Airplane component intelligent assembly data management system based on compliance verification

Abstract

The invention relates to an aircraft component intelligent assembly data management system based on compliance verification, and belongs to the technical field of aerospace manufacturing. In order to solve the problems of data dispersion, low verification efficiency and difficulty in quality tracing in the aircraft component assembly process, the system comprises a standard process library construction unit used for constructing an aircraft component assembly standard process library which is clear in classification and contains detailed specifications; the assembly information acquisition unit is used for collecting assembly data in multiple channels and processing the assembly data into a structured data set; the data management system unit is used for integrating multi-source data and analyzing historical data and verification results to form a trend table so as to realize overall management; and the qualification checking unit is used for checking real-time data in multiple dimensions, generating a report and performing synchronous early warning. According to the system, intelligent management of the aircraft component assembly process is realized, the data processing efficiency and accuracy are improved, and the assembly quality and the safety and reliability of an aircraft are guaranteed.

Description

Technical Field

[0001] This invention belongs to the field of aerospace manufacturing technology, specifically relating to an intelligent assembly data management system for aircraft components based on compliance verification. Background Technology

[0002] In the aerospace manufacturing field, the complexity and high precision requirements of aircraft component assembly place stringent demands on the integrity, timeliness of verification, and traceability of data management. Traditional assembly data management models have significant shortcomings: data acquisition and storage are discrete, key information such as process parameters, environmental indicators, and positioning accuracy lack structured integration, making them prone to redundancy and omissions; compliance verification relies on manual comparison with standard documents, which is inefficient and susceptible to subjective factors, easily leading to potential quality issues; the data traceability chain is not continuous, making it difficult to quickly retrieve relevant information when quality problems occur; and the historical data reuse rate is low, requiring repeated resource investment in data sorting during process improvement or new aircraft model development, which restricts the improvement of assembly intelligence and quality stability. Summary of the Invention

[0003] To address the aforementioned problems in the existing technology, this invention provides an intelligent assembly data management system for aircraft components based on compliance verification. The objective of this invention can be achieved through the following technical solutions: The standard process library construction unit is used to build a standard process library covering all types of aircraft components. The library is structured and classified according to component type, assembly stage, and process type. The categories of the structured classification are process step description, process parameter range, environmental requirements, positioning accuracy standards, and corresponding compliance judgment rules. The assembly information acquisition unit is used to collect environmental data at the assembly site; obtain real-time process parameters and assembly data through the intelligent monitoring module of the assembly equipment; capture real-time positioning coordinates, assembly gaps, hole deviations and positioning accuracy data of components using high-precision visual inspection equipment and measuring tools; and interface with the manufacturing execution subsystem to form a structured assembly information dataset after data cleaning and format standardization. The data management system unit is used to connect with the standard process library construction module, the assembly information acquisition module, and the conformity verification module, and to integrate the real-time process parameters, the real-time assembly data, and the verification result report from multiple sources in a structured manner; and to obtain a data trend analysis table by performing data trend analysis on historical assembly data and verification results through a data analysis model. The qualification verification unit is used to perform multi-dimensional verification on the real-time data transmitted by the assembly information acquisition module, including environmental adaptation verification, process parameter verification and positioning accuracy verification. After the verification is completed, a report containing detailed results of each item is generated, annotating the abnormal location, deviation value and standard basis, and synchronized to the data management system and the assembly site terminal.

[0004] Specifically, the standard process library construction unit provides benchmark data for the conformity verification unit; the real-time data collected by the assembly information acquisition unit serves as the input to the conformity verification unit; and the data management system unit receives the data from the first three units, integrates and analyzes trends to form a closed-loop management system.

[0005] Specifically, the standard process library includes basic component information, assembly stage division, process type, environmental requirements, positioning accuracy standards, and compliance judgment rules. The basic component information, assembly stage division, process type, environmental requirements, positioning accuracy standards, and compliance judgment rules are used to construct a standard process library module based on a preset standard process library template.

[0006] Specifically, the assembly information acquisition unit is constructed as follows: Based on the information dimension requirements and real-time requirements of aircraft component assembly, the required real-time process parameters, real-time assembly data, and positioning accuracy data types are identified, and a multi-dimensional acquisition scheme is designed, determining the selection criteria for acquisition tools. According to the communication protocols and data formats of the acquisition tools, standardized acquisition interfaces are designed, and data cleaning and format conversion processing rules are formulated to ensure the consistency and usability of data from different sources. Data acquisition and transmission functional modules are developed according to the design scheme, integrating sensors, detection equipment, and modules, and debugging is performed to ensure the continuity and accuracy of data acquisition. Based on the actual needs of the assembly scenario, the data acquired by the modules is verified, and any anomalies are optimized.

[0007] Specifically, the data management system unit construction process is as follows: Based on system collaboration requirements and aviation data management specifications, the interfaces that modules need to interface with are clearly defined, and the aviation data standards and business function requirements that need to be met are determined. A hybrid architecture of edge nodes and a central database is adopted, with real-time process parameters stored on the assembly line edge server and historical data and verification reports stored in the central database, and interfaces for interaction with the product lifecycle management system are reserved. According to data types and aviation data characteristics, a structured model is constructed according to data types, data association rules are defined, and storage strategies are formulated for different data characteristics. Based on module functional requirements and system compatibility requirements, core functional modules for data access, access control, data analysis, and security protection are developed and tested in conjunction with other modules. According to aviation industry standards and system performance requirements, the compliance of modules is reviewed in accordance with aviation industry standards, and system bottlenecks are located and resolved through stress testing.

[0008] As a preferred embodiment of the present invention, the conformity verification unit includes a rule definition model, a data verification model, an anomaly handling model, a result archiving model, and a compliance output model. In the data verification model, data calculation requires consideration of engineering standards, design requirements, and actual measurement data. The core principle is to set a conformity threshold using theoretical formulas and then compare it with actual measured data to complete the verification. The specific calculation method includes: The formula for calculating the spatial comprehensive deviation is as follows: Where ΔL is the spatial position deviation in millimeters, ΔX is the position deviation on the X-axis, ΔY is the position deviation on the Y-axis in millimeters, and ΔZ is the position deviation on the Z-axis in millimeters. If both the single-axis deviation and the overall deviation meet the design threshold, the position is deemed qualified. Formula for calculating geometric tolerance verification of component profile: Flatness tolerance calculation uses the least squares method to fit an ideal plane. Let the equation of the fitted plane be: ax + by + cz + d = 0. Calculate the flatness tolerance at each measurement point. Distance to the plane: Flatness tolerance The difference between the maximum and minimum distances, when At that time, among them The flatness tolerance threshold is used to determine whether the condition is acceptable. Profile tolerance calculation is based on the theoretical profile line of curved surface design. Calculate the actual measurement points Shortest distance to the theoretical profile: Take the maximum deviation of all points ,when At that time, among them The contour threshold is used to determine if it is qualified.

[0009] Specifically, the compliance verification unit's verification process is as follows: It calls the benchmark data from the standard process library and matches it with the real-time dataset from the assembly information acquisition unit. Then, based on component characteristics, it adaptively selects a combination algorithm for spatial coordinate matching and geometric tolerance verification. Environmental adaptation verification uses a multi-parameter coupled evaluation model to construct an environmental adaptation index based on weighted factors and maps deviation to determine adaptability. Process parameter verification utilizes a long short-term memory network to extract parameter fluctuation amplitude, frequency, and derivative features, combines them with environmental interference factors to construct a feature matrix, and identifies abnormal patterns through dynamic thresholds. Positioning accuracy verification decomposes translation and rotation errors using an iterative nearest-point algorithm, and calculates the contribution weight of each component based on tolerance levels to evaluate the overall deviation. The triple verification mechanism is simultaneously activated to ensure verification reliability, ultimately generating a structured report containing deviation data and standard basis, providing compliance judgment and anomaly warning support for the assembly process.

[0010] The beneficial effects of this invention are as follows: (1) By setting up real-time compliance verification, it can automatically check every step of the aircraft component assembly process, part specifications, and installation sequence, and promptly detect deviations that do not meet aviation safety standards. This process reduces the subjectivity and oversight of human judgment, reduces assembly errors caused by violations of regulations from the source, ensures that the entire assembly process strictly follows industry norms and technical requirements, and greatly improves the compliance of aircraft component assembly and the quality accuracy of the final product. (2) By setting up a system for centralized collection, storage and management of assembly data, the limitations of traditional scattered data recording are broken; on the one hand, the automatically generated conformity report data can provide clear and complete basis for subsequent inspection and review, improving work efficiency; on the other hand, complete historical assembly data can realize full-process traceability, and when quality problems occur, the problem link can be quickly located and the cause analyzed, providing data support for fault diagnosis and process optimization, while also meeting the stringent requirements of the aviation industry for product life cycle data management. Attached Figure Description

[0011] To facilitate understanding by those skilled in the art, the present invention will be further described below with reference to the accompanying drawings: Figure 1 This is a system architecture diagram of an intelligent assembly data management system for aircraft components based on compliance verification, according to the present invention. Detailed Implementation

[0012] To further illustrate the technical means and effects adopted by the present invention to achieve the intended purpose, the specific embodiments, structures, features, and effects of the present invention will be described in detail below with reference to the accompanying drawings and preferred embodiments: Please see Figure 1A smart assembly data management system for aircraft components based on compliance verification. Includes: a standard process library construction unit, an assembly information acquisition unit, a data management system unit, and a compliance verification unit; The standard process library construction unit is used to build a standard process library covering all types of aircraft components. The library is structured and classified according to component type, assembly stage, and process type. The categories of the structured classification are process step description, process parameter range, environmental requirements, positioning accuracy standards, and corresponding compliance judgment rules. The assembly information acquisition unit is used to collect environmental data at the assembly site; obtain real-time process parameters and assembly data through the intelligent monitoring module of the assembly equipment; capture real-time positioning coordinates, assembly gaps, hole deviations and positioning accuracy data of components using high-precision visual inspection equipment and measuring tools; and interface with the manufacturing execution subsystem to form a structured assembly information dataset after data cleaning and format standardization. The data management system unit is used to connect with the standard process library construction module, the assembly information acquisition module, and the conformity verification module, and to integrate the real-time process parameters, the real-time assembly data, and the verification result report from multiple sources in a structured manner; and to obtain a data trend analysis table by performing data trend analysis on historical assembly data and verification results through a data analysis model. The qualification verification unit is used to perform multi-dimensional verification on the real-time data transmitted by the assembly information acquisition module, including environmental adaptation verification, process parameter verification and positioning accuracy verification. After the verification is completed, a report containing detailed results of each item is generated, annotating the abnormal location, deviation value and standard basis, and synchronized to the data management system and the assembly site terminal.

[0013] Specifically, the standard process library construction unit provides benchmark data for the conformity verification unit; the real-time data collected by the assembly information acquisition unit serves as the input for the conformity verification unit; and the data management system unit receives the data from the first three units, integrates and analyzes trends to form a closed-loop management system.

[0014] In this embodiment, taking the docking process between the mid-section and aft section of the aircraft fuselage as an example, the standard process library construction unit provides the benchmark data for this process in advance; the assembly information acquisition unit collects the real-time coordinates of the docking surface through a laser scanner and the bolt preload through a torque sensor, and synchronizes the data to the qualification verification unit; the qualification verification unit compares the real-time data with the benchmark data, determines the flatness and preload, and generates a verification report; the data management system unit receives the benchmark data, real-time data, and verification report, integrates them to form a data archive for the fuselage docking process, analyzes the data trends through a time series model, provides a basis for process optimization, and realizes a closed loop of benchmark, acquisition, verification, and analysis.

[0015] Specifically, the standard process library includes basic component information, assembly stage division, process type, environmental requirements, positioning accuracy standards, and compliance judgment rules. The basic component information, assembly stage division, process type, environmental requirements, positioning accuracy standards, and compliance judgment rules are used to construct a standard process library module based on a preset standard process library template.

[0016] In this embodiment, for the assembly of aircraft landing gear struts, a standard process library module is constructed according to a preset template: basic component information, assembly stage division, process type, environmental requirements, positioning accuracy standards, and compliance judgment rules; the template adopts a tree structure, and data filling and module generation are completed through a structured data entry tool.

[0017] Specifically, the assembly information acquisition unit is constructed as follows: Based on the information dimension requirements and real-time requirements of aircraft component assembly, the required real-time process parameters, real-time assembly data, and positioning accuracy data types are identified, and a multi-dimensional acquisition scheme is designed, determining the selection criteria for acquisition tools. According to the communication protocols and data formats of the acquisition tools, standardized acquisition interfaces are designed, and data cleaning and format conversion processing rules are formulated to ensure the consistency and usability of data from different sources. Data acquisition and transmission functional modules are developed according to the design scheme, integrating sensors, detection equipment, and modules, and debugging is performed to ensure the continuity and accuracy of data acquisition. Based on the actual needs of the assembly scenario, the data acquired by the modules is verified, and any anomalies are optimized.

[0018] In this embodiment: for the assembly of aircraft engine compartment, it is clear that torque and pressure process parameters, component number assembly data, concentricity positioning data, and real-time torque delay need to be collected. A suitable solution is adopted, and the accuracy standard of torque sensor and the error of tracker are specified. A standardized interface is designed, and rules for outlier rejection and format conversion are formulated. An acquisition module with edge computing nodes is developed. After connecting the equipment, it is debugged for 72 hours to ensure that the data interruption is less than 1 second. During trial assembly, the low-temperature torque delay is reduced from 0.3 seconds to 0.08 seconds by adding a heating jacket, and the data validity rate is confirmed to be qualified.

[0019] Specifically, the data management system unit construction process is as follows: Based on system collaboration requirements and aviation data management specifications, the interfaces that modules need to interface with, the aviation data standards they must meet, and the business function requirements are clearly defined. A hybrid architecture of distributed storage and centralized management is determined, and interfaces for interaction with external systems are reserved. Based on data types and aviation data characteristics, a structured model is constructed according to data types, data association rules are defined, and storage strategies are formulated for different data characteristics. Based on module functional requirements and system compatibility requirements, core functional modules for data access, access control, data analysis, and security protection are developed and tested in conjunction with other modules. Based on aviation industry standards and system performance requirements, the compliance of modules is reviewed according to aviation industry standards, and system bottlenecks are located and resolved through stress testing.

[0020] As a preferred technical solution of the present invention, the conformity verification unit includes a rule definition model, a data verification model, an anomaly handling model, a result archiving model, and a compliance output model; wherein, in the data verification model, the calculation of torque value and position coordinates needs to combine engineering standards, design requirements, and actual measurement data. The core is to set a conformity threshold through theoretical formulas and then compare it with the measured data to complete the verification. The specific calculation method includes: The formula for calculating the spatial comprehensive deviation is as follows: Where ΔL is the spatial position deviation in millimeters, ΔX is the position deviation on the X-axis, ΔY is the position deviation on the Y-axis in millimeters, and ΔZ is the position deviation on the Z-axis in millimeters. If both the single-axis deviation and the overall deviation meet the design threshold, the position is deemed qualified. Formula for calculating geometric tolerance verification of component profile: Flatness tolerance calculation uses the least squares method to fit an ideal plane. Let the equation of the fitted plane be: ax + by + cz + d = 0. Calculate the flatness tolerance at each measurement point. Distance to the plane: Flatness tolerance The difference between the maximum and minimum distances, when At that time, among them The flatness tolerance threshold is used to determine whether the condition is acceptable. Profile tolerance calculation is based on the theoretical profile line of curved surface design. Calculate the actual measurement points Shortest distance to the theoretical profile: Take the maximum deviation of all points ,when At that time, among them The contour threshold is used to determine if it is qualified.

[0021] In this embodiment, taking the docking of the aircraft's vertical tail and rear fuselage as an example, in the spatial comprehensive deviation calculation, the measured coordinates and theoretical coordinates have ΔX=0.2 mm, ΔY=0.1 mm, and ΔZ=0.3 mm, respectively. Substituting these values ​​into the formula, ΔL equals 0.37 mm, which meets the thresholds of single axis ≤ 0.4 mm and ΔL ≤ 0.5 mm, thus the position is deemed qualified. The flatness calculation uses the least squares method to fit the plane equation, and the distance difference between the 10 measurement points is 0.04 mm ≤ the threshold of 0.06 mm. In the contour calculation, the maximum distance from the 20 points to the theoretical surface is 0.08 mm ≤ the threshold of 0.1 mm. Finally, the data verification model determines that the positioning accuracy is qualified and synchronizes it to subsequent models.

[0022] In this embodiment, the compliance verification unit's verification process is as follows: It calls the benchmark data from the standard process library and matches it with the real-time dataset from the assembly information acquisition unit. Then, based on component characteristics, it adaptively selects a combination algorithm of spatial coordinate matching and geometric tolerance verification. Specifically, the environmental adaptation verification uses a multi-parameter coupled evaluation model to construct an environmental adaptation index based on weighted factors and maps deviation to determine adaptability. The process parameter verification utilizes a long short-term memory network to extract parameter fluctuation amplitude, frequency, and derivative features, combines them with environmental interference factors to construct a feature matrix, and identifies abnormal patterns through dynamic thresholds. The positioning accuracy verification decomposes translation and rotation errors using an iterative nearest-point algorithm, combines tolerance levels to calculate the contribution weight of each component to evaluate the overall deviation. Simultaneously, the triple verification mechanism is activated to ensure verification reliability, ultimately generating a structured report containing deviation data and standard basis, providing compliance judgment and anomaly warning support for the assembly process.

[0023] In this embodiment, the working principle and usage process of the invention are as follows: Initialize and build a standard process library and deploy the system. The standard process library provides a benchmark. The assembly information acquisition unit collects and processes multi-source data. The data management system integrates the data to generate a trend table, supporting traceability and process optimization. At the same time, data security is ensured through key management. The qualification verification unit verifies the environment, process parameters, and positioning accuracy based on the benchmark, generates reports and issues warnings, and performs closed-loop management.

[0024] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make some modifications or alterations to the above-disclosed technical content to create equivalent embodiments without departing from the scope of the present invention. Any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the scope of the present invention shall still fall within the scope of the present invention.

Claims

1. A smart assembly data management system for aircraft components based on compliance verification, characterized in that, include: Standard process library construction unit, assembly information acquisition unit, data management system unit, and conformity verification unit; The standard process library construction unit is used to build a standard process library covering all types of aircraft components. The library is structured and classified according to component type, assembly stage, and process type. The categories of the structured classification are process step description, process parameter range, environmental requirements, positioning accuracy standards, and corresponding compliance judgment rules. The assembly information acquisition unit is used to collect environmental data at the assembly site; real-time process parameters and assembly data are obtained through the intelligent monitoring module of the assembly equipment; high-precision visual inspection equipment and measuring tools are used to capture real-time positioning coordinates, assembly gaps, hole position deviations and positioning accuracy data of components; the data is then connected to the manufacturing execution subsystem and formed into a structured assembly information dataset after data cleaning and format standardization. The data management system unit is used to connect with the standard process library construction module, the assembly information acquisition module, and the conformity verification module to structure and integrate the real-time process parameters, the real-time assembly data, and the verification result report from multiple sources. A data trend analysis table is obtained by performing data trend analysis on historical assembly data and verification results using a data analysis model. The qualification verification unit is used to perform multi-dimensional verification on the real-time data transmitted by the assembly information acquisition module, including environmental adaptation verification, process parameter verification and positioning accuracy verification. After verification, a report containing detailed results is generated, marking the location of anomalies, deviation values, and standard basis, and synchronized to the data management system and assembly site terminal.

2. The assembly information acquisition unit according to claim 1, characterized in that, The manufacturing execution subsystem receives information from the manufacturing execution system as a baseline correlation item for data acquisition, pushes the preliminarily cleaned real-time assembly data to the manufacturing execution system, and the manufacturing execution system provides feedback on data verification rules to assist in completing format standardization processing, and integrates multi-source data into a structured assembly information dataset.

3. The data management system unit according to claim 1, characterized in that, The data trend analysis classifies historical data by component type and assembly process, uses a time series decomposition model to extract long-term trend items and periodic fluctuation items, combines control chart method to identify parameter thresholds, and then uses clustering algorithm to classify abnormal patterns to obtain a data trend analysis table containing trend direction, fluctuation range and abnormal warning line.

4. The data management system unit according to claim 1, characterized in that, The system key management module generates a root key and stores it in the hardware security module. Based on the root key, role keys and unique user keys are derived. When data is loaded into the database, it is encrypted using an algorithm to generate a unique data encryption key. The unique data encryption key is then encrypted using the corresponding role key or user key, and only the encrypted unique data encryption key and the ciphertext data are retained. Administrators can decrypt all role keys using the root key to obtain full access to the data. When operators log in, the system verifies their identity and issues them a user key, which can only decrypt the unique data encryption key that the user operates on.

5. The conformity verification unit according to claim 1, characterized in that, The environmental adaptation verification adopts a multi-parameter coupled evaluation model, which constructs an environmental adaptation index by weighting the on-site environmental parameters. The deviation between the real-time parameters and the standard range is mapped by the exponential function. When the deviation exceeds the threshold, a graded warning is triggered.

6. The compliance verification unit according to claim 1, characterized in that, The abnormal trend analysis of the process parameter verification adopts a multi-dimensional time series feature fusion model to extract the fluctuation amplitude, frequency and derivative features of real-time process parameters, and construct a feature matrix by combining environmental parameter interference factors. The long short-term memory network is used to capture the time series dependency relationship between parameters, and a dynamic threshold is set to identify abnormal patterns to obtain a graded early warning report table.

7. The conformity verification unit according to claim 1, characterized in that, The positioning accuracy verification uses an iterative nearest-point algorithm to register the measured coordinates with the theoretical model, decomposes the translation error and rotation error, and calculates the contribution weight of each error component by combining the tolerance level of the positioning reference in the process library. When the comprehensive weighted error exceeds the preset threshold, a visual verification report is generated.

8. The compliance verification unit according to claim 1, characterized in that, The spatial coordinate matching algorithm selection module of the qualification verification unit first identifies the component type. For structural components, the spatial coordinate matching algorithm is used first. For precision components, the spatial coordinate matching and geometric tolerance verification algorithms are automatically combined. For curved surface components, the geometric tolerance verification algorithm is emphasized. The matching result is output after triple verification.

9. The compliance verification unit according to claim 8, characterized in that, The spatial coordinate matching calculation method of the compliance verification unit specifically includes: Spatial coordinate matching calculates positional deviations using three-dimensional geometric relationships, and the overall deviation is considered acceptable if it is within a preset threshold. In geometric tolerance verification, flatness is determined by calculating the distance difference after fitting the plane using the least squares method, and profile is determined by taking the maximum value of the shortest distance from the measured point to the theoretical profile. Both are considered acceptable if they do not exceed the corresponding threshold.

10. The compliance verification unit according to claim 8, characterized in that, The triple verification calculation method for compliance verification specifically includes: The calculation process for spatial coordinate matching or geometric tolerance verification is reverse-engineered; the original measurement data is re-substituted to verify the formula parameters; the deviation threshold of the component type is checked, and if the calculation result deviates from the reverse-engineering, it is directly marked as a verification anomaly; qualified verification data of similar components are called to generate historical deviation distribution curves; if the current component deviation is within the range, the trend is judged to be normal; if it exceeds the range, it is marked as a trend anomaly when calculating the deviation growth rate; if the algorithm logic verification is qualified and the trend is normal, it is directly output as qualified; if the algorithm logic verification is qualified and the trend is abnormal, it is automatically pushed to the 3D visualization platform.

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