part that contributes or all or part of the technical solution can be embodied in the form of a software product, which is stored in a storage medium, including several instructions to enable a device (which can be a single-chip microcomputer, chip, etc.) or a processor (processor) to perform all or part of the steps of the method described in each embodiment of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM), random access memory (RAM), disk or optical disk and other media that can store program code.

[0103] The above contents are only specific implementation methods of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions within the technical scope disclosed in the present application shall be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A monitoring system for a spacecraft power distribution system, characterized in that: include: Physical models, databases and digital models; among them, The physical model is used to detect the spacecraft power distribution system at a first moment to obtain first information; the first information is the operation information of the spacecraft power distribution system at the first moment; the operation information includes environmental information of the environment in which the spacecraft power distribution system is located and configuration information of the spacecraft power distribution system; The database is used to store second information; the second information is obtained based on the physical model history to detect the spacecraft power distribution system; the second information includes the historical operation information of the spacecraft power distribution system; the physical model obtains the second information earlier than the first moment; The physical model is further used to predict third information based on the first information and the second information; the third information is the operation information of the spacecraft power distribution system at a second moment; the second moment is later than the first moment; The digital model is used to determine a target fault among multiple faults occurring in the spacecraft power distribution system at the second moment based on the first information, the second information and the third information satisfying a target preset condition among multiple preset conditions; wherein one fault among the multiple faults corresponds to at least one preset condition among the multiple preset conditions; and the target preset condition corresponds to the target fault.

2. The monitoring system according to claim 1, characterized in that: The spacecraft power distribution system includes multiple power distributors; the spacecraft includes at least one payload; one power distributor is used to supply power to one payload; the physical model includes a sensor network; the sensor network includes multiple sensors; for any one of the multiple power distributors, the any one power distributor corresponds to at least one sensor among the multiple sensors; the at least one sensor is used to detect the operating information of the any one power distributor.

3. The monitoring system according to claim 2, characterized in that: The environmental information of the environment in which the spacecraft power distribution system is located includes the environmental information of the environment in which the multiple power distributors are located; the environmental information of the environment in which any power distributor is located includes at least one of the temperature, humidity and air pressure of the environment in which any power distributor is located; The configuration information of the spacecraft power distribution system includes the configuration information of the multiple power distributors; the configuration information of any power distributor includes at least one of the input current value, input voltage value, internal resistance value, pressure resistance value, and output power value of any power distributor.

4. The monitoring system according to claim 3, characterized in that: The physical model also includes an environment model and a system component model; the first information includes first environment information and first configuration information; the second information includes second environment information and second configuration information; the third information includes third environment information and third configuration information; The sensor network is further used to detect the spacecraft power distribution system at a first moment to obtain the first environmental information and the first configuration information; The environment model is used to obtain the second environment information from the database, and determine the third environment information based on the first environment information and the second environment information; The environmental model is also used to store the determined third environmental information into the database; The system component model is used to obtain the second configuration information from the database, and determine the third configuration information based on the first configuration information and the second configuration information; The system component model is also used to store the determined third configuration information into the database.

5. The monitoring system according to claim 4, characterized in that: The digital model includes a top layer and at least one subsystem layer; wherein one subsystem layer corresponds to one power distributor; the top layer is used to store the plurality of preset conditions, and to store the corresponding relationship between each preset condition in the plurality of preset conditions and each fault in the plurality of faults; For any subsystem layer in the at least one subsystem layer; the any subsystem layer is used to read the multiple preset conditions from the highest layer, and determine that the first information, the second information, and the third information corresponding to the target distributor meet any preset condition in the multiple preset conditions; the target distributor is the distributor corresponding to the any subsystem layer; Any of the subsystem layers is further used to read the fault corresponding to any of the preset conditions from the highest layer, and predict the fault corresponding to any of the preset conditions as a fault occurring in the target power distributor at the second moment.

6. The monitoring system according to claim 5, characterized in that: Any of the subsystem layers is also used to: In the case where it is predicted that the target electrical distributor has a fault at the second moment, determining a fault type corresponding to the fault of the target electrical distributor; different fault types correspond to different fault handling strategies; Determining a fault handling strategy for the target electrical distributor based on a fault type corresponding to the fault of the target electrical distributor; Based on the fault handling strategy for the target power distributor, the target power distributor is handled.

7. The monitoring system according to claim 6, characterized in that: The fault types include hardware fault types and software fault types; the faults corresponding to the hardware fault types include faults caused by hardware damage to the corresponding distributor; the faults corresponding to the software fault types include faults caused by the actual operating program deviating from the preset operating program to the corresponding distributor.

8. The monitoring system according to claim 7, characterized in that: Any of the power distributors corresponds to at least one standby power distributor among the multiple power distributors; The fault handling strategy for the fault corresponding to the hardware fault type includes switching the power supply equipment from a first distributor to a second distributor; the first distributor is a distribution device among the multiple distribution devices predicted to have the fault of the hardware fault type; the second distributor is a backup distributor corresponding to the second distributor among the multiple distribution devices.

9. The monitoring system according to claim 8, characterized in that: The fault handling strategy for the fault corresponding to the software fault type includes restarting and / or initializing a third power distribution device; the third power distribution device is a distribution device among the multiple distribution devices predicted to have a fault of the software fault type.

10. The monitoring system according to claim 9, characterized in that: It also includes an information display platform, which is used to: displaying the first information and / or the second information and / or the third information; and / or, Display the target fault and / or the fault handling strategy corresponding to the target fault; and / or, A preset condition editing page is displayed; the preset condition editing page is used to receive the input of the multiple preset conditions.

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