On-orbit anomaly monitoring and fault co-processing system for manned spacecraft

Abstract

The invention provides an on-orbit anomaly monitoring and fault cooperative processing system for a manned spacecraft. The on-orbit anomaly monitoring and fault cooperative processing system comprises a management configuration module, a core service module and a monitoring cooperative client module, a manned spacecraft model configuration unit of the management configuration module configures model parameter information of the manned spacecraft; the telemetry data configuration unit configures telemetry data required for judging fault information of the manned spacecraft; the algorithm configuration unit configures a fault algorithm; the document configuration unit configures shared information required for processing the fault processing information; a telemetering data processing unit of the core service module receives real-time telemetering data of the manned spacecraft; the algorithm service unit receives a fault algorithm; the fault interpretation unit determines the operation state of the manned spacecraft based on a fault algorithm, the real-time telemetry data and the model parameter information; the collaboration unit provides shared information for the monitoring collaboration client modules according to the operation states, sharing of information of the monitoring collaboration client modules is achieved, and the efficiency of collaboration processing is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of on-orbit operation of manned spacecraft, and in particular to a system for on-orbit abnormality monitoring and fault coordinated handling of manned spacecraft. Background Art

[0002] During the in-orbit operation of manned spacecraft, there will be many abnormal situations, such as cabin pressure alarm, collision alarm, fire alarm and other abnormal alarm situations. After the ground support personnel receive the abnormal alarm information through telemetry signals, they need to perform alarm interpretation and fault handling operations. In this process, they will face problems such as large amount of data and many types of information. In addition, due to the different units to which the ground support personnel belong and the different tasks they are responsible for, the ground support personnel are usually in different work locations.

[0003] At present, various ground support centers generally participate in the above-mentioned fault handling through voice interaction. When participating in fault handling, support personnel in various positions need to query the required information from documents and related business systems based on the fault judgment results. When the amount of information that support personnel in various positions need to share is large or the number of information sources required for the fault handling process is large, the current voice interaction method has low collaborative efficiency and cannot efficiently share information data. Summary of the invention

[0004] The present invention provides a system for on-orbit abnormality monitoring and fault collaborative handling of a manned spacecraft, which is used to solve the technical problem that the prior art cannot efficiently and collaboratively handle abnormalities during spacecraft operation.

[0005] On the one hand, the present invention provides a system for on-orbit abnormality monitoring and fault collaborative handling of manned spacecraft, including a management configuration module, a core service module and a monitoring collaborative client module;

[0006] The management configuration module includes a manned spacecraft model configuration unit, a telemetry data configuration unit, an algorithm configuration unit and a document configuration unit; wherein,

[0007] The manned spacecraft model configuration unit is used to configure model parameter information of the manned spacecraft;

[0008] The telemetry data configuration unit is used to configure the real-time telemetry data required for determining the fault information of the manned spacecraft;

[0009] The algorithm configuration unit is used to configure the fault algorithm;

[0010] The document configuration unit is used to configure the shared information required for processing fault information;

[0011] The core service module includes a telemetry data processing unit, an algorithm service unit, a fault interpretation unit and a coordination unit; wherein,

[0012] The telemetry data processing unit is used to receive real-time telemetry data of the manned spacecraft;

[0013] The algorithm service unit is used to receive the fault algorithm;

[0014] The fault judgment unit is used to determine the operating state of the manned spacecraft based on the fault algorithm, the real-time telemetry data and the model parameter information;

[0015] The collaboration unit is used to provide the monitoring collaboration client module with shared information required for processing fault information according to the operating status;

[0016] The monitoring collaborative client module includes a fault collaborative processing unit;

[0017] The fault collaborative processing unit is used to receive the shared information.

[0018] According to a system for on-orbit abnormality monitoring and fault coordinated handling of a manned spacecraft provided by the present invention, the management configuration module further includes a simulation data configuration unit for configuring telemetry simulation data of the manned spacecraft; the telemetry simulation data is data generated by simulating the operating state of the manned spacecraft in an actual operating environment when it is in orbit;

[0019] The monitoring collaborative client module also includes a telemetry data real-time monitoring unit and a trend curve display unit;

[0020] The telemetry data real-time monitoring unit is used to generate a corresponding simulation curve and a real-time curve according to the telemetry simulation data and the real-time telemetry data;

[0021] The trend curve display unit is used to display the real-time curve and the simulation curve.

[0022] According to a system for on-orbit abnormality monitoring and fault collaborative handling of manned spacecraft provided by the present invention, the monitoring collaborative client module also includes a fault position display unit for displaying the position of the manned spacecraft where the fault state is located in the operating state.

[0023] According to a system for on-orbit abnormality monitoring and coordinated fault handling of a manned spacecraft provided by the present invention, the fault position display unit is used to determine the actual fault position of the manned spacecraft corresponding to the fault state, and determine the model fault position in the model parameter information corresponding to the fault state based on the correspondence between the model parameter information and the position of the manned spacecraft, and mark the model fault position.

[0024] According to a system for on-orbit abnormality monitoring and coordinated fault handling of manned spacecraft provided by the present invention, the manned spacecraft model configuration unit is used to establish a parameter table corresponding to the parameter type in a preset database according to the parameter type of the model parameter information, and store the model parameter information in the corresponding parameter table.

[0025] According to a system for on-orbit abnormality monitoring and coordinated fault handling of manned spacecraft provided by the present invention, the telemetry data configuration unit is used to establish a fault table corresponding to the fault type in a preset database according to the fault type of the fault information, and store the fault information in the corresponding fault table.

[0026] According to a system for on-orbit anomaly monitoring and coordinated fault handling of a manned spacecraft provided by the present invention, the simulation data configuration unit is used to configure a data file, and the data file is used to store telemetry simulation data.

[0027] According to a system for on-orbit anomaly monitoring and coordinated fault handling of a manned spacecraft provided by the present invention, the document configuration unit is used to configure a fault file on a preset server, and the fault file is used to store fault handling information.

[0028] According to a system for on-orbit abnormality monitoring and fault collaborative handling of manned spacecraft provided by the present invention, the collaborative unit is used to use Web Socket to send fault sharing information to a server, and send the fault sharing information to a monitoring collaborative client module via the server.

[0029] According to a system for on-orbit anomaly monitoring and coordinated fault handling of a manned spacecraft provided by the present invention, the model parameter information includes a three-dimensional model, coordinate information, regional equipment information and a panoramic picture.

[0030] The present invention provides a system for on-orbit abnormality monitoring and coordinated fault handling of manned spacecraft. The management configuration module may include a manned spacecraft model configuration unit, a telemetry data configuration unit, an algorithm configuration unit and a document configuration unit. The manned spacecraft model configuration unit is used to configure model parameter information of the manned spacecraft, and is used to provide reference information for ground support personnel during the fault handling process; the telemetry data configuration unit is used to configure real-time telemetry data required for judging the fault information of the manned spacecraft, which is used for fault interpretation; the algorithm configuration unit is used to configure the fault algorithm, and realizes fault judgment based on the algorithm; the coordination unit is used to provide the monitoring coordination client module with the shared information required for processing the fault information according to the operating state; the fault collaborative processing unit is used to receive the shared information, so as to realize the efficient sharing of shared information for technical support personnel in various positions at various work locations, thereby improving the efficiency of technical support personnel at various work locations in collaboratively handling manned spacecraft faults. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the technical solutions in the present invention or the prior art, a brief introduction will be given below to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0032] Figure 1 It is a structural diagram of a system for on-orbit abnormality monitoring and coordinated fault handling of a manned spacecraft provided by an embodiment of the present invention;

[0033] Figure 2 It is a schematic diagram of the architecture of a system for on-orbit anomaly monitoring and fault collaborative handling of manned spacecraft provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] Figure 1 It is a structural diagram of a system for on-orbit abnormality monitoring and coordinated fault handling of a manned spacecraft provided by an embodiment of the present invention; Figure 2 It is a schematic diagram of the architecture of a system for on-orbit anomaly monitoring and fault collaborative handling of manned spacecraft provided by an embodiment of the present invention.

[0036] See also Figure 1 and Figure 2 The on-orbit abnormality monitoring and fault collaborative handling system 10 for manned spacecraft may include a management configuration module 20, a core service module 30 and a monitoring collaborative client module 40.

[0037] The management configuration module 20 may include a manned spacecraft model configuration unit 201 , a telemetry data configuration unit 202 , an algorithm configuration unit 204 and a document configuration unit 205 .

[0038] The manned spacecraft model configuration unit 201 is used to configure model parameter information of the manned spacecraft. The model parameter information can be used to provide reference for ground support personnel during the fault handling process.

[0039] The telemetry data configuration unit 202 is used to configure the real-time telemetry data required for judging the fault information of the manned spacecraft. The real-time telemetry data here can refer to the configuration of telemetry data codes related to various faults, which can be used for fault judgment, such as temperature, pressure, voltage, etc. Each telemetry data has a specific code, which is used to quickly locate and identify in the telemetry data stream, that is, to configure the real-time telemetry data code required for fault information. The above telemetry data corresponds to the fault type. Similarly, each fault type has a unique code, such as "cabin pressure alarm", "collision alarm", "fire alarm", etc. These codes are used to quickly identify the fault type.

[0040] The algorithm configuration unit 204 is used to configure the fault algorithm. The configured fault algorithm can be used for fault interpretation. It is understandable that the fault rules can be set in advance, and then the fault algorithm can be used to determine whether a fault exists and the type of fault according to the fault rules. Different types of faults may have different algorithms. For example, for cabin pressure faults, an algorithm for calculating the pressure drop rate needs to be implemented; for another example, under cabin pressure faults, there are various calculation requirements for key pressure points, such as an algorithm for evacuation pressure, an algorithm for minimum pressure, etc.

[0041] The document configuration unit 205 is used to configure the shared information required for processing fault information. The shared information may refer to various documents related to the fault for solving the fault, and may also be understood as a solution to the fault, which is used to quickly provide documents to ground support personnel when handling the fault.

[0042] The core service module 30 may include a telemetry data processing unit 301 , an algorithm service unit 302 , a fault judgment unit 303 and a coordination unit 304 .

[0043] The telemetry data processing unit 301 is used to receive real-time telemetry data from the manned spacecraft and can cache the telemetry data within a preset time period to provide data for fault diagnosis.

[0044] The algorithm service unit 302 is used to receive the fault algorithm. That is, the algorithm service unit 302 can call the fault algorithm configured by the algorithm configuration unit 204.

[0045] The fault judgment unit 303 is used to determine the operating state of the manned spacecraft based on the fault algorithm, the real-time telemetry data and the model parameter information. For example, the fault judgment unit 303 can compare the real-time telemetry data with the corresponding preset threshold according to the fault algorithm to determine whether it exceeds the preset threshold to determine the operating state, and can also associate the operating state with the corresponding model parameter information.

[0046] The collaboration unit 304 is used to provide the monitoring collaboration client module 40 with the shared information required to process fault information according to the operating status. That is to say, when a fault state occurs in the operating state, shared information such as various documents related to the fault, the fault type, and the solution corresponding to the fault type can be provided. Of course, in addition to providing fault sharing information, non-fault information in the operating state can also be provided, that is, when there is no fault state, the operating state of the spacecraft can also be shared. Shared information can also be understood as a fault handling process. In addition, a control interface for the fault handling process can also be provided. The control interface may include button operations such as start processing, confirm, and push information. After receiving the technician's operations on these buttons, the synchronization of shared information to each monitoring collaboration client module 40 can be completed.

[0047] The monitoring cooperation client module 40 may include a fault cooperation processing unit 403. The number of monitoring cooperation client modules 40 is generally multiple and arranged at different working locations.

[0048] The fault collaborative processing unit 403 is used to receive shared information.

[0049] In this embodiment, the management configuration module 20 may include a manned spacecraft model configuration unit 201, a telemetry data configuration unit 202, an algorithm configuration unit 204 and a document configuration unit 205. The manned spacecraft model configuration unit 201 is used to configure the model parameter information of the manned spacecraft, so as to provide reference information for ground support personnel during the fault handling process; the telemetry data configuration unit 202 is used to configure the real-time telemetry data required for judging the fault information of the manned spacecraft, which is used for fault interpretation; the algorithm configuration unit 204 is used to configure the fault algorithm, and realize fault judgment based on the algorithm; the collaboration unit 304 is used to provide the monitoring collaboration client module 40 with the shared information required for processing the fault information according to the operating status; the fault collaborative processing unit 403 is used to receive the shared information, so as to realize the efficient sharing of shared information for the technical support personnel in each position at each work location, thereby improving the efficiency of the technical support personnel at each work location in collaboratively handling the manned spacecraft faults.

[0050] In an embodiment of the present specification, the management configuration module 20 may further include a simulation data configuration unit 203 for configuring telemetry simulation data of the manned spacecraft; the telemetry simulation data is data generated by simulating the operating state of the manned spacecraft in the actual operating environment of the on-orbit operation;

[0051] The monitoring cooperation client module 40 may also include a telemetry data real-time monitoring unit 401 and a trend curve display unit 404;

[0052] The telemetry data real-time monitoring unit 401 is used to generate a corresponding simulation curve and a real-time curve according to the telemetry simulation data and the real-time telemetry data;

[0053] The trend curve display unit 404 is used to display real-time curves and simulation curves.

[0054] In this embodiment, the telemetry simulation data may refer to data generated by simulating the operating status of a manned spacecraft in an actual environment in which the manned spacecraft is operating on orbit through simulation software on the ground, and the actual environment is the same as the actual environment in which the manned spacecraft is operating on orbit. The telemetry simulation data can be used to predict the possible performance of the spacecraft in the actual environment. The telemetry data real-time monitoring unit 401 is used to generate a corresponding simulation curve and a real-time curve according to the telemetry simulation data and the real-time telemetry data, respectively, and the trend curve display unit 404 is used to display the real-time curve and the simulation curve, so as to compare the simulation curve with the real-time curve and to find faults of the manned spacecraft.

[0055] The horizontal axis of the simulation curve and the real-time curve can be expressed as time, and the vertical axis can be expressed as parameter value. By comparing the similarity between the real-time curve and the simulation curve, it can be judged whether the actual operating status of the spacecraft meets expectations. If the similarity between the real-time curve and the simulation curve is lower than the preset similarity threshold, it may indicate a potential fault or abnormality. This comparison can help operators make more accurate decisions, such as whether operating parameters need to be adjusted or whether troubleshooting is needed.

[0056] The telemetry data real-time monitoring unit 401 can also generate alarm information when a fault state occurs, for example, the alarm prompt can be given by outputting prompt colors, lights, sounds, etc. The lights and sounds need to be configured with corresponding hardware peripherals.

[0057] In an embodiment of the present specification, the monitoring cooperative client module 40 may further include a fault location display unit 402 for displaying the location of the manned spacecraft where the fault state is located in the operating state.

[0058] In this embodiment, the fault location display unit 402 is used to display the location of the manned spacecraft where the fault state is located, so as to facilitate the technicians to quickly determine the fault location of the manned spacecraft.

[0059] In one embodiment of the present specification, the fault location display unit 402 is used to determine the actual fault location of the manned spacecraft corresponding to the fault state, and determine the model fault location in the model parameter information corresponding to the fault state based on the correspondence between the model parameter information and the position of the manned spacecraft, and mark the model fault location.

[0060] In this embodiment, the model fault position in the model parameter information corresponding to the fault state is determined, and the model fault position is marked, so that the position of the fault can be displayed very vividly and intuitively, thereby improving the efficiency of technicians in handling faults. The model parameter information may include a two-dimensional model screen and / or a three-dimensional model screen of a manned spacecraft. The fault position may be displayed in the form of a two-dimensional model screen or a three-dimensional model screen of a manned spacecraft.

[0061] Specifically, the two-dimensional image is a plan view of the unfolded cabin. The shapes of the plan views of different cabin sections are different. For example, the unfolded column section is a rectangle, and the unfolded node cabin is a fan. The plan view is divided into finer areas as needed, and these areas have their own coordinates. The on-orbit spacecraft itself is also divided into different areas according to business needs, and these areas also have their own coordinates. The area division of the two-dimensional image is different from the area division of the spacecraft itself. In order to realize the display of the alarm area, the two need to be matched in the configuration module. When a fault occurs in the on-orbit spacecraft, the on-orbit area is determined based on the on-orbit coordinates, and then matched to the area of ​​the two-dimensional image, so that the fault area of ​​the two-dimensional image can be highlighted. The three-dimensional implementation method can refer to the above-mentioned two-dimensional implementation method, which will not be repeated here.

[0062] In one embodiment of the present specification, the manned spacecraft model configuration unit 201 is used to establish a parameter table corresponding to the parameter type in a preset database according to the parameter type of the model parameter information, and store the model parameter information in the corresponding parameter table.

[0063] In this embodiment, a parameter table corresponding to the parameter type is established in the preset database, and the model parameter information is stored in the corresponding parameter table, which is very simple and convenient. For example, the regional coordinate information configures the characteristic coordinate points of the region according to the shape of the region, such as a rectangular region, storing the coordinates of the four vertices of the region, and the fan-shaped region stores the numbers of different blocks; the three-dimensional model configures the three-dimensional file of the model; the panorama configures the panoramic pictures of different regions; the regional equipment configures the equipment number installed in each region. The UI can be used to provide an operation interface for various information configuration modifications.

[0064] In one embodiment of the present specification, the telemetry data configuration unit 202 is used to establish a fault table corresponding to the fault type in a preset database according to the fault type of the fault information, and store the fault information in the corresponding fault table.

[0065] In this embodiment, a fault table corresponding to the fault type is established in a preset database, and the fault information is stored in the corresponding fault table, which is very simple and convenient. The configuration can be completed using the UI.

[0066] In one embodiment of the present specification, the simulation data configuration unit 203 is used to configure a data file, and the data file is used to store telemetry simulation data.

[0067] In this embodiment, the simulation data configuration unit 203 is used to configure a data file, and the data file is used to store telemetry simulation data, which is very simple and convenient. The format of the data file can be csv format or other formats. A library table corresponding to the data file is established in the database, and the library table can store configuration information such as the data file name, corresponding fault and telemetry code.

[0068] In an embodiment of the present specification, the document configuration unit 205 is used to configure a fault file on a preset server, and the fault file is used to store fault handling information.

[0069] In this embodiment, the document configuration unit 205 is used to configure a fault file on a preset server, and the fault file is used to store fault handling information, which is very simple and convenient. The document entity can be stored on the file server, and the document information can be stored in a database table. This module provides a UI to upload documents and set various document information, such as setting the document name, content type, etc.

[0070] In one embodiment of the present specification, the collaboration unit 304 is used to send the fault sharing information to the server using Web Socket, and send the fault sharing information to the monitoring collaboration client module 40 via the server.

[0071] In this embodiment, the collaboration unit 304 is used to send the fault sharing information to the server by using Web Socket, and then send the fault sharing information to the monitoring collaboration client module 40 via the server, which is very efficient.

[0072] In one embodiment of the present specification, the model parameter information may include a three-dimensional model, coordinate information, regional device information, and a panoramic picture.

[0073] In this embodiment, the model parameter information may include a three-dimensional model, coordinate information, regional equipment information and a panoramic picture, so as to intuitively display the location of the manned spacecraft where the fault is located, which is conducive to technical support personnel to solve the fault more quickly.

[0074] 3D model: refers to the three-dimensional geometric model of a spacecraft, which can show the detailed shape and structure of the spacecraft in computer-aided design (CAD) software or other 3D visualization tools. The 3D model can help technicians understand the physical layout of the spacecraft, including the spatial location of various components and systems.

[0075] Coordinate information: refers to the coordinate position information of various areas or components inside the spacecraft. These coordinate information can be two-dimensional (such as X, Y coordinates in a plan view) or three-dimensional (such as X, Y, Z coordinates) and are used to accurately locate specific locations inside the spacecraft. This is particularly important for fault diagnosis because it can help quickly determine the exact location where the fault occurred.

[0076] Regional equipment information: refers to detailed information about the equipment and components installed in each area of ​​the spacecraft. This includes the equipment model, function, status, and their installation location in the spacecraft. This information helps to quickly identify the affected equipment and take appropriate measures when a failure occurs.

[0077] Panoramic images: refers to panoramic images of the interior of the spacecraft, which can provide visual references inside the spacecraft and help technicians understand the internal layout of the spacecraft more intuitively. Panoramic images can be actual photos or images generated by 3D model rendering.

[0078] The above model parameter information together constitutes a comprehensive information platform, enabling ground support personnel to quickly and accurately understand and respond to fault conditions when a spacecraft fails. With these detailed model parameter information, technicians can more effectively perform fault diagnosis, decision support and collaborative disposal.

[0079] Combine the following Figure 2 The present invention is further described. The management configuration module 20 is implemented using a B / S architecture, and provides entry and storage of a manned spacecraft model configuration unit 201, a telemetry data configuration unit 202, a simulation data configuration unit 203, an algorithm configuration unit 204, and a document configuration unit 205 of the manned spacecraft.

[0080] The core service module 30 performs telemetry data processing unit 301, algorithm service unit 302, fault judgment unit 303, and collaboration unit 304. The telemetry data processing unit 301 uses a separate data collection thread to receive telemetry data related to monitoring alarms through the telemetry data interface. The algorithm service unit 302 performs algorithm processing through the algorithm configuration unit 204 preset by the management configuration module 20 and the data provided by the telemetry data configuration unit 202. The fault judgment unit 303 matches fault parameters according to the calculation results provided by the algorithm service unit 302 and the simulation data preset by the simulation data configuration unit 203 and the fault branch data, and provides the client program with the fault matching results and the fault handling information related to the fault through the front-end interface according to the fault matching results. The collaboration unit 304 uses message lists, document caches, and WebSockets to provide real-time sending and receiving of one-to-one or one-to-many messages and documents for each monitoring collaboration client module 40.

[0081] The monitoring collaborative client module 40 uses a desktop version of the graphical client to receive the telemetry data provided by the core service module 30 through WebSocket in real time for real-time monitoring, and draws a trend curve of the telemetry data, receives the space station fault location information provided by the algorithm service unit 302 and displays it visually, and receives fault information and document materials.

[0082] The management configuration module 20 can be configured by the administrator user through the UI interface. The monitoring collaborative client module 40 can be used for reference by ground support personnel. The management configuration module 20 can store information in a relational database. The core service module 30 can read information from the relational database. The core service module 30 can also obtain real-time telemetry data. The real-time database is used to store real-time data closely related to the operating status of the spacecraft, which is essential for monitoring the health of the spacecraft, quickly responding to abnormal situations, and performing fault diagnosis. For example, telemetry data, which are real-time measurement data sent back to the ground from the spacecraft, include parameters such as temperature, pressure, voltage, current, attitude, position, speed, etc. Telemetry data is used to monitor the operating status of the spacecraft and detect abnormalities in a timely manner. Status information: the current status of each system and component of the spacecraft, such as status information such as on, off, fault, warning, etc. Event log: records all important events and operations that occur in the spacecraft, including system startup, shutdown, abnormal alarm, fault handling, etc. Environmental data: data on the external environment of the spacecraft, such as space radiation levels, temperature, micrometeoroid impact, etc.

[0083] In summary, the present invention uniformly configures various types of data related to the on-orbit operation of manned spacecraft through the management configuration module, and automatically interprets fault alarms through the core service module, providing the alarm-related parameters, various information and documents required for fault handling for the handling work, thereby improving the efficiency of fault judgment and fault handling. The present invention provides unified and synchronized alarm parameters and fault-related information to relevant personnel of the monitoring collaborative client module in different ground support centers through a collaborative unit, and provides a solution for real-time interactive information and documents at various locations, thereby avoiding the need for multi-line operations by ground support personnel during joint handling, thereby improving handling efficiency.

[0084] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, i.e., they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Those of ordinary skill in the art may understand and implement it without creative effort.

[0085] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods of each embodiment or some parts of the embodiment.

[0086] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A system for monitoring anomalies and coordinating faults of manned spacecraft on orbit, characterized in that: Includes management configuration module, core service module and monitoring collaborative client module; The management configuration module includes a manned spacecraft model configuration unit, a telemetry data configuration unit, an algorithm configuration unit and a document configuration unit; wherein, The manned spacecraft model configuration unit is used to configure model parameter information of the manned spacecraft; The telemetry data configuration unit is used to configure the real-time telemetry data required for determining the fault information of the manned spacecraft; The algorithm configuration unit is used to configure the fault algorithm; The document configuration unit is used to configure the shared information required for processing fault information; The core service module includes a telemetry data processing unit, an algorithm service unit, a fault interpretation unit and a coordination unit; wherein, The telemetry data processing unit is used to receive real-time telemetry data of the manned spacecraft; The algorithm service unit is used to receive the fault algorithm; The fault judgment unit is used to determine the operating state of the manned spacecraft based on the fault algorithm, the real-time telemetry data and the model parameter information; The collaboration unit is used to provide the monitoring collaboration client module with shared information required for processing fault information according to the operating status; The monitoring collaborative client module includes a fault collaborative processing unit; The fault collaborative processing unit is used to receive the shared information.

2. The system for on-orbit abnormality monitoring and fault coordinated handling of manned spacecraft according to claim 1 is characterized in that: The management configuration module also includes a simulation data configuration unit for configuring telemetry simulation data of the manned spacecraft; the telemetry simulation data is data generated by simulating the operating state of the manned spacecraft in the actual operating environment of the on-orbit operation; The monitoring collaborative client module also includes a telemetry data real-time monitoring unit and a trend curve display unit; The telemetry data real-time monitoring unit is used to generate a corresponding simulation curve and a real-time curve according to the telemetry simulation data and the real-time telemetry data; The trend curve display unit is used to display the real-time curve and the simulation curve.

3. The system for on-orbit abnormality monitoring and fault coordinated handling of manned spacecraft according to claim 1 is characterized in that: The monitoring cooperative client module further comprises a fault position display unit for displaying the position of the manned spacecraft where the fault state is located in the operating state.

4. The system for on-orbit abnormality monitoring and fault coordinated handling of manned spacecraft according to claim 3 is characterized in that: The fault position display unit is used to determine the actual fault position of the manned spacecraft corresponding to the fault state, and determine the model fault position in the model parameter information corresponding to the fault state according to the correspondence between the model parameter information and the position of the manned spacecraft, and mark the model fault position.

5. The system for on-orbit abnormality monitoring and fault coordinated handling of manned spacecraft according to claim 1, characterized in that: The manned spacecraft model configuration unit is used to establish a parameter table corresponding to the parameter type in a preset database according to the parameter type of the model parameter information, and store the model parameter information in the corresponding parameter table.

6. The system for on-orbit abnormality monitoring and fault coordinated handling of manned spacecraft according to claim 1, characterized in that: The telemetry data configuration unit is used to establish a fault table corresponding to the fault type in a preset database according to the fault type of the fault information, and store the fault information in the corresponding fault table.

7. The system for on-orbit abnormality monitoring and fault coordinated handling of manned spacecraft according to claim 2, characterized in that: The simulation data configuration unit is used to configure a data file, and the data file is used to store telemetry simulation data.

8. The system for on-orbit abnormality monitoring and fault coordinated handling of manned spacecraft according to claim 1, characterized in that: The document configuration unit is used to configure a fault file on a preset server, and the fault file is used to store fault processing information.

9. The system for on-orbit abnormality monitoring and fault coordinated handling of manned spacecraft according to claim 1, characterized in that: The collaboration unit is used to send the fault sharing information to the server by using Web Socket, and send the fault sharing information to the monitoring collaboration client module via the server.

10. The system for on-orbit abnormality monitoring and fault coordinated handling of manned spacecraft according to claim 1, characterized in that: The model parameter information includes a three-dimensional model, coordinate information, regional equipment information and a panoramic picture.

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