An aircraft component assembly detailed process design method, system and medium

Abstract

The application relates to the technical field of aircraft manufacturing, and discloses an aircraft component assembly detailed process design method, system and medium, which comprises the following steps: establishing a process procedure template corresponding to an assembly scene according to an assembly process flow and a standard process procedure library; planning process procedure nodes and process procedure materials from the two dimensions of an assembly scene space and time; establishing a process parameter library according to process knowledge and process rules; and finally automatically preparing process procedure documents, so that the aircraft component assembly detailed process is efficiently and accurately designed, and the technical problems of the existing aircraft assembly process design and process procedure preparation, such as the failure to combine the process procedure preparation with the assembly process flow, the low process procedure preparation efficiency and the low process procedure preparation accuracy are solved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft manufacturing, in particular to an aircraft component assembly detailed process design method, system and medium. BACKGROUND

[0002] The process procedure is a production process document prepared by the process department according to the design requirements, process technical requirements and quality requirements. The process procedure not only includes process information, but also production information and quality information, which guides workers to operate the specific work instructions of the specified assembly process flow, including operation instructions, processes, assembly timing, 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: pre-research stage, research and development stage and batch production stage. Among them, the research and development stage is the main stage of process design, including process joint design definition, top-level process planning, detailed process design, on-site execution, etc. The detailed process design work includes process planning process of material consumption and process procedure node planning, and process procedure compilation process of determining assembly process flow, process parameters, etc.

[0004] At present, three-dimensional process procedure compilation technology, knowledge engineering application, three-dimensional CAPP technology, etc. are mainly researches on advanced technology and advanced platform. In engineering practice, they are not combined with assembly process flow, and cannot play an accurate flow and information guiding role in the process of process personnel process procedure compilation. Process personnel need to spend a lot of time in the process of process preparation, process parameter, process standard, process data summary, calculation and transcription. The repetitive and tedious workload is huge, and the effective work efficiency of process personnel is low, which makes the process procedure compilation period longer, the process procedure compilation result standard poor, and even some quality errors may occur.

[0005] Therefore, an aircraft component assembly detailed process design method is needed to solve the technical problems of no combination of process procedure compilation and assembly process flow, low process procedure compilation efficiency, and low process procedure compilation accuracy in the existing aircraft assembly process design. SUMMARY

[0006] The application aims to provide an aircraft component assembly detailed process design method, system and medium, which realizes efficient and accurate design of aircraft component assembly detailed process by establishing a process procedure template corresponding to an assembly scene according to an assembly process flow and a standard process library, planning process procedure nodes and process procedure materials from the spatial and temporal dimensions of the assembly scene, establishing a process parameter library according to process knowledge and process rules, and finally automatically preparing process procedure documents.

[0007] The application is implemented by the following technical solutions:

[0008] In a first aspect, the application provides an aircraft component assembly detailed process design method, comprising:

[0009] S01, acquiring digital model information of an assembly scene;

[0010] S02, defining an assembly process flow according to an assembly process scheme, adjusting the assembly process flow according to a production mode, establishing a corresponding relationship between the assembly scene and a process procedure template, adjusting the assembly process flow of each assembly scene according to the assembly scene and a standard process library, establishing a process procedure execution flow and a process procedure process flow, and establishing a process procedure template corresponding to the assembly scene according to the corresponding relationship between the assembly scene and the process procedure template, the process procedure execution flow and the process procedure process flow;

[0011] The digital model information is analyzed to obtain an analysis result, and according to the analysis result, process procedure node planning results and process procedure material planning results in the spatial and temporal dimensions of the assembly scene are obtained;

[0012] According to process knowledge and process rules, a process parameter library is established;

[0013] S03, process procedure document preparation is performed according to the process procedure template, the process procedure material planning results, the process procedure node planning results and the process parameter library, and process procedure documents representing the aircraft component assembly detailed process are obtained.

[0014] In order to better implement the application, further, the step of establishing a process procedure template corresponding to the assembly scene according to the corresponding relationship between the assembly scene and the process procedure template, the process procedure execution flow and the process procedure process flow comprises:

[0015] First, the information types contained in the process procedure are determined, the generation mode of each component element information of the process procedure is defined according to the information types, and the target component elements are determined;

[0016] Then, according to the assembly process flow of the aircraft assembly, the hierarchical relationship between the process procedure template and the process procedure is defined to determine the structural form of the process procedure set and the corresponding expression method according to the process procedure template type definition of each type of process procedure; the classification method of the assembly type, the process procedure template type and the process procedure type is defined and the corresponding relationship between the process procedure type and the process procedure set is established to obtain the process procedure parameters of the process procedure template;

[0017] Finally, according to the digital model information of the assembly scene, the identification conditions of the process procedure set are obtained to determine the process procedure timing, and according to the target component, the hierarchical relationship and the corresponding relationship between the process procedure type and the process procedure set, the process procedure matched with the assembly scene is combined according to the process procedure timing to generate the process procedure template corresponding to the assembly scene.

[0018] In order to better realize the present application, further, the method for establishing the process parameter library according to the process knowledge and the process rules comprises:

[0019] Firstly, the assembly requirements involved in the assembly process flow are defined, and the process knowledge and the process rules are generated according to the assembly requirements;

[0020] Then, the data association relationship between the process parameter libraries is constructed to obtain the process parameters in the assembly process flow; the process parameter library is generated according to the data association relationship, the process knowledge and the process rules;

[0021] Finally, according to the characteristics of the assembly information in the process procedure compilation process, the calculation logic rules corresponding to the process parameter library are defined, the parameter acquisition mode of unified pushing data is constructed for the process parameters under the specified flow, and the parameter acquisition mode of active searching data is constructed for the process parameter library common to the whole flow.

[0022] In order to better realize the present application, further, when compiling the aircraft component assembly connection process procedure document, the method for establishing the process parameter library according to the process knowledge and the process rules comprises:

[0023] According to the data retrieval scheme, the data source and the logic rules of the process parameters used in the aircraft component assembly process flow, the data form of the multi-dimensional input / output of the assembly connection process parameter library is constructed;

[0024] According to the assembly connection process experience and the assembly connection process requirements of the aircraft component assembly connection flow, the assembly connection process knowledge and the assembly connection process rules are generated;

[0025] According to the key fields in the assembly connection process parameter library, the data tables in the assembly connection process parameter library are associated to construct the data association relationship between the assembly connection process parameter libraries;

[0026] According to the data association relationship between the assembly connection process parameter library, the data form, the assembly connection process knowledge and the assembly connection process rule, a process parameter library including an assembly connection process parameter library and an assembly connection general process parameter library is established;

[0027] A parameter acquisition mode of unified pushing data is constructed for the assembly connection process parameter library, and a parameter acquisition mode of active data retrieval is constructed for the assembly connection general process parameter library.

[0028] In order to better realize the present application, further, after establishing the process procedure template corresponding to the assembly scene, the judgment logic of the assembly elements affecting the assembly process flow of the aircraft part assembly connection is constructed according to the assembly connection process parameter library.

[0029] In order to better realize the present application, further, when compiling the aircraft part assembly connection process procedure document, the method for establishing the process procedure template of the aircraft part assembly connection according to the assembly process flow and the standard process library comprises:

[0030] Defining the aircraft part assembly elements affecting the assembly process flow of the aircraft part assembly connection;

[0031] Establishing the correlation between the aircraft part assembly elements and the assembly process flow of the aircraft part assembly connection and constructing the assembly process flow of the aircraft part assembly connection;

[0032] According to the assembly process flow of the aircraft part assembly connection and the standard process library, the process procedure template of the aircraft part assembly connection is established.

[0033] In order to better realize the present application, further, when compiling the aircraft part assembly connection process procedure document, the method for compiling the process procedure document according to the process procedure template, the process procedure material planning result, the process procedure node planning result and the process parameter library to obtain the process procedure document representing the detailed process of the aircraft part assembly comprises:

[0034] Defining the parameter type of the assembly connection process parameter;

[0035] According to the materials in the material library involved in the actual aircraft part assembly connection process flow, the parameter association relationship between the assembly connection process parameters is established, and the acquisition logic of the assembly connection process parameter is constructed;

[0036] According to the acquisition logic, the assembly connection process parameter of the specified parameter type is acquired from the process parameter library;

[0037] According to the process procedure template, the process procedure material planning result, the process procedure node planning result and the assembly connection process parameter, the aircraft part assembly connection process procedure document is obtained.

[0038] In order to better realize the present application, further, according to the analysis result of the digital model information, the method for obtaining the process procedure material planning result of the two dimensions of space and time of the assembly scene comprises:

[0039] The digital model information is analyzed to obtain an analysis result;

[0040] According to the analysis result of the to-be-assembled material, the connecting piece and the connecting piece matching material, the connecting relationship between the to-be-assembled material and the connecting piece, and the matching relationship between the connecting piece and the connecting piece matching material are obtained to complete the process procedure material planning of the spatial assembly sequence of the assembly scene;

[0041] According to the assembly timing of the material in different process procedure templates in the assembly process and the role of the material in the assembly process, and the material distribution and warehouse constraint condition, the to-be-assembled material, the connecting piece and the connecting piece matching material are divided in different process procedure templates to complete the process procedure material planning of the time assembly sequence of the assembly scene.

[0042] In order to better realize the present application, further, according to the spatial assembly sequence and the time assembly sequence corresponding to the assembly scene, the method for establishing the process procedure node planning result of the two dimensions of space and time of the assembly scene comprises:

[0043] The digital model information of the assembly scene is analyzed to obtain an analysis result;

[0044] According to the design digital model structure form in the analysis result, the to-be-assembled aircraft part material is divided in the spatial dimension, and the division result is sorted in the spatial dimension according to the assembly simulation condition or the spatial assembly sequence of the design digital model structure;

[0045] According to the assembly process, the centralized work requirement and the fine division requirement, the process procedure templates involved by each group of materials are sorted in the time dimension;

[0046] According to the single process procedure work requirement in the actual assembly process, the process procedure is split and merged;

[0047] According to the time dimension and the spatial dimension assembly sequence of the assembly scene, all the process procedures are planned and sorted, and the number and name of the process procedure nodes are planned according to the coding principle and the naming principle.

[0048] In order to better realize the present application, further, the assembly scene comprises a skeleton structure assembly, a system fixed point assembly, a skin cover assembly, a system conduit line bundle laying and a system conduit line bundle installation.

[0049] In order to better realize the present application, further, when the assembly scene is the skeleton structure assembly, the skeleton parts in the digital model information are classified.

[0050] In order to better realize the present application, further, when the assembly scene is a skeleton structure assembly, before establishing the process procedure template corresponding to the skeleton structure assembly according to the assembly process flow and the standard process library, the step of splitting the skeleton process procedure process step is further included to complete the generation and sequencing of the skeleton process procedure process.

[0051] In order to better realize the present application, further, the step of recording and tracing the data formed in the process procedure planning and preparation process is further included, 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 a plurality of sets corresponding to each BOM data of the part model, and creating a set data object for each set, the set data object including data attribute information of the part model; storing the data formed in the process procedure planning and preparation process 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 tracing the whole life cycle process data of the part model in the graph network using a graph traversal algorithm.

[0052] In a second aspect, the present application provides an aircraft component assembly detailed process design system, comprising:

[0053] A digital model information acquisition module, the digital model information acquisition module is used for acquiring digital model information of an assembly scene;

[0054] A process procedure template generation module, the process procedure template generation module is used for establishing a process procedure template corresponding to the assembly scene according to an assembly process flow and a standard process library;

[0055] A planning module, the planning module is used for analyzing the digital model information to obtain an analysis result, and obtaining process procedure node planning results and process procedure material planning results of the assembly scene in two dimensions of space and time according to the analysis result;

[0056] A process parameter library generation module, the process parameter library generation module is used for establishing a process parameter library according to process knowledge and process rules;

[0057] A process procedure document preparation module, the process procedure document preparation module is used for preparing a process procedure document according to the process procedure template, the process procedure material planning results, the process procedure node planning results and the process parameter library to obtain a process procedure document representing an aircraft component assembly detailed process.

[0058] In a third aspect, the present application provides a computer readable storage medium having a computer program stored thereon, characterized in that the program, when executed by a processor, realizes the aircraft component assembly detailed process design method of any one of the first aspect.

[0059] Compared with the prior art, the present application has the following advantages and beneficial effects:

[0060] By establishing the process procedure template corresponding to the assembly scene in the assembly process flow and the standard process library, the process procedure compilation is not combined with the assembly process flow, and the process procedure compilation can be accurately and automatically performed, thereby improving the process procedure compilation efficiency.

[0061] By planning the process procedure node and the process procedure material from the spatial and temporal dimensions of the assembly scene, the accuracy of the process procedure compilation result is further improved.

[0062] By establishing the process parameter library based on the process knowledge and the process rules, the process parameters are automatically obtained, and the process procedure compilation efficiency and the accuracy of the process procedure compilation result are further improved. BRIEF DESCRIPTION OF DRAWINGS

[0063] The present application is further illustrated in combination with the following drawings and examples, and all the conception innovations of the present application should be regarded as the disclosed content and the protection scope of the present application.

[0064] Figure 1 It is a flowchart of an embodiment of the present application for a detailed process design method of an aircraft component assembly.

[0065] Figure 2 It is a relationship diagram of an embodiment of the present application for a detailed process design method of an aircraft component assembly.

[0066] Figure 3 It is a spatial assembly sequence and a temporal assembly sequence diagram of an embodiment of the present application for a detailed process design method of an aircraft component assembly.

[0067] Figure 4 It is a relationship diagram of an embodiment of the present application for a detailed process design method of an aircraft component assembly. DETAILED DESCRIPTION

[0068] Example 1

[0069] The method comprises the following steps: firstly, obtaining numerical model information of an assembly scene; then, establishing a process procedure template corresponding to the assembly scene according to an assembly process flow and a standard process library; analyzing the numerical model information to obtain an analysis result, and obtaining process procedure node planning results and process procedure material planning results of the assembly scene in two dimensions of space and time according to the analysis result; establishing a process parameter library according to process knowledge and process rules; finally, preparing a process procedure document according to the process procedure template, the process procedure material planning results, the process procedure node planning results and the process parameter library, and obtaining a process procedure document representing a detailed process of aircraft component assembly.

[0070] Referring to Figure 1 a specific embodiment of the embodiment;

[0071] In the embodiment, the assembly scene is set according to the actual situation of the aircraft, and can include assembly scenes such as skeleton structure assembly, system fixed point assembly, skin cover assembly, system conduit bundle laying and system conduit bundle installation;

[0072] The assembly process flow refers to an assembly process flow in the detailed process design stage, which includes part sequence of aircraft assembly, assembly process flow between process procedure nodes and process flow inside the process procedure, and is determined by an assembly process scheme and a production mode;

[0073] A general assembly process flow can be formulated according to the assembly form and assembly scheme of each assembly scene, and the general assembly process flow can be directly used for different production forms of each assembly scene, so that the preparation efficiency of the process procedure template can be improved;

[0074] Specifically, for example, the general assembly process flow of the connection type is positioning-drilling-installation, which involves three general assembly process procedure templates; for the centralized production mode of skeleton structure assembly, the general assembly process flow (positioning-drilling-installation) can be directly used.

[0075] Further, the internal process flow of the assembly scene process procedure template is established, the material type and attribute used in the assembly process flow are obtained, the assembly process flow under each assembly scene is further refined, and it is judged whether each process meets the occurrence condition, and the internal process flow of the assembly scene process procedure template is established;

[0076] Specifically, for example, the "cold extrusion" process procedure template of the skeleton structure assembly fine division production mode, a template only contains cold extrusion operation, according to the assembly process scheme and design requirements, four processes can be set: check the use state of cold extrusion tool-cold extrusion operation-excessiveness check-check the quality of cold extrusion and excessiveness removal; The process flow of the installation process procedure template of the connection type is: gluing-riveting-pasting-screwing-inspection-installation-installation-excessiveness removal-inspection-protection.

[0077] In the embodiment, the process procedure node planning refers to, after the top-level process planning of the MBOM top-level structure design is completed, the work of the assembly scene is decomposed according to the assembly process flow, the design model structure form, the assembly workload and other rules, and a work list for on-site operation of workers is formed.

[0078] In the embodiment, the process procedure material planning refers to, after the top-level process planning of the MBOM top-level structure design is completed, the materials such as components, standard parts and finished products in the design model are allocated to the workstations under the aircraft part nodes and the process procedures according to the process division principle and the process separation surface division principle, the material consumption is completed, and serves as the basis for compiling the process procedure document supporting table;

[0079] The process knowledge and process rules are formed by combing the assembly requirements, i.e. the specific design and process requirements in the assembly process flow, to support the process parameter requirements in the specified process and the process parameter requirements in the whole process in the process procedure compilation process.

[0080] In summary, in the embodiment, the process procedure node and material information in the planning result are taken as the basis, the process procedure template and the process parameter library are combined, the process procedure document is compiled, the detailed process design of the aircraft part assembly is completed, the material consumption, the process procedure node planning and the process procedure compilation process in the process procedure compilation process are realized, the process procedure document compilation is completed, and the technical problems of the existing aircraft assembly process design, the process procedure compilation without combination with the assembly process flow, the low process procedure compilation efficiency and the low process procedure compilation accuracy are solved.

[0081] Embodiment 2

[0082] This embodiment is further optimized on the basis of the above-mentioned embodiment 1. In this embodiment, referring to Table 1, the assembly scene includes skeleton structure assembly, system fixed point assembly, skin cover assembly, system conduit line bundle laying and system conduit line bundle installation.

[0083] Table 1

[0084]

[0085] In an optional embodiment of the embodiment, according to the assembly process flow and the standard process library, the method for establishing the process procedure template corresponding to the assembly scene comprises the following steps:

[0086] Firstly, the assembly process flow is defined according to the assembly process scheme;

[0087] Then, the assembly process flow is adjusted according to the production mode, the corresponding relationship between the assembly scene and the process procedure template is established, the process procedure execution flow and the process procedure flow are established by adjusting the assembly process flow of each assembly scene according to the assembly scene and the standard process library;

[0088] Finally, the process procedure template corresponding to the assembly scene is established according to the corresponding relationship between the assembly scene and the process procedure template, the process procedure execution flow and the process procedure flow.

[0089] By adopting the embodiment, the general assembly process flow is combined and split, the assembly process flow is designed respectively, the production forms such as centralized work, fine division of labor, semi-centralized and semi-fine division of labor of the actual production and process state management are adapted, the corresponding relationship between the assembly scene and the process procedure template is established, different assembly scenes are flexibly coped with, and the adaptability of the process procedure template and the assembly scene is improved.

[0090] Specifically, for the centralized work production mode of the skeleton structure assembly, positioning and hole making can be combined in the form of pre-assembly (pre-assembly-installation), or positioning, hole making and installation can be combined in the form of centralized assembly. For the fine division of labor production mode of the skeleton structure assembly, hole making and installation can be split according to the work rhythm. Finally, the overall assembly process flow after splitting is as follows: positioning-cold extrusion initial hole-cold extrusion-hole making-tapping-plate nut installation-bolt installation-inspection, which involves 8 types of process procedure templates.

[0091] In another optional embodiment of the embodiment, according to the assembly process flow and the standard process library, the method for establishing the process procedure template corresponding to the assembly scene further comprises the following steps:

[0092] Firstly, the information types contained in the process procedure are determined, the generation mode of each component information of the process procedure is defined according to the information types, and the target component is determined.

[0093] Then, the hierarchical relationship between the process procedure template and the process procedure is defined according to the assembly process flow of the aircraft assembly, so as to determine the structure form of the process procedure set and define the corresponding expression method according to the process procedure template type of each type of process procedure; the classification method of the assembly type, the process procedure template type and the process procedure type is defined, and the corresponding relationship between the process procedure type and the process procedure set is established, so as to obtain the process procedure parameters of the process procedure template.

[0094] Finally, according to the digital model information of the assembly scene, the identification conditions of the process procedure set are obtained to determine the procedure timing, and the process procedure matching the assembly scene is combined according to the target component, the hierarchical relationship and the correspondence between the process procedure type and the process procedure set, to generate a process procedure template corresponding to the assembly scene.

[0095] By analyzing the assembly type and the process procedure type of the aircraft assembly from the substantive perspective of assembly, designing the occurrence conditions of the procedures in the assembly process, and sorting out the logical rules of the key conditions affecting the procedure content, the procedures associated by the rules are presented in the process procedure template in a certain structural form and hierarchical relationship. In the subsequent process procedure compilation process, when the digital model information contained in the assembly scene meets the occurrence conditions of the procedure, the procedure meeting the assembly scene will appear in the process procedure, and the procedure content can be obtained by combining the process parameter library and the digital model information, so as to realize the rapid compilation of the aircraft assembly process procedure and form the final complete process procedure document. Through the design of the process procedure template and the compilation of the process procedure content, the compilation efficiency and quality of the process document can be effectively improved, the manual workload and human error can be reduced, strong technical support can be provided for the intelligentization and standardization of the aircraft assembly process, and the deep integration of information technology and assembly process design technology can be promoted.

[0096] Specifically, the information types contained in the process procedure include operation instructions, procedures, procedure timing, operation instructions, as a similar fixed procedure, procedures, i.e. multiple procedures with timing relationship and reflecting the process flow of the current assembly scene, procedure timing, providing the execution order of multiple procedures, wherein the procedure further contains procedure parameters providing specific position, quantity, assembly requirements and other information of the operation, material, tooling, material list and other parameter information such as certificate holding and standard operation procedure; according to the timing of the information in the process procedure, some quality information records that cannot be known in advance in the process procedure compilation process need to be improved gradually in the production process according to the actual situation, and the design change information for the design change and optimization in the later stage is not considered as the content of the process procedure template, while some information obtained by logical rule reasoning and process parameter acquisition according to the actual situation of the assembly digital model, and some fixed sentences can be included in the process procedure template.

[0097] The assembly process flow of aircraft assembly can be subdivided into multiple levels, including assembly scenes, process procedure templates, process procedure procedure sets and procedures, each level containing rich process information and execution details; in this multi-level structure, each assembly scene corresponds to multiple process procedure templates, each process procedure template contains multiple process procedure procedure sets, and each process procedure procedure set may contain multiple procedures with the same name;

[0098] To solve the problem of identifying procedures with the same name, the present embodiment also introduces the concept of "procedure label", which realizes accurate differentiation between procedures with the same name by assigning a unique label to each procedure. When a specific procedure needs to be located, the current assembly scene is first determined, which is the starting point for searching the procedure; then, in the assembly scene, the process procedure template matching the current assembly task is selected, in the selected process procedure template, the process procedure procedure set related to the assembly task is found, and in the process procedure procedure set, the procedure is preliminarily located according to the name of the procedure; finally, the unique procedure label is used to accurately identify the target procedure from the possible procedures with the same name.

[0099] In the present embodiment, the structure of the process procedure procedure set is that each procedure in the process procedure procedure set is activated at the same time when encountering a specific material feature or assembly process scheme. This mechanism ensures that related procedures can be automatically and synchronously executed in assembly scenes that meet specific conditions, improving the efficiency and consistency of the assembly process flow. Of course, for procedures that are extremely versatile and need to be executed in multiple conditions, they can also be divided into multiple process procedure procedure sets. This ensures that these key procedures can be triggered in any assembly scene, avoiding process defects that may be caused by condition judgment omissions. In addition, for procedures that need to appear in a specific assembly scene regardless of any conditions, the present invention provides a default appearing process procedure procedure set. This design ensures that these procedures can be automatically executed in any situation and can flexibly meet the needs of different assembly scenes, ensuring accurate triggering and efficient execution of procedures.

[0100] In the present embodiment, referring to Table 2, the assembly types mainly include connectors, contacts, relative motion, plugs and other types, each type has different functions in aircraft assembly and has specific material and assembly form characteristics; analyze the role of each assembly type in aircraft assembly and the characteristics of material and assembly form in the assembly process flow, and according to the assembly characteristics, preliminarily identify the process procedure template type and procedure type required for this type of assembly.

[0101] Table 2

[0102]

[0103] By analyzing the material characteristics, assembly process scheme that may be involved in the assembly process flow, the influence of process and internal parameter information, the key condition of process occurrence is generated, and the process type and process procedure set are correspondingly related through this key condition.

[0104] In this embodiment, by taking the key condition of process occurrence as the process procedure set of the assembly process plan template, the identification conditions of the process procedure set are sorted into three forms of rules, such as fixed statements, logic diagrams, and process parameter library, to determine the process timing. The fixed statement rule is a concise and intuitive expression method for describing the necessary conditions for process occurrence. The logic diagram rule shows the logical relationship of the process occurrence conditions through the form of flowchart or decision tree, which is used to handle process selection under complex conditions. The process parameter library rule means that the process parameter information is stored in the database, and the corresponding process parameters are automatically obtained according to the key condition of process occurrence through the query and matching mechanism. This rule is suitable for standardized management and rapid retrieval of process parameter information.

[0105] By refining the element information contained in the process plan template and its generation method, the information automatically generated according to the assembly model information, logical reasoning rules, process parameters, and some fixed description statements are pre-set in the process plan template.

[0106] The hierarchical relationship between the process plan template and the process procedure is defined to support the decomposition from the template to the process and the combination from the process to the template. Through the establishment of this two-way hierarchical relationship, the flexible application and efficient management of the process plan template can be realized, and it is also convenient for process designers to customize and adjust the template according to actual needs.

[0107] The occurrence conditions of the process are designed, and the process is combined to form the corresponding process plan template according to the association relationship between the process type and the process procedure set. In this way, a general template can be designed, and the required process can be adaptively matched according to the model information contained in the assembly scene, without the need to design a template for each situation.

[0108] By defining the classification methods of assembly type, process plan template type, and process type, and establishing the corresponding relationship between process type and process procedure set, the classification and corresponding relationship establishment support the acquisition of process plan template process matching parameters, provide clear guidance for subsequent template design, and improve the universality and adaptability of the template.

[0109] Based on the process plan template, combined with the process parameter library and model information, the compilation of aircraft assembly process plan is realized.

[0110] In another alternative embodiment of the present embodiment, according to the process knowledge and process rules, the method for establishing the process parameter library comprises:

[0111] Firstly, define the assembly requirements involved in the assembly process flow, and generate process knowledge and process rules according to the assembly requirements;

[0112] Then, build the data association relationship between the process parameter libraries, so as to obtain the process parameters in the assembly process flow; generate the process parameter library according to the data association relationship, the process knowledge and the process rules;

[0113] Finally, according to the characteristics of the assembly information in the process procedure preparation process, define the calculation logic rules corresponding to the process parameter library, build the parameter acquisition mode of unified pushing data for the process parameters under the specified flow, and build the parameter acquisition mode of active searching data for the process parameter library common to the whole flow.

[0114] Specifically, the data form of the process parameter library is to sort the data retrieval scheme, data source and logic rule of the process parameters used according to the part assembly process flow into a multi-dimensional input and output data form, CLASS1{IN1;OUT1}; CLASS2{IN1, IN2, ……INn; OUT1}; CLASS3{IN1; OUT1, OUT2, OUT3, ……OUTn}; CLASS4{IN1, IN2, IN3, ……INn; OUT1, OUT2, OUT3, ……OUTn}, wherein CLASS1 supports the unified identification of the initial data program, CLASS2 supports the logical reasoning of a unique result after multi-condition input, CLASS3 supports multi-dimensional definition after data input, and outputs different dimensional results which can be applied in different scenarios, and CLASS4 supports the logical reasoning of different dimensional results after multi-condition input, which can be applied in different scenarios;

[0115] The process parameters whose calculation logic rules change with the change of the process procedure template or the process sequence are defined as the process parameters under the specified flow. Different calculation logic rules and different process parameter libraries need to be designed for different process procedure templates, and even different process parameters. For example, in one template and one process sequence, multiple CLASS types of data retrieval scheme, data source and logic rule are used to complete the output of complete information.

[0116] The process parameters whose calculation logic rules are the same regardless of the process procedure template or the location of the process procedure are defined as process parameters common to the whole process. To avoid repeated searching for process parameters during process procedure compilation, a set of parameter libraries is uniformly established. According to the process procedure template, the corresponding process procedure and the material planning, and the uniform calculation logic rules, the process parameters common to the whole process are uniformly pushed to the process procedure template and placed in the process parameter position corresponding to the process procedure template. Each process parameter corresponds to only one data searching scheme, data source and logic rule. For example, a CLASS type can be applied to the calculation of a common process parameter of all process procedure templates.

[0117] In the embodiment, according to the analysis result of the digital model information, the method for obtaining the process procedure material planning result corresponding to the assembly scene includes:

[0118] The digital model information is analyzed to obtain an analysis result.

[0119] According to the analysis result of the to-be-assembled material, the connecting piece and the connecting piece matching material, the connecting relationship between the to-be-assembled material and the connecting piece, and the matching relationship between the connecting piece and the connecting piece matching material are obtained to complete the process procedure material planning of the spatial assembly sequence of the assembly scene.

[0120] According to the assembly timing of the material in different process procedure templates in the assembly process and the role of the material in the assembly process, and the material distribution and warehouse constraint condition, the to-be-assembled material, the connecting piece and the connecting piece matching material are divided into different process procedure templates to complete the process procedure material planning of the time assembly sequence of the assembly scene.

[0121] Specifically, the material in the spatial dimension of the assembly scene includes three types of to-be-assembled material, connecting piece and connecting piece matching material. The to-be-assembled material is the above-mentioned “a group of independent assembly parts material which can be assembled at one time”, the connecting piece is in the form of rivet, draw pin, bolt and screw, the connecting piece matching material is in the form of nut, washer and cotter pin, and is generally used simultaneously with the connecting piece to realize the connecting and fixing function of the to-be-assembled material.

[0122] Referring to Figure 2 The connecting relationship between the to-be-assembled material and the connecting piece, and the relationship between the connecting piece and the connecting piece matching material are obtained through digital model relationship analysis.

[0123] In the connection relationship database, the connection relationship between the to-be-assembled material and the connecting piece is found out. When the to-be-assembled materials having the connection relationship with the same connecting piece appear simultaneously in the "one-time independent assembly group of materials", it is indicated that the connecting piece is the connecting piece inside the "one-time independent assembly group of materials", and the corresponding connecting piece matching material of the connecting piece is also the connecting piece matching material inside the "one-time independent assembly group of materials";

[0124] The division of the material of the assembly scene time dimension is that, according to the assembly timing of the material in different process procedure templates in the assembly process flow and the role of the material in the assembly process flow, as well as the material distribution and warehouse release constraint condition, the to-be-assembled components, standard parts, and to-be-assembled material related connecting pieces and connecting piece matching materials are divided in different process procedure templates, that is, the material of each time assembly sequence of the assembly scene is determined;

[0125] For example, in the initial assembly stage, all to-be-assembled materials need to be positioned and pre-assembled, so all to-be-assembled materials are allocated in the positioning template. In the assembly hole making process, hole making work needs to be performed on the to-be-assembled materials that have been positioned, but since the to-be-assembled materials have been allocated to the positioning template, the materials do not need to be allocated in the hole making template. In the assembly connection process, the connecting piece needs to be inserted through the hole made on the to-be-assembled material, and the connecting piece matching material needs to be used to complete the fixed connection of the to-be-assembled material.

[0126] Referring to Figure 3 In the embodiment, according to the spatial assembly sequence and the time assembly sequence corresponding to the assembly scene, a method for establishing the process procedure node planning result corresponding to the assembly scene includes the following steps:

[0127] Analyzing the digital model information of the assembly scene to obtain an analysis result;

[0128] According to the design digital model structure form in the analysis result, the to-be-assembled aircraft component material is divided in the spatial dimension, and the division result is sorted in the spatial dimension according to the spatial assembly sequence of the assembly simulation or the design digital model structure;

[0129] According to the assembly process flow, the centralized work requirement, and the fine division requirement, the process procedure templates involved in each group of materials are sorted in the time dimension;

[0130] According to the single-process procedure workload requirement in the actual assembly process flow, the process procedure is split and merged;

[0131] According to the time dimension and the spatial dimension assembly sequence of the assembly scene, all the process procedures are planned and sorted, and the number and name of the process procedure nodes are planned according to the coding principle and the naming principle.

[0132] Specifically, process procedure node planning from the spatial dimension of the assembly scene involves planning the spatial assembly sequence of the assembly scene based on the actual assembly process flow, and dividing the aircraft parts to be assembled into a granularity of "a group of parts that can be assembled independently at one time";

[0133] Planning process procedure nodes from the time dimension of assembly scenarios means planning the time assembly sequence of assembly scenarios according to the assembly production rhythm requirements, and dividing the "a group of zero-standard parts and materials that can be assembled independently at one time" into the granular form of multiple process procedure templates with different functions, from material delivery positioning to hole making and connection.

[0134] by Figure 3 For example, a body to be assembled contains 32 components. Based on the assembly process simulation results and the assembly structure, the entire assembly structure is divided into multiple parts. Based on the assembly production rhythm requirements, multiple serial or parallel steps are planned to complete the assembly process of the entire assembly. If it is divided into 6 parts, 6 steps need to be planned, each step completing the assembly of one part. This corresponds to planning 6 "sets of standard parts that can be assembled independently at one time" to complete the material planning of the spatial dimension of the process specification node. Then, based on the serial and parallel order of each step, the sequence planning of the spatial dimension of the process specification node is completed.

[0135] The "a group of standard parts that can be assembled independently at one time" in each step is allocated 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, completing the material planning of the time dimension of the process specification nodes; and then completing the sequence planning of the time dimension of the process specification nodes according to the process flow sequence of positioning, cold extrusion, hole making, connection, inspection and other links.

[0136] In an optional implementation of this embodiment, based on the process specification template, process specification node planning results, process specification material planning results, and process parameter library, accurate matching of process contents in the process specification template is achieved, process specification documentation is compiled, and ultimately, detailed process design for aircraft component assembly is completed;

[0137] Specifically, refer to Figure 4 , according to the assembly process plan and production mode, determine the assembly process flow, combine with the standard process library to form an assembly process specification template; based on the results of digital model analysis, complete the process specification nodes and material planning in the spatial and temporal dimensions of 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 process parameters under the specified process and the full process process parameters in the process of process specification compilation;

[0138] Each process parameter is obtained by searching the relevant process parameter library and logical matching and reasoning judgment. In the process of process procedure compilation, the process procedure content is decomposed into each process procedure template and each process parameter, and each process parameter is judged whether it is a process parameter under the specified process or a process parameter applicable to the whole process. After the process parameters under the specified process are calculated one by one, the process parameters applicable to the whole process are uniformly calculated and pushed to each template and each process. The calculation results of the process parameters are put into the corresponding process parameter positions to form a plurality of process procedure documents that can completely express the assembly information in the whole component assembly process flow.

[0139] Embodiment 3

[0140] This embodiment is further optimized on the basis of embodiment 2. When compiling the aircraft component assembly connection process procedure document, according to the process knowledge and process rules, the method for establishing the process parameter library includes:

[0141] According to the data retrieval scheme, data source and logical rules of the process parameters used in the aircraft component assembly process flow, the data form of the multi-dimensional input / output of the assembly connection process parameter library is constructed;

[0142] According to the assembly connection process experience and assembly connection process requirements of the aircraft component assembly connection flow, the assembly connection process knowledge and assembly connection process rules are generated;

[0143] According to the key fields in the assembly connection process parameter library, the data tables in the assembly connection process parameter library are associated to construct the data association relationship between the assembly connection process parameter libraries;

[0144] According to the data association relationship between the assembly connection process parameter libraries, the data form, the assembly connection process knowledge and the assembly connection process rules, the process parameter library including the assembly connection process parameter library and the assembly connection general process parameter library is established;

[0145] A parameter acquisition mode for unified pushing data is constructed for the assembly connection process parameter library, and a parameter acquisition mode for active data retrieval is constructed for the assembly connection general process parameter library;

[0146] By using this embodiment, the efficiency and accuracy of compiling the aircraft component assembly connection process procedure document can be further improved.

[0147] In an alternative embodiment of the present embodiment, according to the process experience and process requirements of the aircraft component assembly connection process, induction and reasoning are performed to form process knowledge and process rules. In order to reduce the redundancy of data and increase the coherence between data, nine connection process parameter libraries are constructed, including six process parameter libraries and three general process parameter libraries. The six process parameter libraries are material library, standard part library, recycled standard part type library, fixed force tool library, connection part hole diameter library and bonding support plate quality inspection library. The three general process parameter libraries are standard operation procedure library, certificate information library and set inspection type library.

[0148] For the active retrieval data mode in the present embodiment, the process parameters are related to the process procedure template and the assembly process flow. The acquisition logic rules of the process parameters are different for different assembly process flows. According to the process procedure template and the corresponding process, the information of the process parameter library is actively retrieved through the replacement symbol in the template, and the obtained parameter results are put into the replacement symbol position of the process parameter through logical matching and reasoning judgment between the process parameter libraries, for example:

[0149] Material library {input: standard part drawing number; output: connection part sandwich part, sandwich part material brand, connection part quantity, hole making area type};

[0150] Standard part library {input: standard part drawing number; output: drawing number feature, drawing number diameter feature, strength characteristic};

[0151] Recycled standard part type library {input: drawing number feature; output: recycling content};

[0152] Connection part hole diameter library {input: drawing number diameter feature; output: drawing number diameter code};

[0153] Fixed force tool library {input: standard part drawing number, strength characteristic, drawing number diameter code; output: fixed force tool drawing number, fixed force requirement};

[0154] Bonding support plate quality inspection library {input: drawing number diameter feature, drawing number diameter code; output: inspection requirement}.

[0155] For the unified push data mode in the present embodiment, in order to avoid repeated retrieval of process parameters during process procedure compilation, a set of parameter libraries and matching logic rules are uniformly established. According to the process procedure template and the corresponding process, the process parameter library uniformly pushes the general process parameter information to the process, and puts it into the corresponding parameter position of the process, for example:

[0156] Standard operation procedure library {input: process procedure template name, process name, drawing number feature…; output: standard operation procedure number, standard operation procedure name};

[0157] Certificate information base {input: process procedure template name, process name, drawing number feature…; output: certificate code};

[0158] Inspection type base {input: process procedure template name, process name, drawing number feature…; output: inspection type}.

[0159] For the above two parameter acquisition modes, according to the structure form of the hole making process parameter base and the designed input / output function mode, the association relationship between the part assembly hole making process parameters and the eight hole making process parameter bases is established.

[0160] In the embodiment, according to the assembly process flow and the standard process base, the method for establishing the process procedure template corresponding to the assembly scene comprises:

[0161] Defining the aircraft part assembly elements that affect the assembly process flow of the aircraft part assembly connection;

[0162] Establishing the association relationship between the aircraft part assembly elements and the assembly process flow of the aircraft part assembly connection and constructing the assembly process flow of the aircraft part assembly connection;

[0163] According to the assembly process flow of the aircraft part assembly connection and the standard process base, the process procedure template corresponding to the assembly scene is established.

[0164] Specifically, whether the connecting piece is a double-thread bolt, whether the connecting piece is a rivet, whether the connecting piece is a bonded backing nut / screw, whether the connecting piece is a bolt / screw, whether the connecting piece is a constant force type high lock, whether the connecting piece is a nut cap type high lock, and whether the connecting piece is a pull bolt, these seven part assembly elements affect the assembly process flow of the part assembly connection, and the assembly process flow is constructed, and the detailed process is as follows:

[0165] The association relationship between whether the connecting piece is a double-thread bolt and the assembly process flow of the part assembly connection is established, and the connection assembly process flow of the connecting piece as a double-thread bolt is designed; the connection of the double-thread bolt standard part is completed after the hole making and counterboring, etc. According to the design model, a bushing is first installed on the counterbored part, then a backing nut for double-thread bolt is riveted on another laminated part, and finally all laminated parts are installed and fixed through the double-thread bolt to complete all the work of double-thread bolt connection.

[0166] The association relationship between whether the connecting piece is a rivet and the assembly process flow of the part assembly connection is established, and the connection assembly process flow of the connecting piece as a rivet is designed; the connection of the rivet is completed after the hole making and counterboring, etc. According to the design model, all laminated parts are riveted and fixed through the rivet to complete all the work of rivet connection.

[0167] Establish the correlation between whether the connecting piece is a bonded backing plate nut / screw and the component assembly connection assembly process, and design the connecting piece as a bonded backing plate nut / screw connection assembly process; the connection of the bonded backing plate nut / screw is completed after the hole making and counterbore hole making and other hole making work is completed, the position of the connecting piece and the framework is polished, cleaned, and pasted according to the design model, and after the pasting is completed, the excess polishing area before pasting is protected against corrosion, i.e. the connection work of the bonded backing plate nut / screw is completed.

[0168] Establish the correlation between whether the connecting piece is a bolt / screw and the component assembly connection assembly process, and design the connecting piece as a bolt / screw connection assembly process; the connection of the bolt / screw is completed after the hole making and counterbore hole making and other hole making work is completed, all laminated parts are screwed and fixed through the bolt or screw according to the design model, and all the work of the bolt / screw connection is completed.

[0169] Establish the correlation between whether the connecting piece is a high lock of the constant force type and the component assembly connection assembly process, and design the connecting piece as a high lock of the constant force type connection assembly process; the connection of the high lock of the constant force type is completed after the hole making and counterbore hole making and other hole making work is completed, the installation tools such as the constant force wrench are first checked, and after the check is passed, all laminated parts are installed and fixed through the high lock bolt and high lock nut according to the design model, and all the work of the high lock of the constant force type connection is completed.

[0170] Establish the correlation between whether the connecting piece is a high lock of the nut broken cap type and the component assembly connection assembly process, and design the connecting piece as a high lock of the nut broken cap type connection assembly process; the connection of the high lock of the nut broken cap type is completed after the hole making and counterbore hole making and other hole making work is completed, all laminated parts are installed and fixed through the high lock bolt and high lock nut according to the design model, and after the installation is completed, the head of the high lock nut is separated and broken from the main body part of the nut, and after all the work of the high lock of the constant force type connection is completed, the high lock nut broken cap needs to be recycled and checked.

[0171] Establish the correlation between whether the connecting piece is a draw bolt and the component assembly connection assembly process, and design the connecting piece as a draw bolt connection assembly process; the connection of the draw bolt, like the connection of the high lock of the nut broken cap type, also needs to recycle and check the draw bolt broken cap after installation.

[0172] Comprehensive all the above connection processes, set the initial cleaning, gluing, and final excess inspection and inspection processes as public default processes, and finally form a complete component assembly connection process specification template to build a complete component assembly connection assembly process.

[0173] In the embodiment, after establishing the process procedure template corresponding to the assembly scene, the judgment logic of the assembly process flow assembly elements affecting the aircraft component assembly connection is constructed according to the assembly connection process parameter library;

[0174] Specifically, according to the aircraft component assembly design requirements and process requirements, whether the connecting piece is double-line bolt, whether the connecting piece is rivet, whether the connecting piece is adhesive backing nut / screw, whether the connecting piece is bolt / screw, whether the connecting piece is high lock of fixed force type, whether the connecting piece is high lock of nut broken cap type, and whether the connecting piece is bolt, seven component assembly elements affecting the whole component assembly connection assembly process flow are defined.

[0175] The key conditions affecting the process procedure template process 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 part library. In addition, for the special types of high locks, the fixed force type high lock and the nut broken cap type high lock can be distinguished through the recycling standard part type library.

[0176] In the embodiment, the method for preparing the process procedure document representing the detailed process of the aircraft component assembly according to the process procedure template, the process procedure material planning result, the process procedure node planning result and the process parameter library includes:

[0177] Defining the parameter types of the assembly connection process parameters;

[0178] According to the materials in the material library involved in the actual aircraft component assembly connection process flow, the parameter correlation relationship between the assembly connection process parameters is established, and the acquisition logic of the assembly connection process parameters is constructed;

[0179] According to the acquisition logic, the assembly connection process parameters of the specified parameter type are obtained from the process parameter library;

[0180] According to the process procedure template, the process procedure material planning result, the process procedure node planning result and the assembly connection process parameters, the aircraft component assembly connection process procedure document is obtained.

[0181] Specifically, first, the component assembly connection process parameter types are defined. A large number of process parameters are used in the aircraft component assembly connection flow, which will involve different connecting piece types, different assembly requirements, corresponding different standard connecting piece safety requirements, recycling inspection requirements, installation fixed force requirements, fixed force tools, and adhesive backing / screw torque inspection requirements, etc.

[0182] Secondly, according to the materials in the material library involved in the actual aircraft component assembly connection process flow, the association between the process parameters is established, and the acquisition logic of the component assembly connection process parameters is constructed; for example, an example of acquiring the component assembly connection process parameters, according to the data association relationship between the process parameter libraries, the association relationship between the process parameter libraries is classified to form one-to-one, one-to-many, and many-to-one correspondence between the parameter libraries, and single parameter matching and multi-parameter matching relationship between the parameters. Through the parameter association relationship between the databases, the reasoning rules are formed, and according to the materials in the material library involved in the actual aircraft component assembly connection flow, the above-mentioned six relationship process parameter libraries are searched according to the rules to acquire the connection process parameters, and the process procedure template name, process name, standard operation procedure library, certificate information library, and inspection type library are unified in the process parameters and process attribute information in the process procedure template;

[0183] Finally, on the basis of the designed component assembly connection process procedure template, the component assembly connection process parameters actively searched or uniformly pushed are put into the process parameters and process attribute information according to the process procedure template requirement form, and combined with the process procedure material planning result and the process procedure node planning result obtained according to the space and time sequence planning, the aircraft assembly connection process procedure can be compiled.

[0184] In summary, by using the embodiment, the component assembly connection process procedure template and the component assembly connection process parameter library are designed according to the assembly connection assembly process flow, process experience and process requirements, the assembly connection process parameters of the actual aircraft component assembly connection flow are determined, and after the aircraft component assembly model information is acquired in the application software, the corresponding different standard part connection safety requirements, recycling inspection requirements, installation force requirements, force tool, and adhesive backing / screw torque inspection requirements, and general process parameters are quickly called in to complete the compilation of the aircraft assembly connection process procedure. Through systematic and intelligent means, the efficiency and quality of the component assembly connection process design are effectively improved.

[0185] Embodiment 4:

[0186] The embodiment is further optimized on the basis of the above-mentioned embodiments 2 or 3. In the embodiment, when the assembly scene is a skeleton structure assembly, the skeleton parts in the model information are classified.

[0187] Further, when the assembly scene is a skeleton structure assembly, the method for classifying the skeleton parts in the model information includes:

[0188] Step S101, constructing a skeleton part set, specifically constructing a skeleton part rule library, denoted as rule=(frame, beam…), based on MBD model data, identifying skeleton parts, and forming a skeleton part set , ;

[0189] Step S102: Set the skeleton parts assembly threshold and distance threshold. Specifically, the skeleton parts assembly threshold is recorded as smx , that is, the number of parts assembled each time cannot exceed smx The skeleton part distance threshold is recorded as kmx , that is, the distance between parts cannot exceed kmx ;

[0190] Step S103: Based on the MBD digital model, the digital model coordinates are analyzed to calculate the centroid coordinates of each skeleton part. Specifically, the coordinates of the centroid of each skeleton part are calculated according to the coordinates in step S101. parts , extract the coordinates of each skeleton part as ;

[0191] Step S104: Random selection k The center of mass of the skeleton parts forms k Clusters, specifically randomly selected k Skeleton centroid ,form k clusters;

[0192] Step S105, calculate the i The distance from the skeleton part to the cluster , get the minimum distance dmin i ,like , , put the skeleton part into the cluster part subset cparts i Among them, s i For the i The coordinates of the center of mass of the skeleton parts, k i For the i The centroid coordinates of the clusters, , j A subset of cluster parts cparts i Repeat the above steps to form the number of skeleton parts k A subset of cluster parts;

[0193] Step S106: The centroid coordinates of each cluster part subset are expressed as ;

[0194] Step S107: Calculate the silhouette coefficient, specifically based on Calculate the silhouette coefficient, where a(i) yes cparts i In ian average distance of the i-th skeleton part to all skeleton parts in the nearest neighbor cluster part subset; b(i) is the i-th i an average distance of the i-th skeleton part to all skeleton parts in the nearest neighbor cluster part subset;

[0195] If , the i-th cluster part subset i is obtained cparts i The skeleton part with the maximum distance in the i-th cluster part subset is obtained, the minimum distance from the skeleton part with the maximum distance to other cluster part subsets is calculated using the Euclidean distance, and the skeleton part with the maximum distance is assigned to the cluster corresponding to the minimum distance.

[0196] In step S108, the centroid coordinates of the cluster part subset after reassignment are recalculated, and the contour coefficient is calculated until the contour coefficient is greater than the preset value, and the classification of the skeleton parts is completed.

[0197] By constraining the number of part assemblies, the assembly efficiency is effectively controlled; by setting the threshold value between parts, it is ensured that there is an assembly relationship between parts; by using the contour coefficient, the irrationality of clustering is avoided; the technical problem of solving the problem of unclear and non-uniform grouping of skeleton parts is solved, and the efficiency of aircraft process design is effectively improved.

[0198] Embodiment 5

[0199] This embodiment is further optimized on the basis of the above-mentioned embodiments 2 to 4. In this embodiment, when the assembly scene is a skeleton structure assembly, after obtaining the digital mockup information of the skeleton structure assembly, first, a process procedure template corresponding to the skeleton structure assembly is established according to the part type, assembly process flow and standard process library;

[0200] Then, when the digital mockup information is parsed, the target skeleton part is also subjected to part type identification, interference identification and connector identification, and the parsing result also includes the part type identification result, the interference identification result and the connector identification result, so as to match the target skeleton part process procedure template for the target skeleton part according to the part type identification result, remove the skeleton parts causing interference from the assembly skeleton part set composed of the target skeleton part according to the interference identification result, and obtain the skeleton connector set corresponding to the target skeleton part according to the connector identification result;

[0201] Finally, the process procedure document is prepared according to the target skeleton part process procedure template, the assembly skeleton part set, the skeleton connector set, the process procedure material planning result, the process procedure node planning result and the process parameter library, and the process procedure document representing the detailed process of the aircraft skeleton assembly is obtained.

[0202] Further, after obtaining the numerical model information of the skeleton structure assembly, first, the part point coordinates of each part of the aircraft are extracted, an aircraft structure part type library is constructed, a process procedure template corresponding to the skeleton structure assembly is established according to the part type, assembly process flow and standard process library in the aircraft structure part type library; a target skeleton part is determined, the numerical model initial coordinates of the target skeleton part are extracted according to the numerical model information, the assembly skeleton part set is obtained, and the direction vector and movement step of the target skeleton part assembly are set;

[0203] Then, the assembly skeleton part set is traversed, the part type of the target skeleton part is identified according to the part type in the aircraft structure part type library, and a part type identification result is obtained; the assembly path is checked according to the coordinates, direction vector and movement step of the target skeleton part, an interference identification result is obtained, and the skeleton parts that will interfere are removed from the target skeleton parts; the connecting pieces connected by the skeleton parts are identified according to the assembly skeleton part set, a connecting piece identification result is obtained, and a skeleton connecting piece set is obtained according to the connecting piece identification result; the corresponding target skeleton part process procedure template is matched for the assembly skeleton part set according to the part type identification result;

[0204] Finally, the assembly skeleton part set, the skeleton connecting piece set and the target skeleton part process procedure template are used to construct a large language model prompt word, and the process procedure document is prepared according to the process procedure material planning result, the process procedure node planning result, the process parameter library and the large language model prompt word, and a process procedure document representing the detailed process of the aircraft skeleton assembly is obtained.

[0205] Specifically, in an optional embodiment, the process of preparing the aircraft skeleton assembly process procedure document includes the following steps:

[0206] Step S201, the part point coordinates of each part of the aircraft are extracted, an aircraft structure part type library is constructed, and a process procedure template corresponding to the skeleton structure assembly is established according to the part type, assembly process flow and standard process library in the aircraft structure part type library. Specifically, according to the MBD numerical model information, the part point coordinates of each part of the aircraft are extracted and the aircraft structure part type library is constructed according to the part type, and the point cloud coordinates of the parts , and the radius coordinates , , the process procedure template is constructed according to the part type, assembly process flow and standard process library, denoted as , , seq , the process procedure template corresponds to the process, denoted as , , pra , the process corresponds to the parameter name , , con represents the parameter content corresponding to the parameter name;

[0207] Step S202, determine the target skeleton part, extract the initial coordinate of the target skeleton part according to the digital model information, obtain the assembly skeleton part set, and set the direction vector and moving step of the target skeleton part assembly. Specifically, the skeleton part to be assembled is determined, denoted as , , the assembly relationship between parts is obtained, denoted as , wherein r i represents the connection relationship between the first m part and the first n part, and the initial coordinate of the digital model is extracted , , wherein p i represents the starting coordinate of the first i skeleton, and the normal vector coordinate of the part is obtained , , the part p i coordinate is translated in the direction of the normal vector v i to step , wherein is a random step, and the part direction vector ;

[0208] Step S203, traverse the assembly skeleton part set, identify the part type of the target skeleton part according to the part type in the aircraft structure part type library, obtain the part type identification result, traverse the assembly skeleton part set, identify the part type of the target skeleton part according to the part type in the aircraft structure part type library, obtain the part type identification result, and specifically traverse the skeleton part set ske , the classification of parts is realized by using image recognition technology, denoted as f i , , wherein f i represents the category of the first i part;

[0209] Image recognition specifically includes data collection, labeling of historical design digital model part images, part his ={( part his1 , triangular part)……( part hisi ​, square parts), and each part is labeled (triangle parts, square parts); preprocessing, converting historical images into grayscale images, scaling to a 64x64 pixel matrix, and normalizing the matrix; training, selecting a convolutional neural network (CNN), training the model using the labeled data set, and obtaining the model f model ; the skeleton parts ske are classified using the trained model f model , and the classification results are obtained f i , ;

[0210] Step S204, according to the skeleton part starting coordinates p i , move by a step size in the direction of p j , and calculate the distance between the first i part and all parts . If , it indicates that there is interference and the assembly is unreasonable, and the part is removed from the skeleton part set, and step S203 is continued, where rs i , rs j , respectively, represent the radius of the first i part and the first j part;

[0211] Step S205, according to , identify the connecting parts connected to the skeleton parts to form a skeleton connecting part set ;

[0212] Step S206, according to the part type identification result of step S203 f i , match the process procedure template m i ;

[0213] Step S207, according to the assembly skeleton part set, the skeleton connecting part set, and the target skeleton part process procedure template, construct a large language model prompt word, according to the process procedure material planning result, the process procedure node planning result, the process parameter library, and the large language model prompt word, carry out process procedure document preparation, and obtain a process procedure document representing the detailed process of the aircraft skeleton assembly;

[0214] The positioning part prompt word format can adopt the form of fixed sentence + process specification template process content + parts to be assembled, connection relationship set, such as: "please replace the content of

part

connector

part

[0215] By constructing the aircraft structure part type library, the number of model recognition time is reduced, and the number of model recognition efficiency is improved; by the interference method, the part cluster division time is reduced, and the process design difficulty is reduced; by constructing the large language model prompt word, the process specification preparation time is reduced, and the process specification preparation efficiency is improved.

[0216] Embodiment 6

[0217] The embodiment is further optimized on the basis of the above-mentioned embodiment 2, embodiment 3, embodiment 4 or embodiment 5. In this embodiment, when the assembly scene is a skeleton structure assembly, before establishing the process specification template corresponding to the assembly scene according to the assembly process flow and the standard process library, it further includes: splitting the skeleton process specification process step to complete the generation and sorting of the skeleton process specification process.

[0218] Further, the method of splitting the skeleton process specification process step to complete the generation and sorting of the skeleton process specification process includes:

[0219] Firstly, according to the number model information of the skeleton structure assembly, the parts to be assembled are determined and the pile parts set is constructed, and the order of the pile and the order of the parts to be assembled in the pile are marked; then, the number model information is analyzed to obtain the number model connection relationship between the parts to be assembled and the parts to be assembled, and the intra-pile connection relationship between the parts in the pile and the inter-pile connection relationship between the parts in the pile are obtained according to the number model connection relationship; then, according to the intra-pile connection relationship and the inter-pile connection relationship, the rough process is generated and the rough process is split into fine process according to the connection piece type set; finally, according to the connection piece type set, the sorting field set is constructed, and the rough process and the fine process are sorted according to the sorting field set to obtain the skeleton process specification process set.

[0220] Specifically, the following steps are included:

[0221] Step S401, selecting the parts to be assembled of the aircraft to form a pile part set, denoted as d ;

[0222] Step S402, analyzing the MBD number model parts and part coordinates, the parts are denoted as , ; the coordinates are denoted as , ;

[0223] the firstk The order of the pile is , , The coordinate average value of the part is denoted as The minimum value of the coordinate average value of all parts in the pile is denoted as

[0224] Step S403, according to the coordinates in step S402, the order of the parts in the pile is calculated and denoted as , wherein dsort i The order of the nth part in the pile is denoted as i

[0225] Step S404, parse the MBD model, build the part relationship set, denoted as wherein, r n The relationship of the nth part is denoted as

[0226] Step S405, based on step S404, identify the relationship between the parts in the material pile, that is, calculate part i and part j The relationship set between the parts and the parts is built, that is, the connection set in the pile, denoted as , , ra n The connection relationship of the nth part is denoted as, including the part and the connection; the order of the connection in the pile is calculated and denoted as wherein , , ras i The order of the nth connection is denoted as, that is, the order of the nth connection corresponds to the order of the nth part; i i i

[0227] Step S406, based on step S404, identify the relationship between the parts in the material pile, that is, calculate part k and part l The relationship set between the parts and the parts is built, that is, the connection set between the piles, denoted as , , rb n The connection relationship of the nth part is denoted as, including the part and the connection; the order of the connection between the piles is calculated and denoted as wherein , , rbs ​​​​i indicates the first i the order of the connecting pieces;

[0228] Step S407, according to the connecting piece set ra and the connecting piece order ras , the connecting piece set ra is grouped according to the order to form a group, denoted as ras , , , n is the number of rough processes between the internal parts of the split stack;

[0229] Step S408, according to the connecting piece set rb and the connecting piece order rbs , the connecting piece set rb is grouped according to the order to form a group, denoted as rbs , , , m is the number of rough processes of the parts between the split stacks;

[0230] Step S409, construct the connecting piece type set, denoted as c =(rivet, screw, draw bolt, bolt…), according to steps S407 and S408, there are m+n rough processes in total, according to g and gb and c , they are split into fine processes, and the number of fine processes is denoted as de , de ≥m+n ;

[0231] Step S410, according to the connecting piece set of step S409, construct the sorting field set, denoted as , for a single process, form a work step (i.e. the assembly order of the key process) according to the rule field;

[0232] Step S411, construct the special process procedure process set, denoted as special=(hole making, installation…), according to steps S409 and S410, complete the special process procedure process generation and sorting.

[0233] By using the embodiment, the connecting piece order is determined through the part order, which reduces the time for the process personnel to determine the connecting piece order; by constructing the special process procedure process set, the special process procedure process generation and sorting are completed, which improves the time for process procedure process step splitting and process preparation.

[0234] Embodiment 7

[0235] The embodiment is further optimized on the basis of the above embodiments 1 to 6. In the embodiment, after obtaining the digital model information of the assembly scene, the following steps are further included: constructing an aircraft part model metadata according to the digital model information of the assembly scene, and constructing a knowledge graph network of the aircraft according to the aircraft part model metadata, so as to perform cross-BOM tracing on the aircraft part model metadata by using a depth or breadth traversal algorithm of the knowledge graph when data tracing is required.

[0236] Specifically, in an optional implementation, the data tracing includes the following steps:

[0237] In step S501, a part model metadata paradigm is defined, and a part model metadata is constructed. Specifically, a metadata O{Oid, O1, O2…Oi} is defined, where Oid is the unique identification identity of the metadata, and Oi is a set of a certain type of data of the metadata. To ensure the accuracy of the data, a set Q{Q1, Q2…Qi} is created for a type of data Oi to represent the security check of the data, and Qi represents the ith security mechanism thereof. A set T{T1, T2…Ti} is created for each type of data Oi to represent the integrity check of the data, and Ti represents the ith integrity check mechanism thereof.

[0238] Taking engineering data and manufacturing data as an example, each actual material object of each model is given a unique identification code ID, and its data set includes {engineering data set, manufacturing data set, physical data set, maintenance data set…}, its security mechanism includes {drawing number cannot be empty, name cannot be empty, version of engineering data set cannot be empty, manufacturing unit and manufacturing unit in 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 object is part 1{drawing number 1, parent node part 2, child node part 3, belongs to manufacturing BOM, belongs to engineering BOM…}, part 2{drawing number 2, parent node part 4, child node part 3, belongs to engineering BOM…}, part 3{drawing number 3, parent node part 2, child node part 5, belongs to engineering BOM…}, part 4{drawing number 4, parent node part 6, child node part 5, belongs to engineering BOM…}, part 5{drawing number 5, parent node part 4, belongs to engineering BOM…}, part 6{drawing number 6, child node part 4, belongs to manufacturing BOM…}…part n{drawing number n…}.

[0239] Step S502, based on the knowledge graph, the part model data relationship is constructed, the graph network of the metadata is defined through the node, the attribute of the node, the edge and the attribute of the edge, and the graph network M of the data of the airplane is formed, wherein a single logical relationship can be represented as <Oi, Bi, Oj>, wherein Oi represents the i-th metadata object, Oj represents the j-th metadata object, and Bi represents the i-th relationship between the two metadata, and the graph network M between the two metadata is <Oi, B1, Oj>, <Oi, B2, Oj>…<Oi, Bi, Oj>, taking the engineering data set as the starting point, the relationship graph between all material objects is generated, and based on the graph, the graph content of different links is expanded;

[0240] Step S503, cross-BOM data tracing based on the data link graph, specifically, the full life cycle process of the metadata is traced through the depth or breadth traversal algorithm of the knowledge graph, the full life cycle process data result of the current metadata object is obtained through the name, figure number and other keywords and the depth or breadth traversal search algorithm, and the relevance and influence degree of each node are calculated based on the current part tracing graph through the PageRank algorithm, and the calculation formula is:

[0241] PR(I)=(1-d)+d * sum{j\B_i}\frac{PR(j)}{L(j)}, wherein PR(I) is the PageRank value of node i, d is a damping factor, which is 0.85 here, B_i is a set of all nodes pointing to node i, L(j) is the number of out-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, and each node is assigned an initial PageRank value, which is frac{1}{6}, about 0.1666;

[0242] For the first round of part 1 node, there is a part 2 node pointing to it, so the value of "sum{j\B_i}\frac{PR(j)}{L(j)" is 0.1666, then PR(part 1)=(1-0.85)+0.85*0.1666=0.39161, and the calculation method of the remaining nodes is the same, and the iteration is repeated until the PR(I) value of all nodes changes less than the threshold value, and the threshold value is set to 0.0001, and all nodes are sorted according to the calculated value;

[0243] According to the breadth-first, all nodes of part 1 are found, and the node with the largest PageRank value is taken as the next tracing node, and the depth traversal algorithm is continuously used to compile down until the more node is found, and finally, taking part 1 as the input, the shortest tracing link {part 1, part 2, part 4, part 6} is obtained.

[0244] By constructing the metadata of the data, the security verification mechanism, the integrity verification mechanism, and establishing the relationship between the data, the cross-BOM traceability of the data is realized, and the technical problems that the data is easy to cause mistakes and omissions in the traceability process of the aircraft data and the data traceability is relatively difficult and the artificial dependence is strong are solved.

[0245] Embodiment 8

[0246] An embodiment of an aircraft component assembly detailed process design system comprises:

[0247] A digital model information acquisition module is configured to acquire digital model information of an assembly scene.

[0248] A process procedure template generation module is configured to establish a process procedure template corresponding to the assembly scene according to an assembly process flow and a standard process library.

[0249] A planning module is configured to analyze the digital model information to obtain an analysis result, and to obtain process procedure node planning results and process procedure material planning results in the spatial and temporal dimensions of the assembly scene according to the analysis result.

[0250] A process parameter library generation module is configured to establish a process parameter library according to process knowledge and process rules.

[0251] A process procedure document preparation module is configured to prepare a process procedure document according to the process procedure template, the process procedure material planning results, the process procedure node planning results, and the process parameter library, to obtain a process procedure document representing the detailed process of the assembly of the aircraft component.

[0252] Embodiment 9

[0253] An embodiment of a computer-readable storage medium stores a computer program, which, when executed by a processor, implements the aircraft component assembly detailed process design method of the above-mentioned embodiments 1 to 7.

[0254] The above is only a preferred embodiment of the present application, and does not limit the present application in any form. Any simple modification or equivalent change made according to the technical essence of the present application to the above embodiment falls within the protection scope of the present application.

Claims

1. A detailed process design method for aircraft component assembly, characterized in that: include: S01. Obtain digital model information of the assembly scene; S02. Define the assembly process flow according to the assembly process plan, adjust the assembly process flow according to the production mode, and establish a correspondence between the assembly scenario and the process specification template. Adjust the assembly process flow for each assembly scenario according to the assembly scenario and the standard process library, establish a process specification execution process and a process specification process flow. Based on the correspondence between the assembly scenario and the process specification template, the process specification execution process, and the process specification process flow, establish a process specification template corresponding to the assembly scenario. Analyze the digital model information to obtain the analysis results. Based on the analysis results, obtain the process node planning results and process material planning results in the two dimensions of space and time of the assembly scene; Establish a process parameter library based on process knowledge and process rules; S03. Prepare a process specification document based on the process specification template, process specification material planning results, process specification node planning results, and process parameter library to obtain a process specification document representing a detailed process for assembling aircraft components. In step S02, the steps of establishing 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 flow, and the process specification process flow include: First, determine the information type contained in the process specification, define the generation method of each component information of the process specification according to the information type, and determine the target component; Then, based on the aircraft assembly process, the hierarchical relationship between process specification templates and process specification processes is defined to determine the structural form of the process specification process set and define the corresponding expression method based on the process specification template type of each type of process specification. The classification method of assembly type, process specification template type, and process specification process type is defined, and the corresponding relationship between process specification process type and process specification process set is established to obtain the process parameters of the process specification template. Finally, based on the digital model information of the assembly scene, the identification conditions of the process procedure set are obtained to determine the process sequence. According to the correspondence between the target components, hierarchical relationships, and process procedure types and process procedure sets, the process procedure processes that match the assembly scene are combined according to the process sequence to generate a process procedure template corresponding to the assembly scene.

2. The aircraft component assembly detailed process design method according to claim 1, characterized in that: According to process knowledge and process rules, the methods for establishing a process parameter library include: First, define the assembly requirements involved in the assembly process, and generate process knowledge and process rules based on the assembly requirements; Then, the data association relationship between the process parameter libraries is constructed to obtain the process parameters in the assembly process flow; based on the data association relationship, process knowledge and process rules, the process parameter library is generated; Finally, based on the characteristics of assembly information during the process of process specification compilation, the calculation logic rules of the corresponding process parameter library are defined, and a parameter acquisition mode for unified data push is constructed for the process parameters under the specified process. In addition, a parameter acquisition mode for active data retrieval is constructed for the process parameter library that is common to the entire process.

3. The aircraft component assembly detailed process design method according to claim 2, characterized in that: When compiling aircraft component assembly and connection process specification documents, the methods for establishing a process parameter library based on process knowledge and process rules include: Based on the data retrieval scheme, data sources and logical rules of the process parameters used in the aircraft parts assembly process, a multi-dimensional input / output data format for the assembly connection process parameter library is constructed; Generate assembly connection process knowledge and assembly connection process rules based on assembly connection process experience and assembly connection process requirements of aircraft parts; According to the key fields in the assembly connection process parameter library, the data tables in the assembly connection process parameter library are associated to build the data association relationship between the assembly connection process parameter libraries; According to the data association relationship, data format, assembly connection process knowledge and assembly connection process rules between the assembly connection process parameter libraries, a process parameter library including an assembly connection process parameter library and an assembly connection general process parameter library is established; A parameter acquisition mode for unified push data is constructed for the assembly connection process parameter library, and a parameter acquisition mode for active retrieval data is constructed for the assembly connection general process parameter library.

4. The aircraft component assembly detailed process design method according to claim 1, characterized in that: When compiling aircraft component assembly connection process specification documents, the methods for establishing aircraft component assembly connection process specification templates include: Define the aircraft component assembly factors that affect the aircraft component assembly connection assembly process; Establish the relationship between aircraft component assembly elements and aircraft component assembly connection assembly process and construct the aircraft component assembly connection assembly process; According to the aircraft parts assembly and connection assembly process flow and standard process library, a process procedure template for aircraft parts assembly and connection is established.

5. The aircraft component assembly detailed process design method according to claim 4, characterized in that: When compiling aircraft component assembly and connection process specification documents, the process specification document is compiled based on the process specification template, process specification material planning results, process specification node planning results, and process parameter library. The method for obtaining the process specification document that represents the detailed process of aircraft component assembly includes: Parameter types that define assembly connection process parameters; Based on the materials in the material library involved in the actual aircraft parts assembly and connection process, the parameter association relationship between the assembly and connection process parameters is established, and the assembly and connection process parameter acquisition logic is constructed; According to the acquisition logic, the assembly connection process parameters of the specified parameter type are obtained from the process parameter library; According to the process specification template, process specification material planning results, process specification node planning results and assembly connection process parameters, the aircraft component assembly and connection process specification document is obtained.

6. The aircraft component assembly detailed process design method according to claim 1, characterized in that: Based on the analysis results of the digital model information, the methods for obtaining the process material planning results in the spatial and temporal dimensions of the assembly scene include: Analyze the digital-analog information to obtain analysis results; Based on the parsing results of the materials to be assembled, connectors, and supporting materials for the connectors, the connection relationship between the materials to be assembled and the connectors, as well as the supporting relationship between the connectors and their supporting materials, is obtained to complete the process specification material planning for the assembly sequence of the assembly scene space; Based on the assembly timing and role of materials in different process specification templates in the assembly process, as well as the material distribution and outbound constraints, the materials to be assembled, connectors, and supporting materials for connectors are divided into different process specification templates to complete the process specification material planning of the assembly sequence in the assembly scenario time.

7. The aircraft component assembly detailed process design method according to claim 1, characterized in that: According to the spatial assembly sequence and temporal assembly sequence corresponding to the assembly scene, the process procedure node planning results of the assembly scene in both spatial and temporal dimensions are established, including: Analyze the digital model information of the assembly scene and obtain the analysis results; Based on the design digital model structure in the analysis results, the aircraft parts and materials to be assembled are divided according to the spatial dimensions, and the division results are sorted in the spatial dimensions according to the assembly simulation situation or the spatial assembly sequence of the design digital model structure; According to the assembly process, work centralization requirements, and refined division of labor requirements, the process procedure templates involved in each group of materials are sorted in the time dimension; Split and merge process specifications based on the workload requirements of individual process specifications in the actual assembly process flow; According to the assembly sequence of the time dimension and space dimension of the assembly scene, all process procedures are planned and sorted, and the numbers and names of the process procedure nodes are planned according to the coding principle and naming principle.

8. The aircraft component assembly detailed process design method according to claim 1, characterized in that: Assembly scenarios include skeleton structure assembly, system fixing point assembly, skin cover assembly, system duct harness laying and system duct harness installation.

9. The aircraft component assembly detailed process design method according to claim 8, characterized in that: When the assembly scenario is a skeleton structure assembly, the skeleton parts in the digital model information are classified.

10. The aircraft component assembly detailed process design method according to claim 1, characterized in that: When the assembly scenario is skeleton structure assembly, before establishing the process procedure 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 procedure steps to complete the steps of generating and sorting the skeleton process procedure steps.

11. The aircraft component assembly detailed process design method according to claim 1, characterized in that: It also includes steps for recording and tracing data generated during the process of process procedure planning, including: constructing part model metadata for each part model, defining a paradigm for 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 collection data object for each set, the collection data object including data attribute information of the part model; storing the data generated during the process of process procedure planning in the part model metadata; constructing a graph network of the part model metadata based on the logical relationship between the part model metadata; and using a graph traversal algorithm to trace the full life cycle process data of the part model in the graph network.

12. A detailed process design system for aircraft component assembly, characterized in that: A method for implementing detailed process design of aircraft component assembly according to any one of claims 1 to 11, comprising: A digital-analog information acquisition module, configured to acquire digital-analog information of an assembly scene; A process specification template generation module, which is used to create a process specification template corresponding to the assembly scenario based on the assembly process flow and the standard process library; A planning module is used to analyze the digital model information to obtain analysis results, and based on the analysis results, obtain the process node planning results and process material planning results of the assembly scene in the two dimensions of space and time; A process parameter library generation module, wherein the process parameter library generation module is used to establish a process parameter library based on process knowledge and process rules; A process specification document compilation module is used to compile process specification documents based on process specification templates, process specification material planning results, process specification node planning results and a process parameter library to obtain process specification documents that characterize the detailed process of aircraft component assembly.

13. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the program is executed by a processor, the method for designing a detailed process for assembling an aircraft component according to any one of claims 1 to 11 is implemented.

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