Detailed process design method and system for aircraft component assembly and medium

Abstract

The invention relates to the technical field of aircraft manufacturing, and discloses a detailed process design method and system for aircraft component assembly and a medium, and the method comprises the steps: building a process procedure template corresponding to an assembly scene according to an assembly process flow and a standard process library; according to the method, technological procedure node planning and technological procedure material planning are carried out from the two dimensions of assembling scene space and time, a technological parameter library is established according to technological knowledge and technological rules, and finally technological procedure document compiling is automatically carried out, so that the detailed airplane component assembling technology is efficiently and accurately designed, and the design efficiency is improved. The technical problems that according to existing aircraft assembly technology design, technological procedure compiling is not combined with the assembly technological process, the technological procedure compiling efficiency is low, and the technological procedure compiling accuracy is low are solved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft manufacturing, and specifically, to a method, system and medium for detailed process design of aircraft component assembly. Background Art

[0002] A process specification is a productive process document compiled by the process department according to design requirements, process technical requirements and quality requirements. The process specification not only includes process information, but also production information and quality information, and is a specific work instruction for guiding workers to actually operate the specified assembly process flow, including operation instructions, processes, assembly time sequences, change records and other information.

[0003] Aircraft assembly process design is an important link in the aircraft manufacturing process. The process design process can be divided into three stages: the preliminary research stage, the research and development stage and the mass production stage. Among them, the research and development stage is the main stage of process design, including work such as process joint design definition, top-level process planning, detailed process design, and on-site execution. The detailed process design work includes a process planning process for material consumption and process specification node planning, and a process specification compilation process for determining the assembly process flow, process parameters, etc.

[0004] At present, research on three-dimensional process specification compilation technology, knowledge engineering application, three-dimensional CAPP technology, etc. is mostly carried out for advanced technologies and advanced platforms. In engineering practice, it is not combined with the assembly process flow and cannot play an accurate role in guiding the process and information during the process of process specification compilation by process personnel. During the process preparation by process personnel, a large amount of time is required for summarization, calculation and copying of process parameters, process standards and process data. The repetitive and cumbersome workload is very large, and the effective work efficiency of process personnel is low, resulting in a long cycle for process specification compilation work, poor standardization of process specification compilation results, and even some quality errors.

[0005] Therefore, a method for detailed process design of aircraft component assembly is needed to solve the technical problems in the existing aircraft assembly process design, such as the lack of combination between process specification compilation and assembly process flow, low efficiency of process specification compilation, and low accuracy of process specification compilation. Summary of the Invention

[0006] The object of the present invention is to provide a method, a system and a medium for detailed process design of aircraft component assembly. The method establishes a process specification template corresponding to the assembly scenario according to the assembly process flow and the standard process library, plans the process specification nodes and the process specification materials from two dimensions of the assembly scenario space and time, establishes a process parameter library according to process knowledge and process rules, and finally automatically prepares the process specification document, realizing the efficient and accurate design of the detailed process of aircraft component assembly, and solving the technical problems of the existing aircraft assembly process design, such as the lack of combination of process specification compilation with the assembly process flow, low efficiency of process specification compilation and low accuracy of process specification compilation.

[0007] The present invention is realized by the following technical solutions: In the first aspect, the present invention provides a method for detailed process design of aircraft component assembly, including: S01. Obtain the digital model information of the assembly scenario; S02. Define the assembly process flow according to the assembly process plan, adjust the assembly process flow according to the production mode and establish the corresponding relationship between the assembly scenario and the process specification template, adjust the assembly process flow of each assembly scenario according to the assembly scenario and the standard process library, establish the process specification execution process and the process specification operation process, and establish the process specification template corresponding to the assembly scenario according to the corresponding relationship between the assembly scenario and the process specification template, the process specification execution process and the process specification operation process; Analyze the digital model information to obtain the analysis result, and obtain the process specification node planning result and the process specification material planning result in two dimensions of the assembly scenario space and time according to the analysis result; Establish a process parameter library according to process knowledge and process rules; S03. Prepare the process specification document according to the process specification template, the process specification material planning result, the process specification node planning result and the process parameter library, and obtain the process specification document representing the detailed process of aircraft component assembly.

[0008] In order to better implement the present invention, further, the step of establishing the process specification template corresponding to the assembly scenario according to the corresponding relationship between the assembly scenario and the process specification template, the process specification execution process and the process specification operation process includes: First, determine the information types included in the process specification, define the generation methods of the information of each component element of the process specification according to the information types and determine the target component elements; Then, according to the assembly process flow of the aircraft, define the hierarchical relationship between the process specification template and the process specification operation to determine the structural form of the process specification operation set and define the corresponding expression method according to the process specification template type of each type of process specification; define the classification methods for the assembly type, process specification template type, and process specification operation type, and establish the corresponding relationship between the process specification operation type and the process specification operation set to obtain the operation parameters of the process specification template. Finally, according to the digital model information of the assembly scenario, obtain the identification conditions of the process specification operation set to determine the operation time sequence. According to the target component elements, hierarchical relationship, and the corresponding relationship between the process specification operation type and the process specification operation set, combine the process specification operations that match the assembly scenario according to the operation time sequence to generate the process specification template corresponding to the assembly scenario.

[0009] To better implement the present invention, further, the method for establishing a process parameter library according to process knowledge and process rules includes: First, define the assembly requirements involved in the assembly process flow, and generate process knowledge and process rules according to the assembly requirements. Then, construct the data association relationship between the process parameter libraries to obtain process parameters in the assembly process flow; generate the process parameter library according to the data association relationship, process knowledge, and process rules. Finally, according to the characteristics of the assembly information in the process of compiling the process specification, define the calculation logic rules for the corresponding process parameter library, construct a parameter acquisition mode for uniformly pushing data for the process parameters under the specified process, and construct a parameter acquisition mode for actively retrieving data for the process parameter library that is common to the entire process.

[0010] To better implement the present invention, further, when compiling the process specification document for the assembly connection of aircraft components, the method for establishing a process parameter library according to process knowledge and process rules includes: Construct the multi-dimensional input / output data form of the assembly connection process parameter library according to the data retrieval scheme, data source, and logic rules of the process parameters used in the aircraft component assembly process flow. Generate the assembly connection process knowledge and assembly connection process rules according to the assembly connection process experience and assembly connection process requirements of the aircraft component assembly connection process. Associate the data tables in the assembly connection process parameter library according to the key fields in the assembly connection process parameter library to construct the data association relationship between the assembly connection process parameter libraries. Establish a process parameter library including the assembly connection operation process parameter library and the assembly connection general process parameter library according to the data association relationship, data form, assembly connection process knowledge, and assembly connection process rules between the assembly connection process parameter libraries. Construct a parameter acquisition mode for uniformly pushing data for the process parameter library of the assembly connection process, and, construct a parameter acquisition mode for actively retrieving data for the general process parameter library of the assembly connection.

[0011] To better implement the present invention, further, after establishing a process specification template corresponding to the assembly scenario, a judgment logic for the assembly elements affecting the assembly process flow of the aircraft component assembly connection is constructed according to the assembly connection process parameter library.

[0012] To better implement the present invention, further, when compiling the process specification document for the aircraft component assembly connection, the method for establishing the process specification template for the aircraft component assembly connection according to the assembly process flow and the standard process library includes: Define the aircraft component assembly elements affecting the assembly process flow of the aircraft component assembly connection; Establish the association relationship between the aircraft component assembly elements and the assembly process flow of the aircraft component assembly connection and construct the assembly process flow of the aircraft component assembly connection; Establish the process specification template for the aircraft component assembly connection according to the assembly process flow of the aircraft component assembly connection and the standard process library.

[0013] To better implement the present invention, further, when compiling the process specification document for the aircraft component assembly connection, the method for obtaining the process specification document representing the detailed process of the aircraft component assembly according to the process specification template, the process specification material planning result, the process specification node planning result, and the process parameter library includes: Define the parameter types of the assembly connection process parameters; According to the materials in the material library involved in the actual aircraft component assembly connection process flow, establish the parameter association relationship between the assembly connection process parameters and construct the acquisition logic of the assembly connection process parameters; According to the acquisition logic, obtain the assembly connection process parameters of the specified parameter type from the process parameter library; Obtain the process specification document for the aircraft component assembly connection according to the process specification template, the process specification material planning result, the process specification node planning result, and the assembly connection process parameters.

[0014] To better implement the present invention, further, the method for obtaining the process specification material planning results in the two dimensions of space and time of the assembly scenario according to the analysis result of the digital model information includes: Analyze the digital model information to obtain the analysis result; According to the analysis results of the materials to be assembled, the connecting parts, and the mating materials of the connecting parts in the analysis result, obtain the connection relationship between the materials to be assembled and the connecting parts, and the mating relationship between the connecting parts and the mating materials of the connecting parts, so as to complete the process specification material planning of the assembly sequence in the assembly scenario space. According to the assembly timing of materials in different process specification templates in the assembly process flow, their roles in the assembly process flow, and the constraints for material distribution and outbound, the materials to be assembled, connectors, and connector-matched materials are classified into different process specification templates to complete the process specification material planning for the assembly sequence in the assembly scenario time.

[0015] To better implement the present invention, further, a method for establishing the process specification node planning results in two dimensions of space and time for the assembly scenario includes: Analyze the digital model information of the assembly scenario to obtain the analysis result; According to the design digital model structure form in the analysis result, divide the aircraft zero-standard parts materials to be assembled in the space dimension, and sort the division result in the space dimension according to the assembly simulation situation or the space assembly sequence of the design digital model structure; According to the assembly process flow, the requirements for work centralization, and the requirements for refined division of labor, sort the process specification templates involved in each group of materials in the time dimension; Split and merge the process specifications according to the workload requirements of a single process specification in the actual assembly process flow; According to the assembly sequence in the time dimension and space dimension of the assembly scenario, plan and sort all the process specifications, and plan the numbers and names of the process specification nodes according to the coding principle and naming principle.

[0016] To better implement the present invention, further, the assembly scenario includes skeleton structure assembly, system fixed-point assembly, skin and access panel assembly, system conduit and harness laying, and system conduit and harness installation.

[0017] To better implement the present invention, further, when the assembly scenario is skeleton structure assembly, classify the skeleton parts in the digital model information.

[0018] To better implement the present invention, further, when the assembly scenario is skeleton structure assembly, before establishing the process specification template corresponding to the skeleton structure assembly according to the assembly process flow and the standard process library, it also includes splitting the skeleton process specification operation steps to complete the generation and sorting of the skeleton process specification operations.

[0019] To better implement the present invention, further, it also includes steps of recording and tracing the data formed during the process planning and preparation, including: constructing part model metadata for each part model, defining the paradigm of the part model metadata, including data for identifying the identity of the part model and multiple sets corresponding to each BOM data of the part model, and creating a set data object for each set, where the set data object includes the data attribute information of the part model; storing the data formed during the process planning and preparation into the part model metadata; constructing a graph network of the part model metadata according to the logical relationship between the part model metadata; and using a graph traversal algorithm to trace the whole life cycle process data of the part model in the graph network.

[0020] In a second aspect, the present invention provides an aircraft component assembly detailed process design system, including: A digital model information acquisition module, which is used to acquire the digital model information of the assembly scenario; A process specification template generation module, which is used to establish a process specification template corresponding to the assembly scenario according to the assembly process flow and the standard process library; A planning module, which is used to analyze the digital model information to obtain an analysis result, and according to the analysis result, obtain the process specification node planning result and the process specification material planning result in the two dimensions of space and time of the assembly scenario; A process parameter library generation module, which is used to establish a process parameter library according to process knowledge and process rules; A process specification document preparation module, which is used to prepare a process specification document according to the process specification template, the process specification material planning result, the process specification node planning result and the process parameter library, and obtain a process specification document representing the detailed process of aircraft component assembly.

[0021] In a third aspect, the present invention provides a computer-readable storage medium, on which a computer program is stored, and characterized in that when the program is executed by a processor, it implements the aircraft component assembly detailed process design method described in any item of the first aspect.

[0022] Compared with the prior art, the present invention has the following advantages and beneficial effects: By establishing a process specification template corresponding to the assembly scenario based on the assembly process flow and the standard process library, it realizes that the process specification preparation is not combined with the assembly process flow, can accurately and automatically prepare the process specification, and improves the efficiency of process specification preparation; By carrying out process specification node planning and process specification material planning from the two dimensions of space and time of the assembly scenario, the accuracy of the process specification preparation result is further improved; By means of a process parameter library established based on process knowledge and process rules, automatic acquisition of process parameters is achieved, further improving the efficiency of process specification compilation and the accuracy of the process specification compilation results. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The present invention will be further described in conjunction with the following drawings and embodiments. All creative concepts of the present invention should be regarded as the disclosed content and the protection scope of the present invention.

[0024] Figure 1 It is a schematic flow chart of the implementation manner of a detailed process design method for aircraft component assembly in Embodiment 1 of the present invention.

[0025] Figure 2 It is a schematic relationship diagram of the implementation manner of a detailed process design method for aircraft component assembly in Embodiment 2 of the present invention.

[0026] Figure 3 It is a schematic diagram of the spatial assembly sequence and time assembly sequence of the implementation manner of a detailed process design method for aircraft component assembly in Embodiment 2 of the present invention.

[0027] Figure 4 It is a schematic relationship diagram between process parameters and process specification templates of the implementation manner of a detailed process design method for aircraft component assembly in Embodiment 2 of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0028] Embodiment 1 A detailed process design method for aircraft component assembly. First, obtain the digital model information of the assembly scenario; then, establish a process specification template corresponding to the assembly scenario according to the assembly process flow and the standard process library; analyze the digital model information to obtain an analysis result, and according to the analysis result, obtain the process specification node planning results and process specification material planning results in the two dimensions of space and time of the assembly scenario; establish a process parameter library according to process knowledge and process rules; finally, compile a process specification document according to the process specification template, the process specification material planning result, the process specification node planning result and the process parameter library to obtain a process specification document representing the detailed process of aircraft component assembly.

[0029] See Figure 1 , a specific implementation manner of this embodiment; In this implementation manner, the assembly scenario is set according to the actual situation of the aircraft, and may include assembly scenarios such as skeleton structure assembly, system fixed point assembly, skin and access panel assembly, system conduit and wire harness laying, and system conduit and wire harness installation; The assembly process flow refers to the assembly process flow in the detailed process design stage, including the part sequence of aircraft assembly, the assembly process flow between process specification nodes, and the process flow inside the process specification, which is determined by the assembly process plan and the production method; According to the assembly forms and assembly plans of each assembly scenario, a general assembly process flow can be formulated. For different production forms of each assembly scenario, directly adopting the general assembly process flow can improve the compilation efficiency of the process specification template; Specifically, for example, the general assembly process flow for connection is positioning - hole making - installation, involving 3 general assembly process specification templates; for the centralized production method of the skeleton structure assembly, the general assembly process flow (positioning - hole making - installation) can be directly adopted.

[0030] Furthermore, establish the internal process flow of the process specification template for the assembly scenario. According to the material types and attributes used in the assembly process flow, for the process specification template under each assembly scenario, further refine the assembly process flow under the specific scenario, and judge whether each process meets the occurrence conditions one by one to establish the internal process flow of the process specification template for the assembly scenario; Specifically, for example, the "cold extrusion" process specification template for the fine - division production method of the skeleton structure assembly, one template only contains cold extrusion operations. According to the assembly process plan and design requirements, 4 processes can be set: check the usage status of cold extrusion tools - cold extrusion operation - foreign object inspection - check the cold extrusion quality and the quality of foreign object removal; the process flow of the installation process specification template for connection is: gluing - riveting - pasting - screwing - inspection - installation - installation - foreign object removal - inspection - protection.

[0031] In this embodiment, the process specification node planning refers to, after the MBOM top - level structure design of the top - level process planning is completed, decomposing the work of the assembly scenario according to rules such as the assembly process flow, the form of the design digital model structure, and the assembly workload, to form a work list for on - site operation by workers.

[0032] In this embodiment, the process specification material planning refers to, after the MBOM top - level structure design of the top - level process planning is completed, distributing materials such as components, standard parts, and finished products in the design digital model to the workstations and process specifications under the aircraft component nodes according to the process division principle and the process separation surface division principle, completing the material consumption, and using it as the basis for compiling the supporting table of the process specification document; Process knowledge and process rules are sorted out from the assembly requirements, that is, the specific design and process requirements in the assembly process flow, to support the process parameter requirements under the specified process and the process parameter requirements of the whole process during the compilation of the process specification.

[0033] In summary, in this embodiment, based on the process specification nodes and material information in the planning results, combined with the process specification template and the process parameter library, the process specification document is compiled to complete the detailed process design of aircraft component assembly, realizing the material consumption, process specification node planning in the research and development stage of aircraft component assembly, as well as the process flow design and process parameter design in the process of process specification compilation, completing the compilation of the process specification document, and solving the technical problems of the existing aircraft assembly process design, such as the process specification compilation not being combined with the assembly process flow, low efficiency of process specification compilation, and low accuracy of process specification compilation.

[0034] Example 2 This embodiment is further optimized on the basis of the above-mentioned Embodiment 1. In this embodiment, referring to Table 1, the assembly scenarios include skeleton structure assembly, system fixed point assembly, skin and access panel assembly, system duct and wire harness laying, and system duct and wire harness installation.

[0035] Table 1 In an alternative implementation manner of this embodiment, the method for establishing a process specification template corresponding to the assembly scenario according to the assembly process flow and the standard process library includes: First, define the assembly process flow according to the assembly process plan; Then, adjust the assembly process flow according to the production method to establish the corresponding relationship between the assembly scenario and the process specification template; according to the assembly scenario and the standard process library, adjust the assembly process flow of each assembly scenario to establish the process specification execution process and the process specification process flow; Finally, establish a process specification template corresponding to the assembly scenario according to the corresponding relationship between the assembly scenario and the process specification template, the process specification execution process, and the process specification process flow.

[0036] Adopting this embodiment, by means of merging and splitting the general assembly process flow, the assembly process flow is designed respectively to adapt to the production forms such as the centralization of work, the refinement of division of labor, and the semi-centralization and semi-refinement in actual production and process state management, establishing the corresponding relationship between the assembly scenario and the process specification template to flexibly respond to different assembly scenarios and improve the adaptability of the process specification template and the assembly scenario; Specifically, for the production method of work centralization in the skeleton structure assembly, the positioning and hole making can also be combined into the form of pre-assembly (pre-assembly - installation), or the positioning, hole making, and installation can all be combined (centralized assembly). For the production method of refined division of labor in the skeleton structure assembly, the hole making and installation can be split separately according to the work rhythm. Finally, the overall assembly process flow after splitting is: positioning - cold extrusion initial hole - cold extrusion - hole making - countersinking - blind nut installation - bolt installation - inspection, which involves a total of 8 types of process specification templates.

[0037] In another alternative implementation of this embodiment, the method for establishing a process specification template corresponding to the assembly scenario according to the assembly process flow and the standard process library further includes: First, determine the information types included in the process specification, define the generation methods of the information of each component element of the process specification according to the information types, and determine the target component elements; Then, according to the assembly process flow of aircraft assembly, define the hierarchical relationship between the process specification template and the process specification operations to determine the structural form of the process specification operation set and define the corresponding expression methods according to the process specification template types of each type of process specification; define the classification methods of the assembly type, the process specification template type, and the process specification operation type, and establish the corresponding relationship between the process specification operation type and the process specification operation set to obtain the operation parameters of the process specification template; Finally, according to the digital model information of the assembly scenario, obtain the recognition conditions of the process specification operation set to determine the operation time sequence. According to the target component elements, the hierarchical relationship, and the corresponding relationship between the process specification operation type and the process specification operation set, combine the process specification operations that match the assembly scenario according to the operation time sequence to generate a process specification template corresponding to the assembly scenario.

[0038] Adopting this implementation mode, by analyzing the assembly type and the process specification operation type of aircraft assembly from the essential perspective of assembly, designing the appearance conditions of the operations in the assembly process flow, and sorting out the logical rules for the key conditions to affect the operation content, the operations associated by the rules are presented in the process specification template in a certain structural form and hierarchical relationship. In the subsequent process specification compilation process, when the digital model information included in the assembly scenario meets the appearance conditions of the operations, the operations that conform to the assembly scenario will appear in the process specification, and the operation content therein can be obtained by combining the process parameter library and the digital model information, realizing the rapid compilation of the aircraft assembly process specification and forming the final complete process specification document; through the design of the process specification template and the compilation of the process specification operation content, the compilation efficiency and quality of the process documents can be effectively improved, the manual workload and human errors can be reduced, providing strong technical support for the intelligentization and standardization of the aircraft assembly process, and promoting the deep integration of information technology and assembly process design technology.

[0039] Specifically, the types of information included in the process specification include operation instructions, processes, process timing, and operation instructions. As a process that appears relatively fixedly, processes have a timing relationship and embody multiple processes of the current assembly scenario process flow. Process timing provides the sequence of execution between multiple processes. Among them, processes also include process parameters such as the specific location, quantity, and assembly requirements for providing operations, lists of materials, tooling, materials, etc., and parameter information such as certification and standard operating procedures; according to the timing of information generation in the process specification, some processes that cannot be known in advance during the process specification compilation process need to be gradually improved into the quality information records in the process specification content according to the actual situation during production, as well as design change information starting from the changes and optimizations in the later stage of design, which are not considered as the content of the process specification template. However, some information obtained through logical rule reasoning and process parameter acquisition based on the actual situation of the assembly digital model, as well as some fixed statements, can be incorporated into the process specification template.

[0040] The assembly process flow of aircraft assembly can be divided into multiple levels, including assembly scenarios, process specification templates, process specification process sets, and processes. Each level contains rich process information and execution details; in this multi-level structure, each assembly scenario corresponds to multiple process specification templates, each process specification template contains multiple process specification process sets, and each process specification process set may contain multiple processes with the same name; To solve the problem of identifying processes with the same name, this embodiment also introduces the concept of "process label". By assigning a unique label to each process, accurate differentiation between processes with the same name is achieved. When it is necessary to locate a specific process, first clarify the current assembly scenario, which is the starting point for finding the process; then, in this assembly scenario, select the process specification template that matches the current assembly task. In the selected process specification template, find the process specification process set related to the assembly task. In the process specification process set, perform a preliminary location according to the name of the process; finally, through the unique process label, accurately identify the target process from the possible processes with the same name; In this embodiment, the structural form of the process specification operation set is such that each operation in the process specification operation set will be activated simultaneously when encountering specific material characteristics or assembly process plans. This mechanism ensures that in an assembly scenario that meets specific conditions, the relevant operations can be automatically and synchronously executed, improving the efficiency and consistency of the assembly process flow. Of course, for those operations with extremely strong generality that need to be executed under multiple conditions, they can also be divided into multiple process specification operation sets at the same time. This can ensure that these key operations can be triggered regardless of the assembly scenario, avoiding process defects that may be caused by omissions in condition judgment. In addition, for operations that are fixed and need to appear in a specific assembly scenario without being affected by any conditions, the present invention sets up a process specification operation set that appears by default. This design ensures that in any case, these operations can be automatically executed and can flexibly meet the requirements of different assembly scenarios, ensuring the accurate triggering and efficient execution of the operations.

[0041] In this embodiment, referring to Table 2, the assembly types mainly include several types such as connector type, contact type, relative motion type, plug, etc. Each type undertakes different functions in aircraft assembly and has specific material and assembly form characteristics. Analyze the role of each assembly type in aircraft assembly, as well as the material and assembly form characteristics in the assembly process flow, and based on the assembly characteristics, preliminarily identify the types of process specification templates and operation types required to achieve this assembly type.

[0042] Table 2 By analyzing one by one the influence of the possible material characteristics and assembly process plans involved in the assembly process flow on the operations and the internal parameter information of the operations, generate the key conditions for the appearance of the operations. The operation types and the process specification operation sets establish a corresponding relationship through this key condition.

[0043] In this embodiment, by taking the key conditions for the appearance of the operations as the process specification operation sets of the assembly process specification template, sort out the recognition conditions of the process specification operation sets into three forms of rules: fixed statements, logic diagrams, and process parameter libraries, to determine the operation timing. Among them, the fixed statement rule is a simple and intuitive expression method used to describe the necessary conditions for the appearance of the operations. The logic diagram rule shows the logical relationship of the operation appearance conditions in the form of a flow chart or decision tree and is used to handle the operation selection under complex conditions. The process parameter library rule means storing the operation parameter information in a database and automatically obtaining the corresponding process parameters according to the key conditions for the appearance of the operations through a query and matching mechanism. This rule is applicable to the standardized management and rapid retrieval of operation parameter information.

[0044] By adopting this embodiment, by refining the element information included in the process specification template and its generation method, the information automatically generated based on the assembly digital model information, logical reasoning rules, process parameters, etc., as well as some fixed description statements, are preset in the process specification template; Define the hierarchical relationship between the process specification template and the process specification operations, support the decomposition from the template to the operations, and the combination from the operations to the template. By establishing this two-way hierarchical relationship, the flexible application and efficient management of the process specification template can be realized, and at the same time, it is also convenient for process designers to customize and adjust the template according to actual needs; Design the appearance conditions of the operations. According to the association relationship between the operation types and the set of process specification operations, the operations are combined to form the corresponding process specification template. In this way, it can be realized to design a general template, obtain the digital model information included in the assembly scenario, and adaptively match the operations that meet the needs, without designing a template for each situation; By defining the classification methods of the assembly types, process specification template types, and operation types, and at the same time establishing the corresponding relationship between the operation types and the set of process specification operations, the establishment of this classification and corresponding relationship supports the acquisition of the process specification template operation matching parameters, provides clear guidance for the subsequent template design, and at the same time improves the generality and adaptability of the template; Based on the process specification template, combined with the process parameter library and the digital model information, the compilation of the aircraft assembly process specification is realized.

[0045] In another alternative embodiment of this example, the method for establishing a process parameter library according to process knowledge and process rules includes: First, define the assembly requirements involved in the assembly process flow, and generate process knowledge and process rules according to the assembly requirements; Then, construct the data association relationship between the process parameter libraries to obtain process parameters in the assembly process flow; generate the process parameter library according to the data association relationship, process knowledge, and process rules; Finally, according to the characteristics of the assembly information in the process of compiling the process specification, define the calculation logic rules for the corresponding process parameter library, construct a parameter acquisition mode for uniformly pushing data for the process parameters under the specified process, and construct an active retrieval data parameter acquisition mode for the process parameter library that is common to the entire process.

[0046] Specifically, the data format of the process parameter library is a data format that is organized into multi-dimensional input and output data according to the data retrieval scheme, data source and logic rules of the process parameters used in the component assembly process flow, CLASS1{IN1;OUT1}; CLASS2{IN1, IN2, …INn; OUT1}; CLASS3{IN1;OUT1, OUT2, OUT3, …OUTn}; CLASS4{IN1, IN2, IN3, …INn; OUT1, OUT2, OUT3, …OUTn}, among which, CLASS1 supports unified program recognition of initial data, CLASS2 supports logical reasoning of a unique result after multiple conditional input, CLASS3 supports multi-dimensional definition after data input, and outputs results of different dimensions, which can be applied in different scenarios, and CLASS4 supports logical reasoning of results of different dimensions after multiple conditional input, which can be applied in different scenarios; The process parameters that change with the changes in the process specification template or process step, and the calculation logic rules, are defined as the process parameters under the specified process. Different calculation logic rules and different process parameter libraries need to be designed for different process specification templates and even different process parameters. For example, in a process of a template, multiple CLASS-type data retrieval schemes, data sources and logic rules are used to complete the output of complete information. The process parameters whose calculation logic rules are the same regardless of the position of the process specification template or the process step are defined as process parameters common to the whole process. In order to avoid repeated retrieval of process parameters during process specification compilation, a set of parameter libraries are uniformly established. According to the process specification templates and their corresponding processes and process specification planning materials, as well as unified calculation logic rules, the process parameters common to the whole process are uniformly pushed to the process specification templates and put into the process parameter position corresponding to the process specification template. Each process parameter corresponds to only one data retrieval scheme, data source, and logic rule. For example, a certain CLASS type can be applied to the calculation of a common process parameter of all process specification templates.

[0047] In this embodiment, according to the analysis result of the digital model information, the method for obtaining the process specification material planning result corresponding to the assembly scene includes: Analyze the digital-analog information to obtain the analysis result; According to the analysis results of the materials to be assembled, the connectors and the materials supporting the connectors in the analysis results, the connection relationship between the materials to be assembled and the connectors, as well as the matching relationship between the connectors and the materials supporting the connectors are obtained to complete the process specification material planning of the spatial assembly sequence of the assembly scene; According to the assembly timing of materials in different process specification templates in the assembly process flow, their roles in the assembly process flow, and the constraints on material distribution and outbound, the materials to be assembled, connectors, and connector matching materials are divided into different process specification templates to complete the process specification material planning for the assembly sequence in the assembly scenario time.

[0048] Specifically, the materials in the spatial dimension of the assembly scenario include three categories: materials to be assembled, connectors, and connector matching materials. The materials to be assembled are the above-mentioned "group of zero-standard parts that can be assembled independently at one time". The connectors are in the forms of rivets, blind rivets, bolts, screws, etc. The connector matching materials are in the forms of nuts, washers, split pins, etc., and are generally used simultaneously with the connectors to achieve the connection and fixation of the materials to be assembled. See Figure 2 , through the analysis of the digital model relationship, obtain the connection relationship between the materials to be assembled and the connectors, and the relationship between the connectors and the connector matching materials. In the connection relationship library, search for the connection relationship between the materials to be assembled and the connectors. When the materials to be assembled that have connection relationships with the same connector simultaneously appear in the "group of materials that can be assembled independently at one time", it means that this connector is the connector inside this "group of materials that can be assembled independently at one time", and the corresponding connector matching materials of this connector are also the connector matching materials inside this "group of materials that can be assembled independently at one time". The division of materials in the time dimension of the assembly scenario is based on the assembly timing of materials in different process specification templates in the assembly process flow, their roles in the assembly process flow, and the constraints on material distribution and outbound. The components, standard parts to be assembled, as well as the connectors and connector matching materials related to the materials to be assembled are divided into different process specification templates, that is, the materials for each time assembly sequence in the assembly scenario are determined. For example, in the initial stage of assembly, it is necessary to position and pre-assemble all the materials to be assembled, so all the materials to be assembled are assigned to the positioning template. During the assembly hole-making process, it is necessary to perform the assembly hole-making work on the materials to be assembled that have been positioned. However, since the materials to be assembled have been assigned to the positioning template, there is no need to assign materials to the hole-making template. In the assembly connection process, it is necessary to pass the connectors through the pre-drilled holes in the materials to be assembled and assist in using the connector matching materials to complete the fixed connection of the materials to be assembled.

[0049] See Figure 3 , in this embodiment, the method for establishing the process specification node planning result corresponding to the assembly scenario according to the spatial assembly sequence and time assembly sequence corresponding to the assembly scenario includes: Analyze the digital model information of the assembly scenario to obtain the analysis result. According to the design digital model structure form in the parsing result, the aircraft zero-standard part materials to be assembled are divided by spatial dimension, and the division result is sorted by spatial dimension according to the assembly simulation situation or the spatial assembly sequence of the design digital model structure; According to the assembly process flow, the requirements of work centralization, and the requirements of refined division of labor, the process specification templates involved in each group of materials are sorted by time dimension; According to the workload requirements of a single process specification in the actual assembly process flow, the process specifications are split and merged; According to the assembly sequence in the time dimension and spatial dimension of the assembly scenario, all process specifications are planned and sorted, and the numbers and names of the process specification nodes are planned according to the coding principle and naming principle.

[0050] Specifically, for the process specification node planning from the spatial dimension of the assembly scenario, according to the actual assembly process flow, the spatial assembly sequence of the assembly scenario is planned, and the aircraft zero-standard part materials to be assembled are divided into the granularity form of "a group of zero-standard part materials that can be assembled independently at one time"; For the process specification node planning from the time dimension of the assembly scenario, it means that according to the requirements of the assembly production rhythm, the time assembly sequence of the assembly scenario is planned, and the "a group of zero-standard part materials that can be assembled independently at one time" is divided into the granularity form of process specification templates with multiple different functions from the process flow of material storage location to hole making and connection.

[0051] Take Figure 3 as an example. An assembly body to be assembled contains 32 zero-components. According to the assembly process simulation result and the structure form of the assembly body, the entire assembly body structure is split into multiple parts. According to the requirements of the assembly production rhythm, multiple serial or parallel steps are planned correspondingly to complete the assembly process of the entire assembly body. If it is split into 6 parts, 6 steps need to be planned. Each step completes the assembly of one part, and 6 "a group of zero-standard part materials that can be assembled independently at one time" are planned correspondingly to complete the material planning of the spatial dimension of the process specification node; then according to the series-parallel sequence of each step, the sequence planning of the spatial dimension of the process specification node is completed.

[0052] The "a group of zero-standard part materials that can be assembled independently at one time" in each step are distributed to multiple process specification templates with functions such as positioning, cold extrusion, hole making, connection, and inspection according to the assembly process flow and process requirements to complete the material planning of the time dimension of the process specification node; then according to the process flow sequence of links such as positioning, cold extrusion, hole making, connection, and inspection, the sequence planning of the time dimension of the process specification node is completed.

[0053] In an alternative implementation of this embodiment, based on the above process specification template, process specification node planning result, process specification material planning result, and process parameter library, the accurate matching of the operation content in the process specification template is completed to realize the compilation of the process specification document, and finally the detailed process design of the aircraft component assembly is completed; Specifically, referring to Figure 4 , according to the assembly process plan and production method, determine the assembly process flow, and combine it with the standard operation library to form an assembly process specification template; according to the digital model analysis result, complete the process specification node and material planning in the two dimensions of space and time for component assembly; sort out the design and process requirements in the assembly process flow into process knowledge and process rules, and build a process parameter library based on knowledge and rules to support the requirements of process parameters under the specified process and full-process process parameters in the process of compiling the process specification; Each process parameter retrieves the relevant process parameter library and obtains the result through logical matching and reasoning judgment. In the process of compiling the process specification, the content of the process specification is decomposed into each process specification template and each process parameter, and it is judged one by one whether each process parameter is a process parameter under the specified process or a full-process general process parameter. After calculating the process parameters under the specified process one by one, then uniformly calculate and push the full-process general process parameters applicable to each template and each operation, and put the calculation results of the obtained process parameters into the corresponding operation parameter positions to form multiple process specification documents that can completely express the assembly information in the entire component assembly process flow.

[0054] Embodiment 3 This embodiment is further optimized on the basis of Embodiment 2. When compiling the aircraft component assembly connection process specification document, the method for establishing a process parameter library according to process knowledge and process rules includes: Construct the multi-dimensional input / output data form of the assembly connection process parameter library according to the data retrieval scheme, data source, and logical rules of the process parameters used in the aircraft component assembly process flow; Generate assembly connection process knowledge and assembly connection process rules according to the assembly connection process experience and assembly connection process requirements of the aircraft component assembly connection process; Associate the data tables in the assembly connection process parameter library according to the key fields in the assembly connection process parameter library to construct the data association relationship between the assembly connection process parameter libraries; Establish a process parameter library including an assembly connection operation process parameter library and an assembly connection general process parameter library according to the data association relationship, data form, assembly connection process knowledge, and assembly connection process rules between the assembly connection process parameter libraries; Construct a parameter acquisition mode for uniformly pushing data for the process parameter library of the assembly connection process, and a parameter acquisition mode for actively retrieving data for the general process parameter library of the assembly connection; Adopting this embodiment can further improve the efficiency and accuracy of compiling the process specification document for aircraft component assembly connection.

[0055] In an alternative implementation manner of this embodiment, according to the process experience and process requirements of the aircraft component assembly connection process, induction and reasoning are carried out to form process knowledge and process rules. In order to reduce data redundancy and increase the coherence between data, 9 connection process parameter libraries are constructed, including 6 process parameter libraries and 3 general process parameter libraries. The 6 process parameter libraries are respectively the material library, the standard part library, the recycled standard part type library, the constant force tool library, the connecting part hole diameter library, and the bonding pallet quality inspection library; the 3 general process parameter libraries are respectively the standard operation procedure library, the certification information library, and the inspection type library.

[0056] For the active retrieval data mode in this embodiment, the process parameters of the process are related to the process specification template and the assembly process flow where they are located. For different assembly process flows, the acquisition logic rules of the process parameters are different. According to the process specification template and its corresponding process, through the replacement symbols in the template, the information of the process parameter library is actively retrieved for each process, and through the logical matching and reasoning judgment between the process parameter libraries, the obtained parameter results are placed in the replacement symbol position of the process parameters. For example: Material library {Input: Standard part drawing number; Output: Connecting part sandwich parts, sandwich part material grade, number of connecting parts, hole-making area type}; Standard part library {Input: Standard part drawing number; Output: Drawing number feature, drawing number diameter feature, strength characteristic}; Recycled standard part type library {Input: Drawing number feature; Output: Recycled content}; Connecting part hole diameter library {Input: Drawing number diameter feature; Output: Drawing number diameter code}; Constant force tool library {Input: Standard part drawing number, strength characteristic, drawing number diameter code; Output: Constant force tool drawing number, constant force requirement}; Bonding pallet quality inspection library {Input: Drawing number diameter feature, drawing number diameter code; Output: Inspection requirement}.

[0057] For the unified push data mode in this embodiment, in order to avoid repeated retrieval of process parameters during the compilation of the process specification, a set of parameter libraries and matching logic rules are established uniformly. According to the process specification template and its corresponding process, the process parameter library uniformly pushes the general process parameter information to the process and places it in the corresponding parameter position of the process. For example: Standard operating procedure library {input: process procedure template name, process name, drawing number feature...; output: standard operating procedure number, standard operating procedure name}; Certification information database {input: process specification template name, process name, drawing number characteristics...; output: certification code}; Design and inspection type library {input: process specification template name, process name, drawing number characteristics...; output: design and inspection type}.

[0058] For the above two parameter acquisition modes, the association relationship between the component assembly hole making process parameters and the eight hole making process parameter libraries is established according to the structural form of the hole making process parameter library and the designed input / output function mode.

[0059] In this embodiment, according to the assembly process flow and the standard process library, the method for establishing a process specification template corresponding to the assembly scenario includes: Define the aircraft component assembly factors that affect the aircraft component assembly connection assembly process; Establish the association between aircraft component assembly elements and aircraft component assembly connection assembly process flow and construct the aircraft component assembly connection assembly process flow; According to the assembly process flow and standard process library of aircraft parts assembly, a process procedure template corresponding to the assembly scenario is established.

[0060] Specifically, the seven component assembly elements, including whether the connector is a double-line bolt, whether the connector is a rivet, whether the connector is a bonding tray nut / screw, whether the connector is a bolt / screw, whether the connector is a fixed force type high lock, whether the connector is a nut break cap type high lock, and whether the connector is a pull-out nail, are analyzed one by one to see how they affect the component assembly connection assembly process flow, and the assembly process flow is constructed. The detailed process flow is as follows: Establish the relationship between "whether the connection part is a double-thread bolt" and the assembly process of the component assembly connection, and design the connection assembly process of the connection part as a double-thread bolt; for the connection of double-thread bolt standard parts, after completing the hole making work such as hole countersinking, according to the designed digital model, first install the bushing on the countersunk part, then rivet the support plate nut for the double-thread bolt on the other laminated parts, and finally install and fix all the laminated parts with double-thread bolts to complete all the work of double-thread bolt connection; Establish the relationship between "whether the connecting part is a rivet" and the assembly process flow of the component assembly, and design the connection assembly process flow when the connecting part is a rivet; for the connection of rivets, after completing the hole making work such as hole countersinking, all the laminated parts are riveted and fixed by rivets according to the designed digital model, completing all the work of rivet connection; Establish the relationship between "whether the connection part is a bonding tray nut / screw" and the assembly process flow of the component assembly connection, and design the connection assembly process flow of the connection part being the bonding tray nut / screw; for the connection of the bonding tray nut / screw, after completing the hole making work such as hole countersinking, the connection position of the connection part and the skeleton is polished, cleaned, and pasted according to the designed digital model. After the pasting is completed, the excess polishing area before pasting is subjected to anti-corrosion protection, and the connection work of the bonding tray nut / screw is completed; Establish the relationship between "whether the connecting part is a bolt / screw" and the assembly process flow of the component assembly, and design the connection assembly process flow when the connecting part is a bolt / screw; for the connection of bolts / screws, after completing the hole making work such as hole countersinking, all the laminated parts are screwed and fixed by bolts or screws according to the designed digital model, completing all the work of bolt / screw connection; Establish the relationship between "whether the connector is a fixed-force high-lock" and the assembly process of the component assembly connection, and design the connection assembly process of the connector as a fixed-force high-lock; for the fixed-force high-lock connection, after completing the hole making work such as hole countersinking, first check the fixed-force wrench and other tools used for installation. After the inspection is qualified, all the laminated parts are installed and fixed by high-lock bolts and high-lock nuts according to the designed digital model, completing all the work of the fixed-force high-lock connection; Establish the relationship between "whether the connection part is a high-lock type with a nut and a broken cap" and the assembly process flow of the component assembly connection, and design the connection assembly process flow of the connection part with a high-lock type with a nut and a broken cap; for the connection of the high-lock type with a nut and a broken cap, after completing the hole making work such as hole countersinking, all the laminated parts are installed and fixed with high-lock bolts and high-lock nuts according to the designed digital model. After the installation is completed, the head of the high-lock nut is separated and broken from the main part of the nut. After completing all the work of the fixed-force high-lock connection, the broken cap of the high-lock nut needs to be recovered and inspected; Establish the correlation between "whether the connection is a pull-out nail" and the component assembly connection assembly process flow, and design the connection assembly process flow when the connection is a pull-out nail; the pull-out nail connection, like the high-lock connection such as the nut and broken cap, also needs to be recovered and inspected after the installation is completed.

[0061] Combining all the above connection processes, the initial cleaning, gluing, and the final excess material inspection and inspection processes are set as public default processes, and finally a complete component assembly connection process procedure template is formed to construct a complete component assembly connection assembly process flow.

[0062] In this embodiment, after establishing the process specification template corresponding to the assembly scenario, the judgment logic affecting the assembly elements of the aircraft component assembly connection assembly process is also constructed according to the assembly connection process parameter library; Specifically, according to the assembly design requirements and process requirements of aircraft components, seven component assembly elements that affect the entire component assembly connection process are defined, including whether the connecting piece is a double-threaded bolt, whether the connecting piece is a rivet, whether the connecting piece is an adhesive backing nut / screw, whether the connecting piece is a bolt / screw, whether the connecting piece is a constant force type Hi-Lok, whether the connecting piece is a nut cut-off type Hi-Lok, and whether the connecting piece is a blind rivet. The key conditions affecting the process specification template processes can be logically judged through the process parameter library. Most of the key conditions are the material types of the connecting pieces, which can be obtained through the material library and the standard parts library. In addition, for the special types of Hi-Loks, the two key conditions of the constant force type Hi-Lok and the nut cut-off type Hi-Lok can be distinguished through the recycled standard parts type library.

[0063] In this embodiment, a method for obtaining a process specification document representing the detailed process of aircraft component assembly according to the process specification template, the process specification material planning result, the process specification node planning result, and the process parameter library includes: Defining the parameter types of the assembly connection process parameters; Based on the materials in the material library involved in the actual aircraft component assembly connection process, establishing the parameter association relationship between the assembly connection process parameters and constructing the acquisition logic of the assembly connection process parameters; According to the acquisition logic, obtaining the assembly connection process parameters of the specified parameter type from the process parameter library; Obtaining the aircraft component assembly connection process specification document according to the process specification template, the process specification material planning result, the process specification node planning result, and the assembly connection process parameters.

[0064] Specifically, first, define the types of component assembly connection process parameters. The aircraft component assembly connection process uses a large number of process parameters, which will involve different types of connecting pieces, different assembly requirements, corresponding to different standard part connection insurance requirements, recycling inspection requirements, installation constant force requirements, constant force tools, and adhesive backing / screw torque inspection requirements and other parameters; Secondly, based on the materials in the material library involved in the actual aircraft component assembly and connection process flow, establish the correlation relationships between process parameters, and construct the acquisition logic of component assembly and connection process parameters. For example, an instance of obtaining the process parameters of component assembly and connection operations. According to the data correlation relationships between process parameter libraries, classify the correlation relationships between each process parameter library to form one-to-one, one-to-many, and many-to-one correspondence forms between parameter libraries, as well as single-parameter matching and multi-parameter matching relationships between parameters. Through the parameter correlation relationships between databases, form inference rules. According to the materials in the material library involved in the actual aircraft component assembly and connection process flow, retrieve the above 6 relational process parameter libraries according to the rules to obtain the connection operation process parameters. According to the process specification template name, operation name, standard operation procedure library, certification information library, and inspection type library, push general process parameters in a unified operation. Finally, based on the designed component assembly and connection process specification template, put the actively retrieved or uniformly pushed component assembly and connection process parameters into the operation parameters and operation attribute information in the form required by the process specification template. Combining the process specification material planning result and process specification node planning result obtained according to the space and time sequence planning, the compilation of the aircraft assembly and connection process specification can be completed.

[0065] In summary, adopting this embodiment, according to the assembly and connection process flow, process experience, and process requirements of the assembly, complete the design of the component assembly and connection process specification template and the component assembly and connection process parameter library, determine the assembly and connection process parameters of the actual aircraft component assembly and connection process flow, realize that after obtaining the aircraft component assembly digital model information in the application software, quickly call in the corresponding connection insurance requirements, recovery inspection requirements, installation setting force requirements, setting force tools, and bonding bracket / screw torque inspection requirements for different standard parts, as well as general process parameters, and complete the compilation of the aircraft assembly and connection process specification. Through systematic and intelligent means, the efficiency and quality of component assembly and connection process design are effectively improved.

[0066] Example 4: This embodiment further optimizes on the basis of the above Example 2 or 3. In this embodiment, when the assembly scenario is the skeleton structure assembly, classify the skeleton parts in the digital model information.

[0067] Furthermore, when the assembly scenario is the skeleton structure assembly, the method for classifying the skeleton parts in the digital model information includes: Step S101, construct a set of skeleton parts. Specifically, construct a skeleton part rule library, denoted as rule = (frame, beam...). Based on the MBD digital model data, identify the skeleton parts to form a set of skeleton parts , ; Step S102: Set the assembly threshold and distance threshold for the skeleton parts. Specifically, denote the assembly threshold for the skeleton parts as smx , that is, the number of parts assembled each time cannot exceed smx . Denote the distance threshold for the skeleton parts as kmx , that is, the distance between parts cannot exceed kmx ; Step S103: Based on the MBD digital model, analyze the digital model coordinates and calculate the centroid coordinates of each skeleton part. Specifically, according to parts in Step S101, extract the coordinates of each skeleton part and denote them as ; Step S104: Randomly select k centroid points of the skeleton parts to form k clusters. Specifically, randomly select k centroid points of the skeleton to form k clusters; Step S105: Calculate the distance from the i th skeleton part to the cluster, , and obtain the minimum distance dmin i . If , , put this skeleton part into the subset of cluster parts cparts i . Among them, s i is the centroid coordinate of the i th skeleton part, k i is the centroid coordinate of the i th cluster, , j is the number of skeleton parts in the subset of cluster parts cparts i . Repeat the above steps to form k subsets of cluster parts; Step S106: The centroid coordinates of each subset of cluster parts. The centroid coordinates of the subset of cluster parts are expressed as ; Step S107: Calculate the silhouette coefficient. Specifically, calculate the silhouette coefficient according to . Among them, a(i) is cparts i in the i th skeleton part and the average distance between all other skeleton parts in the subset of cluster parts where it is located, that is, the intra-cluster distance; b(i) is the average distance between the i th skeleton part and all skeleton parts in the nearest subset of cluster parts; If , obtain the i th subset of cluster parts cparts i Among them, the skeleton part with the largest distance is obtained. Using the Euclidean distance, calculate the minimum distance from the part with the largest distance to other subsets of cluster parts, and assign the part with the largest distance to the cluster corresponding to the minimum distance; Step S108: Recalculate Step S106 and Step S107, recalculate the centroid coordinates of the subset of cluster parts after reallocation, and calculate the silhouette coefficient until the silhouette coefficient is greater than the preset value to complete the classification of skeleton parts.

[0068] Adopting this embodiment, by restricting the number of part assemblies, the assembly efficiency is effectively controlled; by setting the threshold between parts, the assembly relationship between parts is ensured; by using the silhouette coefficient, the irrationality of clustering is avoided; the technical problem of unclear and inconsistent grouping of skeleton parts is solved, effectively improving the efficiency of aircraft process design.

[0069] Embodiment 5 This embodiment is further optimized on the basis of the above Embodiments 2 to 4. In this embodiment, when the assembly scenario is the assembly of the skeleton structure, after obtaining the digital model information of the skeleton structure assembly, first, according to the part type, the assembly process flow, and the standard process library, establish a process specification template corresponding to the skeleton structure assembly; Then, when parsing the digital model information, also perform part type recognition, interference recognition, and connector recognition on the target skeleton part. The parsing result also includes the part type recognition result, the interference recognition result, and the connector recognition result, so as to match the target skeleton part process specification template for the target skeleton part according to the part type recognition result, remove the interfering skeleton parts from the set of assembly skeleton parts composed of the target skeleton parts according to the interference recognition result, and obtain the set of skeleton connectors corresponding to the target skeleton part according to the connector recognition result; Finally, according to the target skeleton part process specification template, the set of assembly skeleton parts, the set of skeleton connectors, the process specification material planning result, the process specification node planning result, and the process parameter library, compile the process specification document to obtain the process specification document representing the detailed process of aircraft skeleton assembly.

[0070] Furthermore, after obtaining the digital model information of the skeleton structure assembly, first, extract the part point coordinates of each part of the aircraft, construct an aircraft structure part type library, and establish a process specification template corresponding to the skeleton structure assembly according to the part type, the assembly process flow, and the standard process library in the aircraft structure part type library; determine the target skeleton part, extract the initial digital model coordinates of the target skeleton part according to the digital model information, obtain the set of assembly skeleton parts, and set the direction vector and moving step length for the assembly of the target skeleton part; Then, traverse the set of assembled skeleton parts, identify the part type of the target skeleton part according to the part types in the aircraft structural part type library, and obtain the part type recognition result; according to the coordinates, direction vector and moving step of the target skeleton part, perform assembly path verification, obtain the interference recognition result, and remove the skeleton parts that cause interference from the target skeleton parts; according to the set of assembled skeleton parts, identify the connecting parts connected by the skeleton parts, obtain the connecting part recognition result, and obtain the skeleton connecting part set according to the connecting part recognition result; according to the part type recognition result, match the corresponding process specification template for the target skeleton part set. Finally, according to the set of assembled skeleton parts, the skeleton connecting part set and the target skeleton part process specification template, construct the prompt words of the large language model, and perform the preparation of the process specification document according to the process specification material planning result, the process specification node planning result, the process parameter library and the prompt words of the large language model, so as to obtain the process specification document representing the detailed process of aircraft skeleton assembly.

[0071] Specifically, in an optional implementation manner, the preparation of the aircraft skeleton assembly process specification document includes the following steps: Step S201: Extract the part point coordinates of each part of the aircraft, construct the aircraft structural part type library, and establish the corresponding process specification template for the skeleton structure assembly according to the part types, assembly process flow and standard operation library in the aircraft structural part type library. Specifically, according to the MBD digital model information, extract each part of the aircraft and construct the aircraft structural part type library according to the part types, and the point cloud coordinates of the parts , where , and the radius coordinates , where , construct the process specification template according to the part types, assembly process flow and standard operation library, denoted as , , where, seq represents the operation corresponding to the template, denoted as , , pra represents the parameter name corresponding to the operation, , , con represents the parameter content corresponding to the parameter name; Step S202: Determine the target skeleton part, extract the initial digital model coordinates of the target skeleton part according to the digital model information, obtain the set of assembled skeleton parts, and set the direction vector and moving step for the assembly of the target skeleton part. Specifically, clarify the skeleton part to be assembled, denoted as , , obtain the assembly relationship between the parts, denoted as , where ri Indicates the connection relationship between the m th part and the n th part, extracts the initial coordinates of the digital model , , where p i Indicates the starting coordinates of the i th skeleton, obtains the normal vector coordinates of the part , , translates the part p i coordinates in the direction of the normal vector v i by step to , where is a randomly generated step size, and the part direction vector is ; Step S203, traverses the set of assembled skeleton parts, identifies the part type of the target skeleton part according to the part types in the aircraft structure part type library, obtains the part type recognition result, traverses the set of assembled skeleton parts, identifies the part type of the target skeleton part according to the part types in the aircraft structure part type library, obtains the part type recognition result. Specifically, traverse the set of skeleton parts ske , uses image recognition technology to identify and classify the parts, denoted as f i , , where f i Indicates the category of the i th part; Image recognition specifically includes data collection, annotates the historical design digital model part images, part his = {( part his1 , triangular part) …… ( part hisi , square part)}, annotates each part (triangular part, square part); preprocessing, converts the historical image into a grayscale image, scales it to a 64x64 pixel matrix, and normalizes the matrix; training, selects a convolutional neural network (CNN), uses the annotated dataset to train the model, and obtains the model f model ; for the skeleton part ske , uses the trained model f model , obtains the classification result f i , ; Step S204, according to the starting coordinates of the skeleton part pi Step by step Towards p j Move and calculate the distance between the i nth part and all parts If , it means there is interference and the assembly is unreasonable. Remove the part from the set of skeleton parts and continue to execute step S203, where rs i and rs j represent the radii of the i nth part and the j mth part respectively; Step S205: According to , identify the connecting parts connected to the skeleton parts to form a set of skeleton connecting parts ; Step S206: According to the part type recognition result of step S203 f i , match the process specification template m i ; Step S207: According to the set of assembled skeleton parts, the set of skeleton connecting parts and the target skeleton part process specification template, construct the prompt words of the large language model. According to the process specification material planning result, the process specification node planning result, the process parameter library and the prompt words of the large language model, compile the process specification document to obtain the process specification document representing the detailed process of aircraft skeleton assembly; Among them, the format of the positioning part prompt words can adopt the form of fixed statement + process specification template operation content + the set of parts to be assembled and connection relationships, such as: "Please replace the content of

part

connecting part

part

[0072] By adopting this embodiment, by constructing the aircraft structure part type library, the digital model recognition time is reduced and the digital model recognition efficiency is improved; by the interference method therein, the part cluster division time is reduced and the process design difficulty is alleviated; by constructing the prompt words of the large language model, the process specification compilation time is reduced and the process specification compilation efficiency is improved.

[0073] Embodiment 6 This embodiment is further optimized on the basis of the above Embodiment 2, Embodiment 3, Embodiment 4 or Embodiment 5. In this embodiment, when the assembly scenario is skeleton structure assembly, before establishing the process specification template corresponding to the assembly scenario according to the assembly process flow and the standard operation library, it further includes: splitting the skeleton process specification operation steps to complete the generation and sorting of the skeleton process specification operations.

[0074] Furthermore, a method for splitting the process steps of the skeleton process specification to complete the generation and sorting of the skeleton process specification steps includes: First, according to the digital model information of the skeleton structure assembly, determine the parts to be assembled and construct a set of stacked parts, mark the order of the stacks and the order of the parts to be assembled in the stacks; then, parse the digital model information, obtain the digital model connection relationship between the parts to be assembled, and according to the digital model connection relationship, obtain the in-stack connection relationship between the parts in the stack and the inter-stack connection relationship between the parts between the stacks; next, generate rough process steps according to the in-stack connection relationship and the inter-stack connection relationship, and split the rough process steps into fine process steps according to the set of connector types; finally, construct a set of sorting fields according to the set of connector types, and sort the rough process steps and the fine process steps according to the set of sorting fields to obtain the set of skeleton process specification steps.

[0075] Specifically, it includes the following steps: Step S401: Select the parts to be assembled by the aircraft to form a set of stacked parts, denoted as d ; Step S402: Parse the MBD digital model parts and part coordinates, the part is denoted as , ; the coordinate is denoted as , ; Mark the order of the k th stack as , , represents the average value of the coordinates of the parts, is the minimum value among the average values of the coordinates of all parts in the stack; Step S403: Calculate the order of the parts in the stack according to the coordinates in Step S402, denoted as , , where dsort i represents the order of the i rd part in the stack; Step S404: Parse the MBD digital model and construct a set of part relationships, denoted as , where r n is the relationship of the nth part; Step S405: Based on Step S404, identify the relationships between the parts inside the material stack, that is, calculate the part i and part j relationships, and construct a set of relationships between parts, that is, an in-stack connector set, denoted as , , ran Indicates the connection relationship of the nth part, including the part and the connecting piece; the order of calculating the connecting pieces inside the heap is denoted as , where , , ras i Indicates the i order of the connecting piece, that is, the order of the i connecting piece corresponds to the order of the i part; Step S406. Based on Step S404, identify the relationship between the parts of the material stack, that is, calculate part k and part l relationship, construct the relationship set between the parts of the material stack, that is, the connecting piece set between the stacks, denoted as , , rb n Indicates the connection relationship of the nth part, including the part and the connecting piece; the order of calculating the connecting pieces between the stacks is denoted as , where , , rbs i Indicates the i order of the connecting piece; Step S407. According to the connecting piece set ra and the connecting piece order ras , group the connecting piece set ra by ras order to form groups, denoted as , , n is the number of rough processes between the parts inside the split heap; Step S408. According to the connecting piece set rb and the connecting piece order rbs , group the connecting piece set rb by rbs order to form groups, denoted as , , m is the number of rough processes between the parts of the split stacks; Step S409. Construct the connecting piece type set, denoted as c =(rivet, screw, blind rivet, bolt...), according to Step S407 and Step S408, there are a total of m + n rough processes. According to g and gb and c , split into fine processes, and the number of fine processes is denoted as de , where de ≥ m + n ; Step S410: Based on the set of connectors in step S409, construct a set of sorting fields, denoted as . For a single process, form work steps (i.e., the assembly sequence of key processes) according to the rule field; Step S411: Construct a set of special process specification processes, denoted as special = (drilling holes, installation...). According to step S409 and step S410, complete the generation and sorting of special processes in the process specification.

[0076] By adopting this embodiment, the order of connectors is determined through the part order, reducing the time for process personnel to determine the order of connectors; by constructing a set of special process specification processes, the generation and sorting of special processes in the process specification are completed, improving the time for splitting work steps and compiling processes in the process specification.

[0077] Embodiment 7 This embodiment further optimizes on the basis of the above Embodiments 1 to 6. In this embodiment, after obtaining the digital model information of the assembly scenario, it further includes: constructing the metadata of the aircraft part model according to the digital model information of the assembly scenario, and constructing the knowledge graph network of the aircraft according to the metadata of the aircraft part model, so as to perform cross-BOM traceability on the metadata of the aircraft part model by using the depth or breadth traversal algorithm of the knowledge graph when data traceability is required.

[0078] Specifically, in an optional implementation manner, data traceability includes the following steps: Step S501: Define the metadata paradigm of the part model and construct the metadata of the part model. Specifically, define the metadata O{Oid, O1, O2…Oi}, where Oid is the unique identification identity of the metadata, and Oi is a set of a certain type of data in the metadata; to ensure the accuracy of the data, for a type of data Oi, create a set Q{Q1, Q2…Q i} to represent the security verification of the data, and Qi represents its i-th security mechanism; for each type of data Oi, create a set T{T1, T2…Ti} to represent the integrity verification of the data, and Ti represents its i-th integrity verification mechanism; Taking engineering data and manufacturing data as examples, for each actual material object of each aircraft model, a unique identification code ID is assigned to it. Its data set includes {engineering data set, manufacturing data set, physical data set, maintenance data set...}, and its security mechanism includes {drawing number cannot be empty, name cannot be empty, version of the engineering data set cannot be empty, using unit and manufacturing unit in the manufacturing data set cannot be empty...}, and its integrity mechanism includes {engineering data set cannot be empty, manufacturing data set cannot be empty...}. For example, the specific data objects are: part 1 {drawing number 1, parent node part 2, child node part 3, belonging to the manufacturing BOM, belonging to the engineering BOM...}, part 2 {drawing number 2, parent node part 4, child node part 3, belonging to the engineering BOM...}, part 3 {drawing number 3, parent node part 2, child node part 5, belonging to the engineering BOM...}, part 4 {drawing number 4, parent node part 6, child node part 5, belonging to the engineering BOM...}, part 5 {drawing number 5, parent node part 4, belonging to the engineering BOM...}, part 6 {drawing number 6, child node part 4, belonging to the manufacturing BOM...}... part n {drawing number n,...}.

[0079] Step S502: Based on the knowledge graph, construct the data relationship of the part model. Clearly define the graph network of metadata through nodes, node attributes, edges, and edge attributes, and form the graph network M of the aircraft data. Among them, a single logical relationship can be expressed as <Oi, Bi, Oj>, where Oi represents the i-th metadata object, Oj represents the j-th metadata object, and Bi represents the i-th relationship between two metadata. Then the graph network M between two metadata is {<Oi, B1, Oj>, <Oi, B2, Oj>... <Oi, Bi, Oj>}. Starting from the engineering data set, generate the relationship graph between all material objects, and based on this graph, expand the graph content of different links. Step S503: Conduct cross-BOM data traceability based on the data link diagram. Specifically, through the depth-first or breadth-first traversal algorithm of the knowledge graph, trace the full life cycle process of the metadata. Through keywords such as name and drawing number, adopt the graph depth-first or breadth-first traversal search algorithm to obtain the data results of the full life cycle process of the current metadata object. Based on the current part traceability graph, calculate the relevance and influence degree analysis of each node through the PageRank algorithm. The calculation formula is: PR(I)=(1-d)+d * sum{j\B_i}\frac{PR(j)}{L(j)}, where PR(I) is the PageRank value of node i, d is the damping factor, which is 0.85 here, B_i is the set of all nodes pointing to node i, L(j) is the number of outgoing edges of node j, and "sum{j\B_i}\frac{PR(j)}{L(j)" represents the PageRank value of other nodes pointing to this node. Each node is assigned an initial PageRank value of frac{1}{6}, which is about 0.1666; For example, for the first round of Part 1 node, there is a Part 2 node pointing to it, so its "sum{j\B_i}\frac{PR(j)}{L(j)" value is 0.1666, then PR(Part 1)=(1-0.85)+0.85*0.1666=0.39161, and the calculation method for the remaining nodes is similar. Repeat the iteration until the PR(I) value of all nodes changes less than the threshold. Here the threshold is set to 0.0001, and all nodes are sorted according to the calculated value; According to the breadth-first algorithm, find all the nodes of Part 1, and take the node with the largest PageRank value as its next tracing node. Continue to compile downwards through the depth traversal algorithm until a more node is found. Finally, with Part 1 as input, its shortest tracing link is {Part 1, Part 2, Part 4, Part 6}.

[0080] By adopting this embodiment, by constructing metadata, security verification mechanism, and integrity verification mechanism of the data, and establishing the relationship between the data, cross-BOM traceability of the data is achieved, which solves the data characteristics in aircraft manufacturing, such as multiple data types, multiple transmission processes, large data volume, and data modification and production in each link, which leads to errors and omissions in the aircraft data traceability process, difficult data traceability, and strong manual dependence.

[0081] Example 8 An embodiment of a detailed process design system for aircraft component assembly includes: A digital-analog information acquisition module, which is used to acquire digital-analog information of an assembly scene; A process specification template generation module, wherein the process specification template generation module is used to establish a process specification template corresponding to an assembly scenario according to an assembly process flow and a standard process library; A planning module, which is used to analyze the digital model information to obtain the analysis results, and obtain the process specification node planning results and process specification material planning results in the two dimensions of space and time of the assembly scene according to the analysis results; A process parameter library generation module, which is used to establish a process parameter library according to process knowledge and process rules; A process specification document compilation module, which is used to compile a process specification document according to a process specification template, a process specification material planning result, a process specification node planning result, and a process parameter library, so as to obtain a process specification document representing the detailed process of aircraft component assembly.

[0082] Embodiment 9 An embodiment of a computer-readable storage medium, on which a computer program is stored, and when the program is executed by a processor, it implements the detailed process design method for aircraft component assembly described in the above Embodiments 1 to 7.

[0083] As mentioned above, the above are only the preferred embodiments of the present invention, and do not impose any form of limitation on the present invention. Any simple modification or equivalent change made to the above embodiments based on the technical essence of the present invention falls within the protection scope of the present invention.

Claims

1. A detailed process design method for aircraft component assembly, characterized in that, Including: S01. Obtain the digital mock-up information of the assembly scenario; S02. Define the assembly process flow according to the assembly process plan, adjust the assembly process flow according to the production mode, establish the corresponding relationship between the assembly scenario and the process specification template, adjust the assembly process flow of each assembly scenario according to the assembly scenario and the standard operation library, establish the process specification execution flow and the process specification operation flow, and establish the process specification template corresponding to the assembly scenario according to the corresponding relationship between the assembly scenario and the process specification template, the process specification execution flow and the process specification operation flow; Analyze the digital mock-up information to obtain the analysis result, and obtain the process specification node planning result and the process specification material planning result in the two dimensions of space and time of the assembly scenario according to the analysis result; Establish a process parameter library according to process knowledge and process rules; S03. Compile the process specification document according to the process specification template, the process specification material planning result, the process specification node planning result and the process parameter library, and obtain the process specification document representing the detailed process of aircraft component assembly.

2. The detailed process design method for aircraft component assembly according to claim 1, wherein, The steps of establishing the process specification template corresponding to the assembly scenario according to the corresponding relationship between the assembly scenario and the process specification template, the process specification execution flow and the process specification operation flow include: Firstly, determine the information types included in the process specification, define the generation methods of the information of each component element of the process specification according to the information types, and determine the target component elements; Secondly, define the hierarchical relationship between the process specification template and the process specification operation according to the assembly process flow of aircraft assembly to determine the structural form of the process specification operation set and define the corresponding expression method according to the process specification template type of each type of process specification; define the classification methods of the assembly type, the process specification template type and the process specification operation type, and establish the corresponding relationship between the process specification operation type and the process specification operation set to obtain the operation parameters of the process specification template; Finally, according to the digital mock-up information of the assembly scenario, obtain the recognition conditions of the process specification operation set to determine the operation time sequence, and combine the process specification operations matching the assembly scenario according to the operation time sequence according to the target component elements, the hierarchical relationship and the corresponding relationship between the process specification operation type and the process specification operation set to generate the process specification template corresponding to the assembly scenario.

3. The detailed process design method for aircraft component assembly according to claim 1, characterized in that, The method of establishing a process parameter library according to process knowledge and process rules includes: Firstly, define the assembly requirements involved in the assembly process flow, and generate process knowledge and process rules according to the assembly requirements; Secondly, construct the data association relationship between the process parameter libraries to obtain process parameters in the assembly process flow; generate the process parameter library according to the data association relationship, process knowledge and process rules; Finally, according to the characteristics of the assembly information in the process of process specification compilation, define the calculation logic rules corresponding to the process parameter library, construct a parameter acquisition mode for uniformly pushing data for the process parameters under the specified process, and construct an active retrieval data parameter acquisition mode for the process parameter library common to the whole process.

4. The aircraft component assembly detailed process design method according to claim 3, characterized in that When compiling the process specification document for aircraft component assembly connection, the method of establishing a process parameter library according to process knowledge and process rules includes: Construct a multi-dimensional input / output data form for the assembly connection process parameter library according to the data retrieval scheme, data source, and logical rules of the process parameters used in the aircraft component assembly process flow. Generate assembly connection process knowledge and assembly connection process rules based on the assembly connection process experience and assembly connection process requirements of the aircraft component assembly connection process. Associate the data tables in the assembly connection process parameter library according to the key fields in the assembly connection process parameter library, and construct the data association relationship between the assembly connection process parameter libraries. Establish a process parameter library including the assembly connection operation process parameter library and the assembly connection general process parameter library according to the data association relationship, data form, assembly connection process knowledge, and assembly connection process rules between the assembly connection process parameter libraries. Construct a parameter acquisition mode for uniformly pushing data for the assembly connection operation process parameter library, and construct a parameter acquisition mode for actively retrieving data for the assembly connection general process parameter library.

5. The detailed process design method for aircraft component assembly according to claim 1, characterized in that, When compiling the aircraft component assembly connection process specification document, the method for establishing the process specification template for aircraft component assembly connection includes: Define the aircraft component assembly elements that affect the aircraft component assembly connection process flow. Establish the association relationship between the aircraft component assembly elements and the aircraft component assembly connection process flow and construct the aircraft component assembly connection process flow. Establish the process specification template for aircraft component assembly connection according to the aircraft component assembly connection process flow and the standard operation library.

6. The method for detailed process design of aircraft component assembly according to claim 5, characterized in that, When compiling the aircraft component assembly connection process specification document, the method for obtaining the process specification document representing the detailed process of aircraft component assembly according to the process specification template, the process specification material planning result, the process specification node planning result, and the process parameter library includes: Define the parameter types of the assembly connection process parameters. Establish the parameter association relationship between the assembly connection process parameters according to the materials in the material library involved in the actual aircraft component assembly connection process flow, and construct the acquisition logic of the assembly connection process parameters. Obtain the assembly connection process parameters of the specified parameter type from the process parameter library according to the acquisition logic. Obtain the aircraft component assembly connection process specification document according to the process specification template, the process specification material planning result, the process specification node planning result, and the assembly connection process parameters.

7. The detailed process design method for aircraft component assembly according to claim 1, characterized in that, The method for obtaining the process specification material planning results in the two dimensions of space and time of the assembly scene according to the analysis results of the digital model information includes: Analyze the digital model information to obtain the analysis results. According to the analysis results of the materials to be assembled, the connectors, and the connector matching materials in the analysis results, obtain the connection relationship between the materials to be assembled and the connectors, and the matching relationship between the connectors and the connector matching materials, so as to complete the process specification material planning of the assembly sequence in the assembly scene space. According to the assembly timing of the materials in different process specification templates in the assembly process flow and their roles in the assembly process flow, as well as the material distribution and outbound constraint conditions, divide the materials to be assembled, the connectors, and the connector matching materials into different process specification templates to complete the process specification material planning of the assembly sequence in the assembly scene time.

8. The detailed process design method for aircraft component assembly according to claim 1, characterized in that Based on the spatial and temporal assembly sequences corresponding to the assembly scenario, establish the planning results of process specification nodes in the two dimensions of space and time for the assembly scenario, including: Analyze the digital model information of the assembly scenario to obtain the analysis result; According to the design digital model structure form in the analysis result, divide the aircraft zero-standard parts and materials to be assembled by the spatial dimension, and sort the division result in the spatial dimension according to the assembly simulation situation or the spatial assembly sequence of the design digital model structure; According to the assembly process flow, the requirements of work centralization, and the requirements of refined division of labor, sort the process specification templates involved in each group of materials in the temporal dimension; Split and merge the process specifications according to the workload requirements of a single process specification in the actual assembly process flow; According to the assembly sequences in the temporal and spatial dimensions of the assembly scenario, plan and sort all the process specifications, and plan the numbers and names of the process specification nodes according to the coding principle and naming principle.

9. The detailed process design method for aircraft component assembly according to claim 1, characterized in that: The assembly scenario includes the assembly of the frame structure, the assembly of system fixed points, the assembly of skin and covers, the laying of system ducts and wiring harnesses, and the installation of system ducts and wiring harnesses.

10. The method for detailed process design of aircraft component assembly according to claim 9, characterized in that, When the assembly scenario is the assembly of the frame structure, classify the frame parts in the digital model information.

11. The aircraft component assembly detailed process design method according to claim 1, wherein, When the assembly scenario is the assembly of the frame structure, before establishing the process specification template corresponding to the frame structure assembly according to the assembly process flow and the standard process library, it also includes the step of splitting the process steps of the frame process specification to complete the generation and sorting of the process steps of the frame process specification.

12. The aircraft component assembly detailed process design method according to claim 1, wherein, It also includes the step of recording and tracing the data formed during the planning and compilation of the process specification, including: constructing part model metadata for each part model, defining the paradigm of the part model metadata, including the data for identifying the identity of the part model and multiple sets corresponding to each BOM data of the part model, and creating a set data object for each set, and the set data object includes the data attribute information of the part model; storing the data formed during the planning and compilation of the process specification into the part model metadata; constructing a graph network of the part model metadata according to the logical relationship between the part model metadata; using the graph traversal algorithm to trace the whole life cycle process data of the part model in the graph network.

13. An aircraft component assembly detailed process design system, characterized in that, For implementing the detailed process design method for aircraft component assembly described in any one of claims 1-12, including: A digital model information acquisition module, which is used to acquire the digital model information of the assembly scenario; A process specification template generation module, which is used to establish the process specification template corresponding to the assembly scenario according to the assembly process flow and the standard process library; A planning module, which is used to analyze the digital model information to obtain the analysis result, and according to the analysis result, obtain the planning results of the process specification nodes in the two dimensions of space and time and the process specification material planning results of the assembly scenario; A process parameter library generation module, which is used to establish a process parameter library according to process knowledge and process rules; A process specification document compilation module, which is used to compile a process specification document based on a process specification template, a process specification material planning result, a process specification node planning result, and a process parameter library, so as to obtain a process specification document representing the detailed process of aircraft component assembly.

14. A computer-readable storage medium having a computer program stored thereon, characterized in that, When executed by a processor, the program implements the detailed process design method for aircraft component assembly according to any one of claims 1-12.

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