Spacecraft health state monitoring platform based on digital twinning and operation method thereof

Abstract

The invention belongs to the technical field of spacecraft health state monitoring, and particularly relates to a spacecraft health state monitoring platform based on digital twinning and an operation method thereof. The sensing layer is used for monitoring body data and environment data; the data layer is used for ensuring high-precision data acquisition of operation accuracy, high-speed data transmission of interaction real-time performance and full-life-cycle data management of access reliability; the operation layer is used for realizing the functions of system cognition, system diagnosis, state prediction and collaborative decision; and the expression layer is used for realizing a visual visualization effect of the state of the spacecraft. According to the invention, multi-source data, multi-scale modeling and intelligent decision technologies are integrated, and real-time monitoring and closed-loop management of the health state of the spacecraft structure are realized.

Description

Technical Field

[0001] The present invention belongs to the technical field of spacecraft health status monitoring, and specifically relates to a spacecraft health status monitoring platform based on digital twins and an operation method thereof. Background Art

[0002] To achieve condition monitoring, reuse maintenance, and life assessment throughout the spacecraft's lifecycle, it is urgent to establish an autonomous and controllable spacecraft structural health status technology system to lay the technical foundation for ensuring the long-term stable operation of spacecraft on orbit and extending their service life. However, due to the complex and uncertain loads that spacecraft experience in space, it is very difficult to accurately identify structural loads, accurately detect damage, perform high-quality repairs, and evaluate their reusability. Traditional spacecraft health management suffers from problems such as data fragmentation, delayed diagnosis, and reliance on experience in decision-making. Therefore, building a digital twin platform for spacecraft health status monitoring and a full lifecycle management system covering "condition perception - intelligent diagnosis - predictive decision-making - visual interaction" can provide core tools for spacecraft health management throughout its lifecycle. This has significant economic benefits and strategic value and is of great significance for promoting the structural intelligence of spacecraft. Summary of the Invention

[0003] The present invention provides a spacecraft health status monitoring platform based on digital twins, which integrates multi-source data, multi-scale modeling and intelligent decision-making technology to realize real-time monitoring and closed-loop management of the spacecraft structural health status.

[0004] The present invention provides an operating method of a spacecraft health status monitoring platform based on digital twin, which is used to operate a spacecraft health status monitoring platform based on digital twin.

[0005] The present invention is achieved through the following technical solutions: A digital twin-based spacecraft health status monitoring platform, comprising a perception layer, a data layer, a computing layer, and a presentation layer; The perception layer is used to monitor body data and environmental data; The data layer is used to ensure high-precision data collection to ensure computational accuracy, high-speed data transmission to ensure interactive real-time performance, and full-lifecycle data management to ensure access reliability. The computing layer is used to realize the functions of system cognition, system diagnosis, state prediction, and collaborative decision-making; The expression layer is used to achieve an intuitive visualization effect of the spacecraft status.

[0006] Furthermore, the platform interface includes a title bar, a home page, a secondary home page, a special page, and sub-pages; The title bar includes a search box, a return to home page, a system settings icon, a minimized window icon, a close software icon, and a paging control for logging in and out of accounts; The search box is used to search the entire platform database; The return homepage is used for users to view the global status; The login account-logout account paging control is used to ensure the security of platform data.

[0007] Furthermore, the homepage reflects the spacecraft operation status information by setting different background colors; Among them, the green background indicates that the operating status is good; the yellow background indicates that there are moderately damaged parts in the spacecraft - requiring repair / forced landing; the red background indicates that there are severely damaged parts in the spacecraft - requiring repair / forced landing; they are arranged from high to low according to the danger level.

[0008] Furthermore, the secondary homepage is the jump interface after clicking the spacecraft on the homepage; Displays all information components contained in the spacecraft, including the finite element model of the spacecraft; the three-dimensional schematic diagram of the spacecraft; the status and quantity of spacecraft data transmission; detailed information about the spacecraft; additional functions include displaying time and date, and component retrieval.

[0009] Furthermore, the topic pages include a real-time evolution page, an event log page, a detection process page, and a repair process page; The real-time evolution page is the page that jumps to when clicking on the secondary homepage component function module: it reflects the spacecraft; The real-time evolution page includes event logs, inspection process library, maintenance process library, and performance evaluation; The event log page displays the historical data of the component, including flight log, repair log, production log and scrap log; The inspection process page integrates an inspection process library, which lists offline inspection methods for different components and different types of damage. Users can access the database by selecting a component or damage type, or jump to this page through the inspection suggestions in the event log page. Users can modify the data in the library and create and delete data entries. The repair process page integrates a repair process library, which records the repair methods that should be taken for different components and different types of damage. Other functions are similar to the inspection process page.

[0010] Furthermore, the subpages include a flight log subpage, a repair log subpage, a production log subpage, and a scrap log subpage; The flight log subpage analyzes past data damage and provides corresponding offline inspection and repair suggestions. This page is searched by time and includes an overall analysis: a finite element model diagram of the spacecraft during that period; real-time line or color charts of stress, strain, temperature distribution, and vibration; a damage evolution diagram and damage evolution analysis; and the location, type, and size of the damage on the spacecraft. This provides two functional blocks: offline inspection methods and repair process methods. Clicking either block automatically searches the digital twin platform database for the most matching inspection process library and repair process library data. The repair log subpage records past component repair data and performs performance evaluation, life prediction, and reusability evaluation on the repaired components. This page displays a component repair performance evaluation chart, a life prediction curve chart, and a component reuse confidence evaluation. It can also be searched by time. The production log sub-page records the factory information of the component, including factory performance, processing plant, price and model; The scrapping log subpage records the scrapping history of the component, including failure behavior analysis, working hours and number of repairs.

[0011] An operating method for a digital twin-based spacecraft health status monitoring platform, wherein the operating method uses the digital twin-based spacecraft health status monitoring platform as described above, and the operating method is specifically as follows: Collect the overall operational status data of the spacecraft and detailed information at the component level in real time through the sensor network to form a basic data layer; Based on physical models such as finite element analysis and data-driven models, high-precision digital twins are constructed to dynamically simulate the on-orbit behavior of spacecraft and achieve synchronous mapping of virtual and real states; Identify potential damage through structural damage detection methods, optimize repair solutions, and drive dynamic evolution processes; Integrate multi-source data to achieve comprehensive performance evaluation and output maintenance and resource optimization suggestions.

[0012] The above-mentioned monitoring platform is applied in the field of spacecraft health status monitoring.

[0013] A computer device includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the platform described above is implemented.

[0014] A computer-readable storage medium stores a computer program, wherein the computer program implements the above-mentioned platform when executed by a processor.

[0015] The beneficial effects of the present invention are: 1. The digital twin platform of the present invention supports the synchronization of multi-modal sensors such as stress, temperature, and vibration, and combines aerodynamic thermal environment data to build a real-time dynamic image of the spacecraft.

[0016] 2. The digital twin platform of the present invention integrates damage detection algorithms and load identification technologies to achieve automatic damage location; it integrates the remanufacturing repair process library and life prediction model to support the evaluation of structural performance recovery after repair.

[0017] 3. The software interface of the digital twin platform of the present invention displays damage thermal maps, stress distribution cloud maps and multi-physics field coupling analysis results in real time through a three-dimensional visualization interface, thereby improving the efficiency of maintenance path planning.

[0018] 4. The software interface of the digital twin platform of the present invention records data from the entire flight, repair, production and scrapping cycle, supports historical operating condition backtracking and failure mode analysis, improves the confidence level of reusability assessment, and facilitates the reuse of key components. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic diagram of the operating logic and architecture of the present invention.

[0020] Figure 2 This is a schematic diagram of the title bar of the present invention.

[0021] Figure 3 Schematic diagram of the spacecraft operating status of the present invention.

[0022] Figure 4 This is a schematic diagram of the home page of the present invention.

[0023] Figure 5 This is a schematic diagram of the secondary homepage of the present invention.

[0024] Figure 6 This is a schematic diagram of the real-time evolution page of the present invention.

[0025] Figure 7 Schematic diagram of the flight log subpage in the event log page of the present invention.

[0026] Figure 8 Schematic diagram of the repair log subpage in the event log page of the present invention.

[0027] Figure 9 This is a schematic diagram of the production log subpage in the event log page of the present invention.

[0028] Figure 10 Schematic diagram of the scrap log subpage in the event log page of the present invention. DETAILED DESCRIPTION

[0029] In the following description, specific details such as specific system structures and technologies are provided for illustration rather than limitation to facilitate a thorough understanding of the embodiments of the present application. However, it should be clear to those skilled in the art that the present application may be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to avoid obstructing the description of the present application with unnecessary details.

[0030] It will be understood that when used in this specification and the appended claims, the term "comprising" indicates the presence of described features, integers, steps, operations, elements and / or components, but does not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or groups thereof.

[0031] It should also be understood that the terms used in this specification are only for the purpose of describing specific embodiments and are not intended to limit the present application. As used in this specification and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms unless the context clearly indicates otherwise.

[0032] The following is a clear and complete description of the technical solutions in the embodiments of this application in conjunction with the drawings in the specification of this application. Obviously, the embodiments described are only part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0033] In the following description, many specific details are set forth to facilitate a full understanding of the present application. However, the present application may also be implemented in other ways different from those described herein. Those skilled in the art may make similar generalizations without violating the connotation of the present application. Therefore, the present application is not limited to the specific embodiments disclosed below.

[0034] Implementation Method 1 This embodiment is as follows Figures 1-10 As shown, a spacecraft health status monitoring platform based on digital twin is provided, which includes a perception layer, a data layer, a calculation layer and an expression layer; The sensing layer is used to monitor body data such as stress, strain, temperature, vibration, and environmental data such as aerodynamic force and aerodynamic heat; The data layer is used to ensure high-precision data collection to ensure computational accuracy, high-speed data transmission to ensure interactive real-time performance, and full-lifecycle data management to ensure access reliability. The computing layer is used to realize the functions of system cognition, system diagnosis, state prediction, and collaborative decision-making; Among them, system cognition refers to the ability of digital twins to truly describe and present the status of physical entities; system diagnosis refers to the real-time monitoring system of digital twins, which can identify, locate and evaluate losses or faults; state prediction refers to the ability of digital twins to predict the future status of physical entities based on system operation data; collaborative decision-making refers to the results presented, diagnosed and predicted by digital twins to provide a basis for relevant personnel to make various decisions on the system operation process, and even for the system to make autonomous analysis and decisions.

[0035] The expression layer uses three-dimensional display visualization technology to achieve an intuitive visualization effect of the spacecraft status.

[0036] Furthermore, the platform interface includes a title bar, a home page, a secondary home page, a special page, and sub-pages; like Figure 2 As shown, the title bar first introduces the platform name and logo to enhance brand recognition; adds a search box to facilitate retrieval of the entire platform database; adds a return to homepage function to facilitate users to view the global status; provides login account - logout account and other functions to ensure the security of platform data; provides system settings icon, minimize window, close software and other functions; The search box is used to search the entire platform database; The return homepage is used for users to view the global status; The login account-logout account paging control is used to ensure the security of platform data.

[0037] Further, such as Figure 3-4 As shown, the homepage reflects the spacecraft operation status information by setting different background colors; A green background indicates good operating status; a yellow background indicates moderate damage to the spacecraft, requiring repair or forced landing; and a red background indicates severe damage to the spacecraft, requiring repair or forced landing. The list is arranged from highest to lowest risk. A time and date function is also available, expressed in the format of year-month-day-time.

[0038] Further, such as Figure 5 As shown, the secondary homepage is the jump interface after clicking the spacecraft on the homepage; Displays detailed information about all information components contained in the spacecraft (similar to the expression of the spacecraft's operating status), including the spacecraft's finite element model (which can be enlarged and jumped after finding a component; model import; real-time or non-real-time update, and rapid model adjustment); a three-dimensional schematic diagram of the spacecraft (which can be enlarged to view the spacecraft assembly; import, real-time / non-real-time update); the status and quantity of spacecraft data transmission (displaying the status of major sensors, with a small pop-up window indicating detailed information about the sensor); detailed information about the spacecraft (working hours, working status, working route, and maintenance history); and additional functions such as display time and date, and component retrieval (search box).

[0039] Furthermore, the topic pages include a real-time evolution page, an event log page, a detection process page, and a repair process page; like Figure 6 As shown, the real-time evolution page is the page that jumps to the component function module on the secondary homepage: this page mainly reflects the real-time operating status of the spacecraft component. It includes the finite element model of the component (real-time / non-real-time update, import); the 3D schematic diagram of the component; the real-time line graph of the component's real-time stress, strain, temperature distribution, vibration, etc.; the multi-physics field coupling analysis diagram; the real-time damage evolution diagram of the component; the real-time damage analysis diagram + data; The real-time evolution page includes four main functional modules: event log, inspection process library, maintenance process library and performance evaluation; The event log page displays the historical data of the component and includes four sub-pages: flight log, repair log, production log, and scrap log. The inspection process page integrates an inspection process library, which records the offline inspection methods that should be adopted for different components and different types of damage. This page calls the database by selecting the component and damage type, or jumps to this page through the inspection suggestions on the event log page. Users can modify the data in the library and create and delete data entries. The repair process page integrates a repair process library, which records what repair methods should be adopted for different components and different types of damage. Other functions are similar to the inspection process page.

[0040] Furthermore, the subpages include a flight log subpage, a repair log subpage, a production log subpage, and a scrap log subpage; like Figure 7As shown, the flight log subpage analyzes past data damage and provides corresponding offline inspection and repair suggestions. This page searches by time, and the expression is: click the lower slider and select year / month / day to view the past data analysis of the spacecraft. It includes an overall analysis: a finite element model diagram of the spacecraft during this period; real-time broken line or color diagrams of stress, strain, temperature distribution, vibration, etc., a damage evolution diagram, and damage evolution analysis, and provides the location, type, and size of the damage of the spacecraft. It then provides two functional blocks: offline inspection method and repair process method. Clicking on the two functional blocks will automatically find the most matching inspection process library and repair process library data in the digital twin platform database. Users can also choose to change, create, or delete data in the database according to actual conditions, which is user-friendly. like Figure 8 As shown, the repair log subpage records past component repair data and performs performance evaluation, life prediction, and reusability evaluation on the repaired components. This page displays a component repair performance evaluation chart, a life prediction curve chart, and a component reuse confidence evaluation. Similarly, you can search by time: click the lower slider and select year / month / day to view the component repair history. like Figure 9 As shown, the production log sub-page records the factory information of the component, including factory performance, processing plant, price and model, etc.; it is convenient for users to check the initial information of the component; like Figure 10 As shown, the scrapping log subpage records the scrapping history of the component (if the component has been scrapped and cannot be used, if it has not been scrapped, it will be displayed as no scrapping history); including failure behavior analysis, working hours and number of repairs, so as to provide data reference for users and platforms.

[0041] Implementation Method 2 This embodiment is as follows Figure 1 As shown, an operation method of a spacecraft health status monitoring platform based on digital twin is provided. The operation method uses the spacecraft health status monitoring platform based on digital twin as described in embodiment 1. The operation method is specifically as follows: Collect the overall operational status data of the spacecraft and detailed information at the component level in real time through the sensor network to form a basic data layer; Based on physical models such as finite element analysis and data-driven models, high-precision digital twins are constructed to dynamically simulate the on-orbit behavior of spacecraft and achieve synchronous mapping of virtual and real states; Identify potential damage through structural damage detection methods, optimize repair solutions, and drive dynamic evolution processes; Integrate multi-source data to achieve comprehensive performance evaluation and output maintenance and resource optimization suggestions.

[0042] Implementation Method 3 This embodiment provides a monitoring platform as described in Embodiment 1, which uses digital twin technology to be applied in the field of spacecraft health status monitoring.

[0043] Implementation Method 4 An embodiment of the present invention provides an electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor. The memory is used to store software programs and modules, and the processor executes various functional applications and data processing by executing the software programs and modules stored in the memory. The memory and processor are connected via a bus. Specifically, the processor implements any step of the first embodiment described above by executing the computer program stored in the memory.

[0044] It should be understood that in the embodiments of the present invention, the processor referred to may be a central processing unit (CPU), and the processor may also be other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor may be a microprocessor or any conventional processor, etc.

[0045] The memory may include a read-only memory, a flash memory, and a random access memory, and provides instructions and data to the processor. A portion or all of the memory may also include a non-volatile random access memory.

[0046] It should be understood that if the above-mentioned integrated modules / units are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the present invention can also implement all or part of the processes in the above-mentioned method embodiments by using a computer program to instruct the relevant hardware. The above-mentioned computer program can be stored in a computer-readable storage medium. When executed by a processor, the computer program can implement the steps of each of the above-mentioned method embodiments. The above-mentioned computer program includes computer program code, which can be in source code form, object code form, executable file, or some intermediate form. The above-mentioned computer-readable medium can include: any entity or device capable of carrying the above-mentioned computer program code, recording medium, USB flash drive, mobile hard drive, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signal, telecommunication signal, and software distribution medium. It should be noted that the content contained in the above-mentioned computer-readable storage medium can be appropriately increased or decreased based on the requirements of legislation and patent practice in a jurisdiction.

[0047] The above description of the disclosed embodiments will enable one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be readily apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not limited to the embodiments shown herein, but is to be construed in the widest manner consistent with the principles and novel features disclosed herein.

[0048] Those skilled in the art can clearly understand that, for the convenience and brevity of description, only the division of the above-mentioned functional units and modules is used as an example for illustration. In actual applications, the above-mentioned functions can be distributed and completed by different functional units and modules as needed, that is, the internal structure of the above-mentioned device can be divided into different functional units or modules to complete all or part of the functions described above. The functional units and modules in the implementation method can be integrated into one processing unit, or each unit can exist physically alone, or two or more units can be integrated into one unit. The above-mentioned integrated unit can be implemented in the form of hardware or in the form of software functional units. In addition, the specific names of the functional units and modules are only for the convenience of distinguishing each other, and are not used to limit the scope of protection of the present invention. The specific working process of the units and modules in the above-mentioned system can refer to the corresponding process in the aforementioned method implementation method, and will not be repeated here.

[0049] It should be noted that the methods and detailed examples provided in the above embodiments can be combined with the devices and equipment provided in the embodiments, and references can be made to each other, and no further details will be given.

[0050] Those skilled in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professionals and technicians may use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of the present invention.

[0051] In the embodiments provided by the present invention, it should be understood that the disclosed apparatus / terminal equipment and methods can be implemented in other ways. For example, the apparatus / device embodiments described above are merely illustrative. For example, the division of the modules or units described above is merely a logical functional division. In actual implementation, other division methods may be used. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not implemented.

[0052] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or make equivalent replacements for some of the technical features therein. 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 various embodiments of the present invention, and should all be included in the scope of protection of the present invention.

Claims

1. A spacecraft health status monitoring platform based on digital twins, characterized by: The platform includes a perception layer, a data layer, a computing layer, and a presentation layer; The perception layer is used to monitor body data and environmental data; The data layer is used to ensure high-precision data collection to ensure computational accuracy, high-speed data transmission to ensure interactive real-time performance, and full-lifecycle data management to ensure access reliability. The computing layer is used to realize the functions of system cognition, system diagnosis, state prediction, and collaborative decision-making; The expression layer is used to achieve an intuitive visualization effect of the spacecraft status.

2. The platform according to claim 1, characterized in that The platform interface includes a title bar, home page, sub-home page, special page and sub-pages; The title bar includes a search box, a return to home page, a system settings icon, a minimized window icon, a close software icon, and a paging control for logging in and out of accounts; The search box is used to search the entire platform database; The return homepage is used for users to view the global status; The login account-logout account paging control is used to ensure the security of platform data.

3. The platform according to claim 2, characterized in that The home page reflects the spacecraft operation status information by setting different background colors; Among them, the green background indicates that the operating status is good; the yellow background indicates that there are moderately damaged parts in the spacecraft - requiring repair / forced landing; the red background indicates that there are severely damaged parts in the spacecraft - requiring repair / forced landing; they are arranged from high to low according to the danger level.

4. The platform according to claim 2, characterized in that The secondary homepage is the jump interface after clicking the spacecraft on the homepage; Displays all information components contained in the spacecraft, including the finite element model of the spacecraft; the three-dimensional schematic diagram of the spacecraft; the status and quantity of spacecraft data transmission; detailed information about the spacecraft; additional functions include displaying time and date, and component retrieval.

5. The platform according to claim 2, characterized in that The topic pages include a real-time evolution page, an event log page, a detection process page, and a repair process page; The real-time evolution page is the page that jumps to when clicking on the secondary homepage component function module: it reflects the spacecraft; The real-time evolution page includes event logs, inspection process library, maintenance process library, and performance evaluation; The event log page displays the historical data of the component, including flight log, repair log, production log and scrap log; The inspection process page integrates an inspection process library, which lists offline inspection methods for different components and different types of damage. You can access the database by selecting a component or damage type, or by using the inspection suggestions in the event log page. Users can modify the data in the library, create new data and delete data; The repair process page integrates a repair process library, which records the repair methods that should be taken for different components and different types of damage. Other functions are similar to the inspection process page.

6. The platform according to claim 2, characterized in that The subpages include a flight log subpage, a repair log subpage, a production log subpage, and a scrap log subpage; The flight log subpage analyzes past data damage and provides corresponding offline detection and repair suggestions; This page searches by time and includes an overall analysis: a finite element model diagram of the spacecraft during that period; real-time line or color plots of stress, strain, temperature distribution, and vibration; a damage evolution diagram and analysis; and provides the location, type, and size of damage on the spacecraft. This provides two functional blocks: offline inspection methods and repair process methods. Clicking on either block automatically searches the digital twin platform database for the most matching inspection and repair process library data. The repair log subpage records past component repair data and performs performance evaluation, life prediction, and reusability evaluation on the repaired components. This page displays a component repair performance evaluation chart, a life prediction curve chart, and a component reuse confidence evaluation. It can also be searched by time. The production log sub-page records the factory information of the component, including factory performance, processing plant, price and model; The scrapping log subpage records the scrapping history of the components; Includes failure behavior analysis, working hours and number of repairs completed.

7. A method for operating a spacecraft health status monitoring platform based on digital twins, characterized in that: The operation method uses the digital twin-based spacecraft health status monitoring platform according to any one of claims 1 to 6, and the operation method is specifically as follows: Collect the overall operational status data of the spacecraft and detailed information at the component level in real time through the sensor network to form a basic data layer; Based on physical models such as finite element analysis and data-driven models, high-precision digital twins are constructed to dynamically simulate the on-orbit behavior of spacecraft and achieve synchronous mapping of virtual and real states; Identify potential damage through structural damage detection methods, optimize repair solutions, and drive dynamic evolution processes; Integrate multi-source data to achieve comprehensive performance evaluation and output maintenance and resource optimization suggestions.

8. A monitoring platform according to any one of claims 1 to 6, applied to the field of spacecraft health status monitoring.

9. A computer device, characterized in that: The platform comprises a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the platform according to any one of claims 1 to 6 is implemented.

10. A computer-readable storage medium, characterized in that The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the platform according to any one of claims 1 to 6 is implemented.

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