Civil aircraft fatigue condition-oriented analysis system and analysis method

Abstract

The invention relates to a civil aircraft fatigue condition-oriented analysis system and analysis method, and provides a set of standardized fatigue analysis data management and control system, so that the normalization of an analysis process and the reliability of a result are ensured; a system preset to-be-called algorithm and basic data resources are called through an algorithm calling arrangement module to generate a fatigue analysis algorithm corresponding to a to-be-analyzed object, so that analysis of different analysis target objects and different fatigue analysis items can be met, and the flexibility of fatigue analysis is guaranteed; the civil aircraft fatigue condition-oriented analysis system and analysis method can automatically respond to the to-be-analyzed test data information and the to-be-analyzed object information and execute automatic analysis operation, so that the analysis accuracy and efficiency are effectively improved, and the operation of operators is more convenient.

Description

Technical Field

[0001] The present invention relates to the technical field of fatigue testing, and in particular to an analysis system and an analysis method for fatigue conditions of civil aircraft. Background Art

[0002] In the field of civil aircraft structural design, airframe metal fatigue analysis plays a crucial role. It is not only the cornerstone for ensuring safety and economic efficiency throughout the aircraft's lifecycle, but also a key indicator for measuring the core competitiveness of civil aircraft airframe structures. Excellent fatigue durability and cost-effective maintenance plans are both essential for flight safety and economic efficiency. Therefore, optimizing airframe structural fatigue design is crucial for domestically produced civil aircraft to gain a foothold in the global aviation industry.

[0003] However, existing technologies typically require professional operators to perform fatigue analysis themselves. This results in high professional expertise in the relevant calculations, which can lead to a large number of fatigue detection projects being delayed. Furthermore, because each operator performs analysis independently, there may be inconsistencies in the methods used by different operators, or errors may occur. This can lead to inconsistent final results when analyzing the same target object. When related issues arise, review is difficult, and existing technologies cannot achieve full-process fatigue detection.

[0004] Therefore, the existing technology cannot achieve a rapid and accurate assessment of aircraft fatigue, resulting in low efficiency in the verification of civil aircraft airframe structural engineering and difficulty in achieving rapid and accurate assessment. This has become a major bottleneck restricting the research and development process and serial development of domestic civil aircraft. Summary of the Invention

[0005] In view of the above-mentioned defects of the prior art, the present invention proposes an analysis system and analysis method for civil aircraft fatigue conditions that can solve at least one of the above-mentioned problems, better meet the civil aircraft fatigue detection needs under different requirements, and is easier to operate and has good adaptability.

[0006] To achieve the above objectives, the present invention provides a fatigue analysis system and method for civil aircraft as follows:

[0007] In a first aspect, an embodiment of the present invention provides a fatigue analysis system for civil aircraft, the main feature of which is that the system includes:

[0008] The data collection module includes an analysis parameter collection unit, wherein the analysis parameter collection unit is used to obtain information about the test data to be analyzed and information about the object to be analyzed;

[0009] Algorithm and basic data storage module, used to store the system preset algorithms and basic data resources used for fatigue analysis;

[0010] An algorithm call arrangement module is used to respond to the information of the object to be analyzed, call the corresponding algorithm and basic data resources from the algorithms to be called and basic data resources, and generate a fatigue analysis algorithm corresponding to the object to be analyzed;

[0011] The calculation result generating module is used to perform fatigue analysis on the object to be analyzed based on the fatigue analysis algorithm and the test data information to be analyzed, so as to generate a fatigue analysis calculation result of the object to be analyzed.

[0012] In some embodiments, the algorithm and basic data storage module includes:

[0013] Professional basic data storage unit, including preset related algorithms and basic data resources for fatigue analysis;

[0014] General basic algorithm storage unit, including preset general algorithm resources;

[0015] The algorithms and basic data resources to be called are jointly constituted by the relevant algorithms and basic data resources for fatigue analysis and the general algorithm resources.

[0016] In some embodiments, the algorithm call orchestration module includes:

[0017] An algorithm scheduling engine, configured to call a corresponding algorithm from the algorithm and basic data storage module in response to the information of the object to be analyzed;

[0018] A universal data access engine, configured to call corresponding basic data resources from the algorithm and basic data storage module in response to the information of the object to be analyzed;

[0019] The algorithm generation module is used to generate a fatigue analysis algorithm corresponding to the object to be analyzed based on the algorithm called by the algorithm scheduling engine and the basic data resources called by the general data access engine.

[0020] In some embodiments, the system further includes an AI engine module and an AI machine learning algorithm library,

[0021] The AI engine module is used to schedule algorithms in the AI machine learning algorithm library to assist in analyzing civil aircraft fatigue conditions.

[0022] In some embodiments, the calculation result generation module includes:

[0023] a calculation unit, configured to perform fatigue analysis on the object to be analyzed based on the fatigue analysis algorithm and the test data information to be analyzed, so as to generate a fatigue analysis calculation result of the object to be analyzed;

[0024] A report generating unit, configured to generate a fatigue analysis strength verification report based on the information of the object to be analyzed and the fatigue analysis calculation result of the object to be analyzed;

[0025] The log generation unit is used to generate log information when the analysis system for civil aircraft fatigue conditions is running.

[0026] In some embodiments, the system further comprises:

[0027] A data entry and display module is used to receive input instructions and data to be analyzed, send the input instructions and data to be analyzed to the data collection module, and display the fatigue analysis calculation results of the object to be analyzed, wherein the input instructions and data to be analyzed include test data information to be analyzed, object information to be analyzed, customized algorithm instructions, and customized parameter instructions;

[0028] Among them, the data collection module, algorithm and basic data storage module, algorithm call orchestration module and calculation result generation module are located in the cloud server, and the data entry and display module is located in the user-end device. The user-end device can realize data interaction with the cloud server through the WEB terminal.

[0029] In some embodiments, the cloud server further includes:

[0030] User authority management module, used to manage the authority of each operating account;

[0031] The project management module is used to manage each civil aircraft fatigue analysis project.

[0032] In a second aspect, an embodiment of the present invention further provides a method for analyzing fatigue conditions of a civil aircraft, the method comprising executing a detection object acquisition operation and a calculation and analysis operation;

[0033] The detection object acquisition operation at least includes: acquiring the test data information to be analyzed and the object information to be analyzed;

[0034] The calculation and analysis operation at least includes: combining the test data information to be analyzed and responding to the information of the object to be analyzed, calling the corresponding algorithm and basic data resources from the system's preset algorithms and basic data resources to be called, generating a fatigue analysis algorithm corresponding to the object to be analyzed, and performing fatigue analysis on the object to be analyzed based on the fatigue analysis algorithm and the test data information to be analyzed to generate a fatigue analysis calculation result for the object to be analyzed.

[0035] In some embodiments, the computational analysis operation specifically includes:

[0036] Acquire the test data information to be analyzed to read the internal force solution file information, and determine the object to be analyzed through the acquired information of the object to be analyzed;

[0037] In response to the information of the object to be analyzed, based on the internal force solution file information, a corresponding algorithm and basic data resource are retrieved from the algorithms and basic data resources to be called, and a working stress algorithm for fatigue hazard details in the fatigue analysis algorithm corresponding to the object to be analyzed is generated;

[0038] Obtaining the working stress of the fatigue hazard details corresponding to the object to be analyzed based on the working stress algorithm of the fatigue hazard details;

[0039] In response to information of an object to be analyzed, a cross-section corresponding to the object to be analyzed is determined, and based on the working stress of the fatigue hazard details corresponding to the object to be analyzed, corresponding algorithms and basic data resources are retrieved from the algorithms to be called and basic data resources, to generate load algorithms for each working condition corresponding to the cross-section in the fatigue analysis algorithm corresponding to the object to be analyzed,

[0040] Based on the load algorithms for each working condition corresponding to the cross section, the loads for each working condition under the cross section are screened out;

[0041] Based on the selected loads of each working condition under the cross section, the corresponding algorithm and basic data resources are retrieved from the to-be-called algorithm and basic data resources to generate a far-field tensile combined working condition stress algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed;

[0042] Determining the far-field tensile combined working condition stress of the object to be analyzed based on the far-field tensile combined working condition stress algorithm;

[0043] Determine the load sequence based on the preset load spectrum;

[0044] Based on the load sequence and the far-field tensile combined working condition stress of the object to be analyzed, and in combination with calling corresponding algorithms and basic data resources from the to-be-called algorithms and basic data resources, a fatigue working stress spectrum algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed is generated;

[0045] Determining the fatigue working stress spectrum of the object to be analyzed based on the fatigue working stress spectrum algorithm;

[0046] Simplifying the fatigue working stress spectrum of the object to be analyzed by using a rain flow calculation method to generate a simplified fatigue working stress spectrum;

[0047] Retrieving a corresponding algorithm and basic data resource from the algorithms and basic data resources to be called, and generating a fatigue assessment rating algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed;

[0048] determining a fatigue assessment rating of the object to be analyzed based on the fatigue assessment rating algorithm;

[0049] Based on the simplified fatigue working stress spectrum and the fatigue assessment rated value, a fatigue damage calculation algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed is generated in combination with the corresponding algorithm and basic data resources retrieved from the to-be-called algorithm and basic data resources;

[0050] Determining fatigue damage of the object to be analyzed based on the fatigue damage calculation algorithm;

[0051] Based on the fatigue damage of the object to be analyzed, a fatigue margin algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed is generated by combining corresponding algorithms and basic data resources retrieved from the algorithms to be called and basic data resources;

[0052] Determining the fatigue margin of the object to be analyzed based on the fatigue margin algorithm;

[0053] Based on the fatigue margin of the object to be analyzed, a fatigue result algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed is generated by calling a corresponding algorithm and basic data resource from the algorithm to be called and the basic data resource;

[0054] Based on the fatigue result algorithm, a fatigue analysis calculation result of the object to be analyzed is generated.

[0055] In some embodiments, the analysis method further comprises performing a result output operation and a log recording operation;

[0056] The result output operation is used to output the fatigue analysis calculation results of the object to be analyzed;

[0057] The logging operation is used to generate log information when the analysis system for civil aircraft fatigue conditions is running.

[0058] The beneficial effects of the analysis system and analysis method for fatigue conditions of civil aircraft of the present invention are as follows:

[0059] The analysis system and analysis method for fatigue conditions of civil aircraft of the present invention can provide a standardized fatigue analysis data management and control system, ensure the standardization of the analysis process and the reliability of the results, and call the system's preset algorithms and basic data resources through the algorithm call orchestration module to generate a fatigue analysis algorithm corresponding to the object to be analyzed, thereby meeting the analysis of different analysis target objects and different fatigue analysis projects, thereby ensuring the flexibility of fatigue analysis. In addition, the analysis system and analysis method for fatigue conditions of civil aircraft of the present invention can automatically respond to the test data information to be analyzed and the information of the object to be analyzed, perform automated analysis operations, effectively improve the accuracy and efficiency of the analysis, and make it more convenient for operators to operate. BRIEF DESCRIPTION OF THE DRAWINGS

[0060] The concept, specific structure and technical effects of the present invention will be further described below in conjunction with the accompanying drawings to fully understand the purpose, characteristics and effects of the present invention.

[0061] Figure 1 4 is a system architecture diagram of a fatigue analysis system for civil aircraft in one embodiment of the present invention.

[0062] Figure 2 This is a flow chart of a method for analyzing fatigue conditions of civil aircraft in one embodiment of the present invention.

[0063] Figure 3 FIG. 4 is a flow chart of a computational analysis operation in one embodiment of the present invention. DETAILED DESCRIPTION

[0064] In order to make the technical means, creative features, objectives and effects of the invention easier to understand, the invention is further described below with reference to specific diagrams. However, the invention is not limited to the following implementation cases.

[0065] It should be noted that the structures, proportions, sizes, etc. illustrated in the drawings in this specification are only used to match the contents disclosed in the specification so that people familiar with this technology can understand and read them. They are not used to limit the conditions under which the present invention can be implemented. Therefore, they have no substantive technical significance. Any modification of the structure, change in the proportion relationship or adjustment of the size should still fall within the scope of the technical content disclosed in the present invention without affecting the efficacy and purpose that can be achieved by the present invention.

[0066] It should be noted that, in this document, relational terms such as “first” and “second” are merely used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations.

[0067] Currently, my country's aircraft manufacturing industry does not have dedicated software for analyzing fatigue conditions in civil aircraft. This has led to the lack of a systematic fatigue analysis platform that can automate and batch-produce the entire process from units and internal forces to fatigue stress spectra and fatigue margins. This has led to low efficiency in the verification of civil aircraft airframe structural engineering and difficulty in achieving rapid and accurate assessments. This has become a major bottleneck restricting the R&D process and serial development of domestic civil aircraft.

[0068] To address the above issues, the present invention provides a civil aircraft fatigue analysis system and method with strong compatibility, autonomous controllability, high standardization, and good adaptability to meet the needs of full-process analysis of civil aircraft fatigue status. This civil aircraft fatigue analysis system and method are characterized by high efficiency, a higher degree of standardization in the detection process, and flexibility. The following further analyzes the civil aircraft fatigue analysis system and method of the present invention in conjunction with specific embodiments:

[0069] First embodiment:

[0070] This embodiment provides a system for analyzing fatigue conditions of civil aircraft, the system comprising:

[0071] The data collection module includes an analysis parameter collection unit, which is used to obtain test data information to be analyzed and object information to be analyzed; wherein the test data information to be analyzed may include information such as civil aircraft detection data collected by external equipment, and the object information to be analyzed includes user operation instructions, such as selected object data to be analyzed and some parameter design information;

[0072] The algorithm and basic data storage module is used to store the system-preset algorithms and basic data resources to be called for fatigue analysis; the method call orchestration module is used to respond to the information of the object to be analyzed, call the corresponding algorithm and basic data resources from the algorithms and basic data resources to be called, and generate a fatigue analysis algorithm corresponding to the object to be analyzed; some commonly used orchestration and calling rules corresponding to each analysis object can be pre-stored in the system in advance, and in special cases, the operator can also flexibly use the algorithm call orchestration module to generate the algorithm;

[0073] a calculation result generating module, configured to perform fatigue analysis on the object to be analyzed based on the fatigue analysis algorithm and the test data information to be analyzed, so as to generate a fatigue analysis calculation result of the object to be analyzed;

[0074] AI engine module;

[0075] AI machine learning algorithm library;

[0076] The AI engine module is used to schedule algorithms in the AI machine learning algorithm library to assist in analyzing civil aircraft fatigue conditions. The AI module settings can assist user operations.

[0077] User authority management module, used to manage the authority of each operating account;

[0078] The project management module is used to manage each civil aircraft fatigue analysis project.

[0079] A data entry and display module is used to receive input instructions and data to be analyzed, send the input instructions and data to be analyzed to the data collection module, and display the fatigue analysis calculation results of the object to be analyzed, wherein the input instructions and data to be analyzed include test data information to be analyzed, object information to be analyzed, customized algorithm instructions, and customized parameter instructions;

[0080] Among them, the data collection module, algorithm and basic data storage module, algorithm call orchestration module, calculation result generation module, AI engine module, AI machine learning algorithm library, user authority management module and project management module are located in the cloud server, and the data entry and display module is located in the user-end device. The user-end device can realize data interaction with the cloud server through the WEB terminal (full name: World Wide Web, that is, the Global Wide Area Network, also known as the World Wide Web, which is a global, dynamically interactive, cross-platform distributed graphic information system based on hypertext and HTTP).

[0081] The civil aircraft fatigue analysis system in this embodiment places the analysis functions on a cloud device, while other users can access the server via a web interface. This reduces the operational requirements for local devices while still meeting the fatigue analysis needs. This eliminates system compatibility and flexibility restrictions on local user devices, and eliminates the need for system users to manually install and update the system. Instead, the system simply uploads the civil aircraft data to be analyzed via the local device's web interface and selects the object to be analyzed, which drives the system to execute the analysis. The fatigue analysis system on the cloud server only requires maintenance by professionals, reducing maintenance complexity and meeting the needs of use in a wider range of office environments.

[0082] Since the main part of the system used for fatigue analysis is set up in the cloud, and the user end is only used to upload the data to be analyzed, specify the analysis target and display the analysis results, the system has a more standardized analysis method, high analysis efficiency, and the analysis results can be presented in a more standardized and standardized manner, which also provides convenience for subsequent review work.

[0083] Furthermore, relevant fatigue analysis data and model files can be stored in cloud servers, enabling better control over the iteration of fatigue analysis results (i.e., facilitating data iteration during fatigue analysis after adjustments to the relevant components under test during the design process, facilitating data processing) and facilitating data collaboration between teams. The full-process automated analysis platform provided by this invention can reduce the time spent on civil aircraft structural engineering verification, lowering labor costs while enabling faster response to design changes, effectively accelerating the development and serialization of domestically produced civil aircraft.

[0084] In summary, the system has the advantages of good system compatibility, high autonomous controllability, high degree of standardization, convenient data management and reduced human resource consumption. It is a more efficient, standardized and flexible aircraft fatigue analysis solution.

[0085] In this embodiment, the algorithm and basic data storage module include:

[0086] Professional basic data storage unit, including preset related algorithms and basic data resources for fatigue analysis;

[0087] General basic algorithm storage unit, including preset general algorithm resources;

[0088] The algorithms and basic data resources to be called are jointly constituted by the relevant algorithms and basic data resources for fatigue analysis and the general algorithm resources.

[0089] In this embodiment, the professional basic data storage unit may include:

[0090] Model library, pre-stored basic callable models;

[0091] Parameter library, pre-stored parameter information to be retrieved and used to implement fatigue analysis;

[0092] Case library, pre-stored case information to be used for fatigue analysis;

[0093] Material library, pre-stored material information that can be used to implement fatigue analysis

[0094] Algorithm library, pre-stored algorithm data to be retrieved for fatigue analysis;

[0095] Internal force solution library, pre-stored finite element calculation results that can be used to implement fatigue analysis;

[0096] A general algorithm library pre-stores general algorithm data to be retrieved that can be used to implement fatigue analysis; in specific applications, the general algorithm library may include Python scientific computing algorithms, which can provide some general algorithms for being called when performing fatigue analysis on civil aircraft.

[0097] Among them, the content of each library in the professional basic data storage unit can be preset in the corresponding library by the system setting personnel. The data and information in the professional basic data storage unit are the data and information commonly used in the process of fatigue testing of civil aircraft. They can be called and combined to form the corresponding fatigue analysis algorithm according to the objects to be tested specified by the user, so as to analyze the objects to be analyzed. At the same time, in the subsequent application process, users with operation permissions can also add, delete or edit the content in each library. The above-mentioned libraries can be called by the algorithm scheduling engine or the general access engine;

[0098] In this embodiment, the algorithm call arrangement module includes:

[0099] An algorithm scheduling engine, configured to call a corresponding algorithm from the algorithm and basic data storage module in response to the information of the object to be analyzed;

[0100] A universal data access engine, configured to call corresponding basic data resources from the algorithm and basic data storage module in response to the information of the object to be analyzed;

[0101] The algorithm generation module is used to generate a fatigue analysis algorithm corresponding to the object to be analyzed based on the algorithm called by the algorithm scheduling engine and the basic data resources called by the general data access engine.

[0102] In this embodiment, the calculation result generation module includes:

[0103] a calculation unit, configured to perform fatigue analysis on the object to be analyzed based on the fatigue analysis algorithm and the test data information to be analyzed, so as to generate a fatigue analysis calculation result of the object to be analyzed;

[0104] A report generating unit, configured to generate a fatigue analysis strength verification report based on the information of the object to be analyzed and the fatigue analysis calculation result of the object to be analyzed;

[0105] The log generation unit is used to generate log information when the analysis system for civil aircraft fatigue conditions is running.

[0106] In this embodiment, the computing module includes a distributed computing engine that performs fatigue analysis on the object to be analyzed based on the fatigue analysis algorithm and the test data to be analyzed. Using a distributed computing engine to perform computing operations can effectively improve computing efficiency and accelerate analysis speed.

[0107] It should be noted that the modules mentioned above are not necessarily independent hardware structures. They may also be a combination of multiple hardware modules, or may be located in the same device at the same time. They are not necessarily independent entities.

[0108] For ease of understanding, the following Figure 1 The composition of the above-mentioned analysis system for civil aircraft fatigue is further explained:

[0109] Figure 1 FIG. 1 is a system architecture diagram of a fatigue analysis system for civil aircraft according to an embodiment of the present invention. Figure 1 As shown, the front end of the system can be built using 3D visualization components, Vue (Vue is a JavaScript framework for building user interfaces), Ka-Tex (full name Khan Academy TeX) is a mathematical typesetting library for the web, Echarts (ECharts is a JavaScript-based data visualization chart library), and Grafana (Grafana is an open source data visualization and monitoring platform), so that operators can upload analysis data and read analysis results on the web.

[0110] The specific design utilizes the Vue front-end framework and the Element UI component library (Element UI provides a rich set of UI components for quickly building enterprise-level web application interfaces), combined with customized front-end scaffolding to meet the unique page layout requirements of engineering software projects. Utilizing 3D visualization components to load 3D mesh models, and through front-end rendering acceleration and Vue componentization, the aircraft mesh model can be displayed and interacted with on the web, enabling interaction with the 3D model.

[0111] The application service layer shows that the system's operations can be divided into five main parts: creating a fatigue analysis project, the operator can set relevant parameters, the system then executes the algorithm, and displays the analysis results to the user for viewing. It can also generate an analysis report. The basic operating architecture is implemented through common basic components. The details are as follows:

[0112] a. Create fatigue analysis: Based on typical fatigue analysis scenarios, automatically create structural combination units and automatically complete fatigue analysis assessment.

[0113] b. Calculation parameter settings: Provides a tree diagram display to facilitate parameter modification and design iteration. Relevant parameter settings are part of the information of the object to be analyzed.

[0114] c. Algorithm orchestration and calling: Schedule algorithm execution based on requests and parameters, supporting parallel computing and logging.

[0115] d. Calculation result display: summarizes the calculation results and supports log export and Excel file generation.

[0116] e. Report generation: Automatically generate fatigue analysis strength verification report based on calculation results and analysis type.

[0117] The system's engine layer leverages Python's robust technical ecosystem and broad adaptability, as well as its ability to integrate with other scientific languages, to call algorithm libraries from Python and other languages (such as Matlab, FORTRAN, and C / C++). The computing engine also provides computational scheduling and cluster parallel computing capabilities.

[0118] The fatigue algorithm layer implements the typical calculation process of fatigue analysis, including working stress calculation, fatigue stress spectrum calculation, CFQ calculation (CFQ professional terminology is explained as: fatigue assessment rating), rain flow calculation (that is, the rain flow calculation method can be used to simplify the relevant data to facilitate subsequent faster data analysis. In other embodiments, other simplified algorithms can also be used to simplify the data), fatigue damage calculation and fatigue margin calculation modules. That is, the fatigue analysis algorithm that can be constructed by the algorithm call orchestration module includes the above-mentioned fatigue analysis algorithms.

[0119] It should be noted that sometimes, based on user needs, only part of the analysis calculations can be performed, and it is not necessary to fully execute a complete set of algorithm analysis and processing processes.

[0120] The foundation layer includes IT foundation functional units, specialized foundational databases, and a general foundational algorithm library. The data storage layer utilizes relational databases, NoSQL databases, time-series databases, object storage (OSS), and big data Hadoop to provide data storage. The IT foundation functional units implement common functions such as user permission settings, project management (i.e., management of individual fatigue analysis projects), model analysis, and personalized configuration to better suit user operating habits, or to meet specific analysis needs.

[0121] The foundational layer includes functions such as user permissions, project management, computing resource scheduling, model import and parsing, and algorithm orchestration. A specialized foundational database stores finite element model data, internal force solution results, op2 data, material data, and algorithm storage. op2 and bdf model data (i.e., the raw test data to be analyzed, where op2 is the internal force solution file, which includes specialized information such as stress information; and bdf model files, which are input files describing the structural model and analysis conditions and contain key data such as model geometry, material properties, boundary conditions, load cases, and solution options) are stored in the NoSQL database MongoDB. Time series data is stored in the time series database IoTDB. User permissions and other data are stored in a relational database. By building specialized databases such as model libraries, algorithm libraries, and material libraries, data sources are unified, improving overall utilization efficiency and enabling model and data sharing. This allows for data access by other users, allowing different operators to apply analysis algorithms and reducing the complexity of fatigue analysis. The data available in each database is scheduled and combined for application by the corresponding engine. Object storage OSS is mainly used to store log information, while the data in big data Hadoop is mainly used for subsequent analysis.

[0122] By structuring fatigue analysis process data and performing structured parsing of object data files, and adopting a hybrid database architecture (MongoDB + IoTDB + relational database) on the server side, we address the difficulty of storing and accessing large-scale data in the GB / 100 million range. This enables millisecond-level fast queries and lightweight web-based data utilization (such as millisecond-level queries and lightweight presentation of finite element node internal force solutions). Standardized verification reports are generated through structured report templates. Data versions are traceable, result formats are unified, and review efficiency is improved.

[0123] Intelligent Analysis and Scenario Flexibility: This system provides a parameter template mechanism based on a "material library, fastener library, and model library" (e.g., fatigue damage algorithm CFQ / rainflow analysis), supporting customized analysis processes by aircraft type (e.g., rapid switching between different internal force batches). This adapts to the diverse needs of civil aircraft models (covering 80% of typical fatigue scenarios) and reduces the error rate of manual parameter adjustment.

[0124] The analysis system for civil aircraft fatigue conditions built through the above architecture is easy to operate, has a wide range of applications, and runs quickly.

[0125] Second embodiment:

[0126] This embodiment provides a method for analyzing fatigue conditions of civil aircraft, the method comprising executing a detection object acquisition operation and a calculation and analysis operation;

[0127] The detection object acquisition operation at least includes: acquiring the test data information to be analyzed and the object information to be analyzed;

[0128] The calculation and analysis operation at least includes: combining the test data information to be analyzed and responding to the information of the object to be analyzed, calling the corresponding algorithm and basic data resources from the system preset algorithms and basic data resources to be called, generating a fatigue analysis algorithm corresponding to the object to be analyzed, and performing fatigue analysis on the object to be analyzed based on the fatigue analysis algorithm and the test data information to be analyzed to generate a fatigue analysis calculation result of the object to be analyzed, specifically including:

[0129] Acquire the test data information to be analyzed to read the internal force solution file information, and determine the object to be analyzed through the acquired information of the object to be analyzed;

[0130] In response to the information of the object to be analyzed, based on the internal force solution file information, a corresponding algorithm and basic data resource are retrieved from the algorithms and basic data resources to be called, and a working stress algorithm for fatigue hazard details in the fatigue analysis algorithm corresponding to the object to be analyzed is generated;

[0131] Obtaining the working stress of the fatigue hazard details corresponding to the object to be analyzed based on the working stress algorithm of the fatigue hazard details;

[0132] In response to information of an object to be analyzed, a cross-section corresponding to the object to be analyzed is determined, and based on the working stress of the fatigue hazard details corresponding to the object to be analyzed, corresponding algorithms and basic data resources are retrieved from the algorithms to be called and basic data resources, to generate load algorithms for each working condition corresponding to the cross-section in the fatigue analysis algorithm corresponding to the object to be analyzed,

[0133] Based on the load algorithms for each working condition corresponding to the cross section, the loads for each working condition under the cross section are screened out;

[0134] Based on the selected loads of each working condition under the cross section, the corresponding algorithm and basic data resources are retrieved from the to-be-called algorithm and basic data resources to generate a far-field tensile combined working condition stress algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed;

[0135] Determining the far-field tensile combined working condition stress of the object to be analyzed based on the far-field tensile combined working condition stress algorithm;

[0136] Determine the load sequence based on the preset load spectrum;

[0137] Based on the load sequence and the far-field tensile combined working condition stress of the object to be analyzed, and in combination with calling corresponding algorithms and basic data resources from the to-be-called algorithms and basic data resources, a fatigue working stress spectrum algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed is generated;

[0138] Determining the fatigue working stress spectrum of the object to be analyzed based on the fatigue working stress spectrum algorithm;

[0139] Simplifying the fatigue working stress spectrum of the object to be analyzed by using a rain flow calculation method to generate a simplified fatigue working stress spectrum;

[0140] Retrieving a corresponding algorithm and basic data resource from the algorithms and basic data resources to be called, and generating a fatigue assessment rating algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed;

[0141] determining a fatigue assessment rating of the object to be analyzed based on the fatigue assessment rating algorithm;

[0142] Based on the simplified fatigue working stress spectrum and the fatigue assessment rated value, a fatigue damage calculation algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed is generated in combination with the corresponding algorithm and basic data resources retrieved from the to-be-called algorithm and basic data resources;

[0143] Determining fatigue damage of the object to be analyzed based on the fatigue damage calculation algorithm;

[0144] Based on the fatigue damage of the object to be analyzed, a fatigue margin algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed is generated by combining corresponding algorithms and basic data resources retrieved from the algorithms to be called and basic data resources;

[0145] Determining the fatigue margin of the object to be analyzed based on the fatigue margin algorithm;

[0146] Based on the fatigue margin of the object to be analyzed, a fatigue result algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed is generated by calling a corresponding algorithm and basic data resource from the algorithm to be called and the basic data resource;

[0147] Generate fatigue analysis calculation results of the object to be analyzed based on the fatigue result algorithm;

[0148] Execute the result output operation to output the fatigue analysis calculation results of the object to be analyzed;

[0149] A log recording operation is performed to generate log information of the analysis system for civil aircraft fatigue conditions during operation.

[0150] The analysis method for fatigue conditions of civil aircraft in this embodiment is a web-based online calculation method for aircraft fatigue analysis, which aims to cover the typical business process of fatigue analysis of complex structures and improve engineering efficiency. The system realizes the automation of the entire fatigue analysis process from model import to results by integrating functions such as aircraft model selection, BDF import, SE creation (i.e., creating a strength verification model), fatigue detail selection (i.e., selecting fatigue details of the analysis object), analysis establishment, calculation parameter setting, fatigue analysis calculation, and calculation result export. For specific operations, please refer to Figure 2 As shown, when the user uses this analysis method for civil aircraft fatigue to perform civil aircraft fatigue analysis, he can perform the following Figure 2 The operation process shown includes:

[0151] Select the target model corresponding to the test data to be analyzed. During the operation, users can select the model suitable for specific analysis needs through the graphical interface. The system provides a variety of model options to ensure the targeted and accurate analysis;

[0152] The system then performs the BDF import operation. During this operation, the system supports the import of BDF files, including private and public account management, allowing users to directly use BDF files in the shared library or upload personal files. The imported BDF file (which is the internal force solution model) can be instantly converted into a 3D finite element model for easy preview and operation;

[0153] Execute SE creation (i.e., strength check model). This step converts the DBF file into a strength check model. The specific conversion method is based on existing technology and will not be explained here. Subsequent operations will be processed and analyzed based on the SE format model. Users can select specific areas or the entire model from the 3D model and create SE (structural element) with one click. The system automatically recognizes and generates various types of SE, such as frame and panel, simplifying the definition process of structural elements.

[0154] Perform the selection of airframe structural fatigue details. This step allows you to select specific details to be analyzed. During the operation, you can select analysis units as needed or combine them into structural combination units as the starting point for analysis and calculation. Based on SE, users can further create SEA (structural element collection). By selecting SE or directly selecting on the model, the system supports the creation of multiple SEA types, which are closely linked to subsequent analysis to ensure flexibility and depth of analysis.

[0155] The system establishes fatigue analysis algorithms. During operation, the system provides a variety of analysis type options according to typical fatigue analysis scenarios. After the user selects the required analysis method based on the selected details, the system automatically completes the creation of the corresponding fatigue analysis.

[0156] Operators can set calculation parameters, and the system automatically renders the required calculation parameters in the form of a structure tree based on the selected analysis. In combination with the model library in the basic database, automatic initialization of geometric parameters can be achieved. Based on the internal force solution library, users can select the internal force batch to be used in the analysis. In addition, based on basic databases such as the material library and fastener library, users can customize analysis parameters, including material properties, fastener types, and connection parameters, to meet different engineering needs.

[0157] During fatigue analysis, the algorithm scheduling module reads the corresponding algorithm configuration based on the calculation request and parameter object, submits and schedules the corresponding algorithm execution task. The parallel computing module performs the calculation and automatically generates a calculation log, including the calculation steps and all intermediate calculation results. A typical process of performing fatigue analysis;

[0158] Fatigue result export: During the operation, after the system performs the calculation, the intermediate process and final results can be intuitively displayed, and the results can be exported as Excel files to facilitate subsequent analysis and report preparation.

[0159] The operation process of performing fatigue analysis calculation can be found in Figure 3 The specific operations are as follows:

[0160] Import the OP2 file (i.e. the test data information to be analyzed, that is, the original data of the internal force solution file), and enter the detailed unit number of the object to be analyzed (i.e. the information of the object to be analyzed);

[0161] The system reads the internal force solution file information;

[0162] Calculate operating stresses for fatigue hazard details;

[0163] Select the calculation section;

[0164] Filter the loads of each working condition under this section;

[0165] Calculate the stress of the far-field tensile combined load case of the selected details;

[0166] Combined with the load sequence output by the load spectrum module in the system, the fatigue working stress spectrum is calculated;

[0167] The fatigue working stress spectrum is simplified using the rain flow calculation method;

[0168] Combined with the fatigue assessment rating (CFQ value) of the detail to be analyzed, fatigue damage calculation is performed;

[0169] Fatigue margin calculations are then performed;

[0170] Finally, fatigue result output is generated.

[0171] The above method can realize the full process of automated analysis, effectively improving efficiency, and realizing the full process automation from model import (BDF file → 3D mesh model), structural element (SE / SEA) creation, parameter setting to fatigue calculation. Parallel computing optimization is achieved through the algorithm arrangement module. The actual measurement efficiency is improved by more than 50% (integrated distributed computing framework), and supports the rapid evaluation of multiple rounds of design iterations (result export and model adaptation in seconds).

[0172] The above analysis method for civil aircraft fatigue has the following advantages:

[0173] 1) By adopting an automated and intelligent operation mode, human intervention can be reduced, and fatigue analysis calculations can be automated. Combined with intelligent data processing, the accuracy and efficiency of the analysis are improved. By integrating the entire process of typical fatigue analysis, the need for human intervention is significantly reduced. For example, in the calculation and adjustment of working stress, the analysis efficiency is effectively improved.

[0174] 2) Through Web-based integration technology: Integrate complex fatigue analysis processes into Web-based applications to achieve seamless cross-platform and multi-scenario applications, lower the usage threshold, and adapt to diverse office scenarios: support fatigue analysis needs in various office environments, whether working remotely or on-site, can provide a consistent analysis experience, enhance the universality and flexibility of the method, avoid the installation of local software, support remote collaboration, and reduce deployment costs; compatible with multiple algorithm languages (such as Matlab / FORTRAN), suitable for complex fatigue analysis scenarios, and facilitate business collaboration.

[0175] 3) Utilize efficient data storage strategies to support rapid evaluation of multiple rounds of design iterations, optimize the design feedback loop, accelerate design iterations, and based on the storage mechanism of fatigue analysis data, quickly evaluate the effects of multiple rounds of design iterations, shorten the cycle from design to verification, and speed up product development progress.

[0176] 4) Standardization and normalization: The originally scattered fatigue analysis processes and data are managed in a unified manner, and a standardized management and control process is established to ensure the controllability of input parameters and the accuracy of output data, thereby improving the reliability and consistency of fatigue analysis.

[0177] 5) Facilitate review work: By standardizing the output format of intermediate results and fatigue analysis results, the review process is simplified, making it easier for experts to quickly and effectively evaluate the analysis results and accelerating the decision-making process.

[0178] In a third aspect, the present invention further provides a fatigue analysis and processing device, comprising:

[0179] At least one processor; a memory coupled to the at least one processor, the memory storing executable instructions, wherein the executable instructions, when executed by the at least one processor, enable the method of the second aspect of the present invention to be implemented.

[0180] This embodiment provides a fatigue analysis and processing device, comprising: at least one processor; and a memory coupled to the at least one processor. The processor and the memory may be provided separately or integrated together.

[0181] For example, the memory may include random access memory, flash memory, read-only memory, programmable read-only memory, non-volatile memory, or registers. The processor may be a central processing unit (CPU), or a graphics processing unit (GPU). The memory may store executable instructions. The processor may execute the executable instructions stored in the memory to implement the various processes described herein.

[0182] It is understood that the memory in this embodiment may be a volatile memory or a non-volatile memory, or may include both volatile and non-volatile memories. Among them, the non-volatile memory may be a ROM (Read-Only Memory), a PROM (Programmable ROM), an EPROM (Erasable PROM), an EEPROM (Electrically EPROM), or a flash memory. The volatile memory may be a RAM (Random Access Memory), which is used as an external cache. By way of example and not limitation, many forms of RAM are available, such as SRAM (Static RAM), DRAM (Dynamic RAM), SDRAM (Synchronous DRAM), DDR SDRAM (Double Data Rate SDRAM), ESDRAM (Enhanced SDRAM), SLDRAM (Synchlink DRAM), and DRRAM (Direct Rambus RAM). The memory 42 described herein is intended to include, but is not limited to, these and any other suitable types of memory.

[0183] In some embodiments, the memory stores the following elements, upgrade packages, executable units or data structures, or a subset or extended set thereof: an operating system and applications.

[0184] The operating system includes various system programs, such as the framework layer, core library layer, and driver layer, which are used to implement various basic services and handle hardware-based tasks. The application program includes various application programs used to implement various application services. The program implementing the method of the embodiment of the present invention can be included in the application program.

[0185] In an embodiment of the present invention, the processor is used to execute the method steps provided in the second aspect by calling a program or instruction stored in a memory, specifically, a program or instruction stored in an application.

[0186] In a fourth aspect, an embodiment of the present invention further provides a chip for executing the method of the second aspect. Specifically, the chip includes: a processor for calling and running a computer program from a memory, so that a device equipped with the chip executes the method of the second aspect.

[0187] In a fifth aspect, the present invention further provides a computer-readable storage medium having a computer program stored thereon, which implements the steps of the method of the second aspect of the present invention when the computer program is executed by a processor.

[0188] For example, machine-readable storage media may include, but are not limited to, various known and unknown types of non-volatile memory.

[0189] In a sixth aspect, an embodiment of the present invention further provides a computer program product, comprising computer program instructions, which enable a computer to execute the method in the second aspect above.

[0190] It will be understood by those skilled in the art 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 software and electronic hardware. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art may use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of this application.

[0191] In the embodiments of the present application, the disclosed systems, devices, and methods can be implemented in other ways. For example, the division of units is merely a logical functional division, and other division methods can be used in actual implementation. For example, multiple units or components can be combined or integrated into another system. In addition, the coupling between the various units can be direct coupling or indirect coupling. In addition, the various functional units in the embodiments of the present application can be integrated into a processing unit, or can exist separately physically, etc.

[0192] It should be understood that in the various embodiments of the present application, the size of the serial number of each process does not mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of the present application.

[0193] If the functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a machine-readable storage medium. Therefore, the technical solution of the present application can be embodied in the form of a software product, which can be stored in a machine-readable storage medium, which can include several instructions for enabling an electronic device to execute all or part of the process of the technical solution described in the embodiments of the present application. The above-mentioned storage medium can include various media that can store program codes, such as ROM, RAM, removable disk, hard disk, magnetic disk or optical disk.

[0194] The preferred embodiments of the present invention have been described in detail above. It should be understood that numerous modifications and variations based on the concepts of the present invention are possible without inventive effort by those skilled in the art. Therefore, any technical solution that can be derived by one skilled in the art through logical analysis, reasoning, or limited experimentation based on the concepts of the present invention and the prior art should be within the scope of protection defined by the claims.

Claims

1. A fatigue analysis system for civil aircraft, characterized by: The system comprises: The data collection module includes an analysis parameter collection unit, wherein the analysis parameter collection unit is used to obtain information about the test data to be analyzed and information about the object to be analyzed; Algorithm and basic data storage module, used to store the system preset algorithms and basic data resources used for fatigue analysis; An algorithm call arrangement module is used to respond to the information of the object to be analyzed, call the corresponding algorithm and basic data resources from the algorithms to be called and basic data resources, and generate a fatigue analysis algorithm corresponding to the object to be analyzed; The calculation result generating module is used to perform fatigue analysis on the object to be analyzed based on the fatigue analysis algorithm and the test data information to be analyzed, so as to generate a fatigue analysis calculation result of the object to be analyzed.

2. The fatigue analysis system for civil aircraft according to claim 1, characterized in that: The algorithm and basic data storage module include: Professional basic data storage unit, including preset related algorithms and basic data resources for fatigue analysis; General basic algorithm storage unit, including preset general algorithm resources; The algorithms and basic data resources to be called are jointly constituted by the relevant algorithms and basic data resources for fatigue analysis and the general algorithm resources.

3. The fatigue analysis system for civil aircraft according to claim 1, characterized in that: The algorithm call arrangement module includes: An algorithm scheduling engine, configured to call a corresponding algorithm from the algorithm and basic data storage module in response to the information of the object to be analyzed; A universal data access engine, configured to call corresponding basic data resources from the algorithm and basic data storage module in response to the information of the object to be analyzed; The algorithm generation module is used to generate a fatigue analysis algorithm corresponding to the object to be analyzed based on the algorithm called by the algorithm scheduling engine and the basic data resources called by the general data access engine.

4. The fatigue analysis system for civil aircraft according to claim 1, characterized in that: The system also includes an AI engine module and an AI machine learning algorithm library. The AI engine module is used to schedule algorithms in the AI machine learning algorithm library to assist in analyzing civil aircraft fatigue conditions.

5. The fatigue analysis system for civil aircraft according to claim 1, characterized in that: The calculation result generation module includes: a calculation unit, configured to perform fatigue analysis on the object to be analyzed based on the fatigue analysis algorithm and the test data information to be analyzed, so as to generate a fatigue analysis calculation result of the object to be analyzed; A report generating unit, configured to generate a fatigue analysis strength verification report based on the information of the object to be analyzed and the fatigue analysis calculation result of the object to be analyzed; The log generation unit is used to generate log information when the analysis system for civil aircraft fatigue conditions is running.

6. The fatigue analysis system for civil aircraft according to any one of claims 1 to 5, characterized in that: The system further comprises: A data entry and display module is used to receive input instructions and data to be analyzed, send the input instructions and data to be analyzed to the data collection module, and display the fatigue analysis calculation results of the object to be analyzed, wherein the input instructions and data to be analyzed include test data information to be analyzed, object information to be analyzed, customized algorithm instructions, and customized parameter instructions; Among them, the data collection module, algorithm and basic data storage module, algorithm call orchestration module and calculation result generation module are located in the cloud server, and the data entry and display module is located in the user-end device. The user-end device can realize data interaction with the cloud server through the WEB terminal.

7. The fatigue analysis system for civil aircraft according to claim 6, characterized in that: The cloud server also includes: User authority management module, used to manage the authority of each operating account; The project management module is used to manage each civil aircraft fatigue analysis project.

8. A method for analyzing fatigue conditions of civil aircraft, characterized in that: The analysis method includes performing a detection object acquisition operation and a calculation and analysis operation; The detection object acquisition operation at least includes: acquiring the test data information to be analyzed and the object information to be analyzed; The calculation and analysis operation at least includes: combining the test data information to be analyzed and responding to the information of the object to be analyzed, calling the corresponding algorithm and basic data resources from the system's preset algorithms and basic data resources to be called, generating a fatigue analysis algorithm corresponding to the object to be analyzed, and performing fatigue analysis on the object to be analyzed based on the fatigue analysis algorithm and the test data information to be analyzed to generate a fatigue analysis calculation result for the object to be analyzed.

9. The method for analyzing fatigue conditions of civil aircraft according to claim 8, characterized in that: The calculation and analysis operations specifically include: Acquire the test data information to be analyzed to read the internal force solution file information, and determine the object to be analyzed through the acquired information of the object to be analyzed; In response to the information of the object to be analyzed, based on the internal force solution file information, a corresponding algorithm and basic data resource are retrieved from the algorithms and basic data resources to be called, and a working stress algorithm for fatigue hazard details in the fatigue analysis algorithm corresponding to the object to be analyzed is generated; Obtaining the working stress of the fatigue hazard details corresponding to the object to be analyzed based on the working stress algorithm of the fatigue hazard details; In response to information of an object to be analyzed, a cross-section corresponding to the object to be analyzed is determined, and based on the working stress of the fatigue hazard details corresponding to the object to be analyzed, corresponding algorithms and basic data resources are retrieved from the algorithms to be called and basic data resources, to generate load algorithms for each working condition corresponding to the cross-section in the fatigue analysis algorithm corresponding to the object to be analyzed, Based on the load algorithms for each working condition corresponding to the cross section, the loads for each working condition under the cross section are screened out; Based on the selected loads of each working condition under the cross section, the corresponding algorithm and basic data resources are retrieved from the to-be-called algorithm and basic data resources to generate a far-field tensile combined working condition stress algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed; Determining the far-field tensile combined working condition stress of the object to be analyzed based on the far-field tensile combined working condition stress algorithm; Determine the load sequence based on the preset load spectrum; Based on the load sequence and the far-field tensile combined working condition stress of the object to be analyzed, and in combination with calling corresponding algorithms and basic data resources from the to-be-called algorithms and basic data resources, a fatigue working stress spectrum algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed is generated; Determining the fatigue working stress spectrum of the object to be analyzed based on the fatigue working stress spectrum algorithm; Simplifying the fatigue working stress spectrum of the object to be analyzed by using a rain flow calculation method to generate a simplified fatigue working stress spectrum; Retrieving a corresponding algorithm and basic data resource from the algorithms and basic data resources to be called, and generating a fatigue assessment rating algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed; determining a fatigue assessment rating of the object to be analyzed based on the fatigue assessment rating algorithm; Based on the simplified fatigue working stress spectrum and the fatigue assessment rated value, a fatigue damage calculation algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed is generated in combination with the corresponding algorithm and basic data resources retrieved from the to-be-called algorithm and basic data resources; Determining fatigue damage of the object to be analyzed based on the fatigue damage calculation algorithm; Based on the fatigue damage of the object to be analyzed, a fatigue margin algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed is generated by combining corresponding algorithms and basic data resources retrieved from the algorithms to be called and basic data resources; Determining the fatigue margin of the object to be analyzed based on the fatigue margin algorithm; Based on the fatigue margin of the object to be analyzed, a fatigue result algorithm in the fatigue analysis algorithm corresponding to the object to be analyzed is generated by calling a corresponding algorithm and basic data resource from the algorithm to be called and the basic data resource; Based on the fatigue result algorithm, a fatigue analysis calculation result of the object to be analyzed is generated.

10. The method for analyzing fatigue conditions of civil aircraft according to claim 8, characterized in that: The analysis method further includes executing result output operations and log recording operations; The result output operation is used to output the fatigue analysis calculation results of the object to be analyzed; The logging operation is used to generate log information during the operation of the civil aircraft fatigue analysis system.

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