Aircraft component assembly hole making process design method, apparatus, and medium

Abstract

This invention discloses a method, equipment, and medium for designing drilling processes for aircraft component assembly. It establishes a knowledge- and rule-based drilling process parameter library and establishes the correlation between the component assembly drilling process parameters and the drilling process parameter library. It analyzes the impact of each component assembly element on the component assembly drilling process flow, establishes the correlation between component assembly elements and the component assembly drilling process flow, and designs the component assembly drilling process flow. It analyzes the conditions of component assembly elements and constructs judgment logics for each component assembly element that affects the component assembly drilling process flow. Based on the component assembly drilling process flow and the analytical information of the aircraft component assembly digital model, it obtains the drilling process parameters and performs the process design for drilling in aircraft component assembly. This invention can quickly obtain relevant process parameters such as drilling diameter and drilling tooling, realizing the process design for drilling in aircraft component assembly.

Description

Technical Field

[0001] This invention belongs to the field of process document preparation technology, and specifically relates to a method, equipment and medium for designing drilling processes for aircraft component assembly. Background Technology

[0002] Aircraft component assembly is an intermediate step between parts manufacturing and overall assembly. It involves drilling holes in the parts to be connected, inserting rivets, rivets, bolts, screws, and other connectors into these holes, and using nuts and washers for installation. This achieves the connection and fixation of multiple layers of materials, completing the assembly and connection of aircraft frame structures, system fixing points, and external components. Drilling holes in aircraft component assembly is the first important step, involving operations such as hole drilling, cold extrusion, non-destructive testing, countersinking, and inspection.

[0003] With the development of computer technology, the deep integration of information technology and assembly process design technology has become an urgent need. It requires the digitalization of product information transmission and the speed and accuracy of process design.

[0004] Currently, in process design research, knowledge engineering mainly focuses on the study of advanced technologies and platforms, without in-depth exploration of process technology knowledge, thus failing to meet the requirements of engineering practice. Automated hole-making process design technology primarily targets digital hole-making path planning and is not integrated with assembly process flows; 3D CAPP technology, including preliminary database design, also lacks engineering application methods and cannot provide accurate process and information guidance in the hole-making process of aircraft component assembly. Summary of the Invention

[0005] The purpose of this invention is to provide a method for designing drilling processes for aircraft component assembly, so as to solve the problem of low intelligence in the design of drilling processes for aircraft component assembly.

[0006] This invention is achieved through the following technical solution:

[0007] The design method for drilling processes in aircraft component assembly includes the following steps:

[0008] S01. Define the component assembly elements that affect the component assembly hole drilling process;

[0009] S02. Construct the data format of the hole-making process parameter library, establish a hole-making process parameter library based on knowledge and rules, and establish the association between the hole-making process parameters of component assembly and the hole-making process parameter library;

[0010] S03. Analyze the impact of component assembly elements on the component assembly hole-making process, establish the correlation between component assembly elements and component assembly hole-making process, and design the component assembly hole-making process.

[0011] S04. Based on the hole-making process parameter library, analyze the component assembly elements that affect the component assembly hole-making process flow under the condition that the component assembly element conditions are met.

[0012] S05. Based on the correlation between the component assembly hole-making process parameters and the hole-making process parameter library, and the judgment logic of the component assembly elements that affect the component assembly hole-making process flow, obtain the acquisition logic of the hole-making process parameters; based on the component assembly hole-making process flow and the analysis information of the aircraft component assembly digital model, obtain the hole-making process parameters and carry out the process design of aircraft component assembly hole-making.

[0013] In some embodiments of the present invention, the component assembly factors that affect the component assembly hole-making process include whether the hole-making type is cold extrusion hole-making, whether the connector is a double-line bolt, whether the sandwich part material is a composite material, and whether the connector needs to be countersunk.

[0014] In some embodiments of the present invention, the established hole-making process parameter library includes a material library, a standard parts library, a main material database, a hole-making type library, a connector hole diameter library, a hole-making tool library, and a cold extrusion parameter library.

[0015] In some embodiments of the present invention, the input / output data format of the hole-making process parameter library is as follows:

[0016] Material library {Input: Connector drawing number, connector name, interlayer part material grade; Output: Connector drawing number, interlayer part material grade};

[0017] Standard parts library {Input: connector drawing number; Output: connector drawing number feature, connector type};

[0018] Material Master Database {Input: Material grade of sandwich component; Output: Material type of sandwich component};

[0019] Hole type library {Input: Connector type, sandwich part material type; Output: Hole type};

[0020] Connector hole diameter library {Input: Connector drawing number feature, hole type; Output: Connector drawing number feature, cold extrusion hole diameter code};

[0021] Hole-making tool library {Input: Material type of sandwich part, drawing number and characteristics of connector; Output: Hole-making tool, hole diameter inspection tool}.

[0022] In some embodiments of the present invention, in step S02, the association between the component assembly drilling process parameters and the seven drilling process parameter libraries is established according to the structural form of the drilling process parameter library and the input / output data form.

[0023] In some embodiments of the present invention, step S04 involves constructing judgment logic for component assembly elements that affect the component assembly hole-making process; including:

[0024] The logic for determining whether the constructed hole type is cold extrusion hole making is as follows: obtain the material grade of the sandwich part and the drawing number of the connector from the material library; obtain the material type of the sandwich part from the main material database based on the material grade of the sandwich part; output the connector type from the standard parts library based on the connector drawing number; obtain the hole type from the hole type library based on the material type of the sandwich part and the connector type; and determine whether to perform cold extrusion hole making based on the hole type.

[0025] The logic for determining whether a connector is a double-wire bolt is as follows: based on the connector drawing number obtained from the material library, the connector type is obtained from the standard parts library, and the connector type is used to determine whether the connector is a double-wire bolt.

[0026] The logic for determining whether the material of the sandwich component is a composite material is as follows: based on the material grade of the sandwich component obtained from the material library, the material type is obtained from the main material database, and the sandwich component material is determined to be a composite material based on the material type.

[0027] The logic for determining whether a connector needs countersinking is as follows: based on the connector drawing number obtained from the material library, the connector drawing number feature is obtained from the standard parts library; based on the connector drawing number feature, the countersinking information is obtained from the connector aperture library; and based on the countersinking information, it is determined whether the connector needs countersinking.

[0028] In some embodiments of the present invention, step S05 includes obtaining the logic for acquiring the process parameters of the component assembly hole drilling; including:

[0029] Output the cold extrusion orifice code from the connector orifice library, and obtain the cold extrusion orifice parameters and cold extrusion tool from the cold extrusion parameter library based on the cold extrusion orifice code;

[0030] Based on the hole type, obtain the hole diameter parameters and countersink angle parameters from the connector hole diameter library;

[0031] Based on the hole type and connector drawing number characteristics, retrieve the connector drawing number characteristics from the connector hole diameter library. Based on the connector drawing number characteristics corresponding to the hole type, retrieve the hole-making tool, countersinking tool, and inspection tool from the hole-making tool library.

[0032] In some embodiments of the present invention, in step S05, the assembly hole-making process parameters are obtained and pushed to the process content of the corresponding process specification template to complete the process design for assembling holes of aircraft components.

[0033] On the other hand, the present invention also provides an electronic device, comprising:

[0034] Processor; and,

[0035] Memory for storing the executable instructions of the processor;

[0036] The processor is configured to execute the aircraft component assembly hole-making process design method by executing the executable instructions.

[0037] On the other hand, the present invention also provides a computer-readable storage medium having a computer program stored thereon, wherein the computer program, when executed by a processor, implements the aforementioned method for designing the drilling process for assembling aircraft components.

[0038] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0039] 1) Based on the hole-making process flow and hole-making process parameter library, this invention determines the actual hole-making process flow and hole-making process parameters for aircraft component assembly, realizes the design of the hole-making process flow for component assembly, and after obtaining the aircraft component assembly digital model information in the application, it can quickly obtain relevant process parameters such as hole diameter and hole-making tooling according to the acquisition logic of the component assembly hole-making process parameter library, thus realizing the process design of hole-making for aircraft component assembly.

[0040] 2) This invention defines the component assembly elements that influence the component assembly hole-making process, clarifies which elements affect the process flow, designs a complete component assembly hole-making process flow, and completes the design of a component assembly hole-making process specification template. The component assembly hole-making process specification template includes all necessary process steps and parameters in the component assembly hole-making process, achieving the integration of multi-source heterogeneous data, information, process requirements, design requirements, and process schemes. This provides standardized and structured guidance for component assembly hole-making, enabling the structured and standardized accumulation of component assembly hole-making process experience.

[0041] 3) This invention achieves the accumulation of process knowledge to meet the parameter requirements of the entire process of hole making in component assembly by constructing a knowledge and rule-based component assembly hole making process parameter library.

[0042] 4) This invention establishes the association between hole-making process parameters and process parameter libraries by designing data access logic between process parameter libraries, which can quickly and accurately respond to different process parameter requirements. Attached Figure Description

[0043] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings in the embodiments will be briefly described below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0044] Figure 1 This is a schematic diagram of the process design method for drilling holes in aircraft component assembly according to an embodiment of the present invention.

[0045] Figure 2 This is a diagram showing the data relationship between the assembly hole-making process parameter library for aircraft components in an embodiment of the present invention.

[0046] Figure 3 This is a flowchart illustrating the process of drilling holes for assembling aircraft components according to an embodiment of the present invention.

[0047] Figure 4 This is a logic diagram for determining whether the hole-making type is cold extrusion hole-making in an embodiment of the present invention.

[0048] Figure 5 This is a logic diagram for determining whether a connector is a double-wire bolt in an embodiment of the present invention.

[0049] Figure 6 This is a logic diagram for determining whether the material of the sandwich component is a composite material in an embodiment of the present invention.

[0050] Figure 7 This is a logic diagram for determining whether a connector needs countersinking in an embodiment of the present invention.

[0051] Figure 8 This is a logic diagram for obtaining the process parameters of drilling holes for aircraft component assembly in an embodiment of the present invention. Detailed Implementation

[0052] To make the objectives, technical solutions, and advantages of this application clearer, specific embodiments of this application will be described in further detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are merely for explaining this application and not for limiting it. It should also be noted that, for ease of description, only the parts relevant to this application are shown in the drawings, not all of them. Before discussing exemplary embodiments in more detail, it should be mentioned that some exemplary embodiments are described as processes or methods depicted as flowcharts. Although the flowcharts describe operations (or steps) as sequential processes, many of these operations can be performed in parallel, concurrently, or simultaneously. Furthermore, the order of the operations can be rearranged. The process can be terminated when its operation is completed, but may also have additional steps not included in the drawings. The process can correspond to a method, function, procedure, subroutine, subprogram, etc.

[0053] This invention defines component assembly elements that affect the component assembly hole-making process, constructs judgment logic that affects the component assembly hole-making process, and realizes the design of a complete component assembly hole-making process and a component assembly hole-making process specification template.

[0054] By analyzing the operational requirements of the hole-making process, a logic for obtaining the process parameters of the hole-making process is formulated. Based on the hole-making process parameter library and the analytical information of the assembly CAD model, relevant process parameters such as hole diameter, hole-making tooling, and countersink angle requirements in the assembly hole-making process parameters are quickly obtained, and the process design for hole-making in aircraft component assembly is completed.

[0055] In some embodiments of the present invention, reference is made to Figure 1 The design method for drilling holes in aircraft component assembly includes the following steps:

[0056] S01. Define the component assembly elements that affect the component assembly drilling process.

[0057] Based on the aircraft component assembly design and process requirements, the component assembly elements that affect the component assembly hole-making process are defined, including whether the hole-making type is cold extrusion hole-making, whether the connector is a double-line bolt, whether the sandwich part material is a composite material, and whether the connector needs countersinking.

[0058] S02. Construct a multi-dimensional input / output data format for the hole-making process parameter library, establish a knowledge- and rule-based hole-making process parameter library, and establish the association between the component assembly hole-making process parameters and the hole-making process parameter library.

[0059] S03. Analyze the impact of four component assembly elements on the component assembly hole-making process: whether the hole type is cold extrusion hole-making, whether the connector is a double-line bolt, whether the sandwich part material is a composite material, and whether the connector needs countersinking. Establish the correlation between component assembly elements and component assembly hole-making process, and complete the design of component assembly hole-making process.

[0060] S04. Based on the hole-making process parameter library, analyze the conditions under which the following four situations occur: cold extrusion hole-making type, double-line bolt for connector, composite material for sandwich part, and countersinking required for connector. Construct the judgment logic for component assembly elements that affect the hole-making process flow of component assembly.

[0061] S05. Based on the correlation between the component assembly hole-making process parameters and the hole-making process parameter library, and the judgment logic of the component assembly elements that affect the component assembly hole-making process flow, obtain the acquisition logic of the hole-making process parameters; based on the component assembly hole-making process flow and the analysis information of the aircraft component assembly digital model, obtain the hole-making process parameters and carry out the process design of aircraft component assembly hole-making.

[0062] This invention determines the actual drilling process flow and drilling parameters for aircraft component assembly based on the drilling process flow and drilling process parameter library, and realizes the design of the drilling process flow for component assembly. After obtaining the aircraft component assembly digital model information in the application, it can quickly obtain relevant process parameters such as drilling diameter and drilling tooling, and realize the process design of drilling for aircraft component assembly.

[0063] By defining the component assembly elements that affect the component assembly hole-making process, identifying which elements will affect the component assembly hole-making process, designing a complete component assembly hole-making process flow, and completing the design of the component assembly hole-making process specification template.

[0064] The component assembly hole-making process specification template includes all necessary process steps and procedure parameters in the component assembly hole-making process. It integrates multi-source heterogeneous data, information, process requirements, design requirements, and process schemes, providing standardized and structured guidance for component assembly hole-making and enabling the structured and standardized accumulation of component assembly hole-making process experience.

[0065] By constructing a knowledge- and rule-based parameter library for component assembly hole drilling, we can accumulate process knowledge to meet the parameter requirements of the entire component assembly hole drilling process.

[0066] By designing the data access logic between process parameter libraries, the association between hole-making process parameters and process parameter libraries is established, enabling a rapid and accurate response to different process parameter requirements.

[0067] The following detailed description of the aircraft component assembly hole-making process design method of the present invention, with reference to specific embodiments, provides a detailed explanation.

[0068] Step S01: Define the component assembly elements that affect the component assembly hole drilling process.

[0069] Based on the aircraft component assembly design and process requirements, we define four component assembly elements that affect the entire component assembly hole-making process: whether the hole-making type is cold extrusion hole-making, whether the connector is a double-line bolt, whether the sandwich part material is a composite material, and whether the connector needs countersinking.

[0070] Step S02: Construct a knowledge- and rule-based hole-making process parameter library, and establish the association between the component assembly hole-making process parameters and the hole-making process parameter library, including:

[0071] S021. Construct a knowledge- and rule-based hole-making process parameter library.

[0072] Based on the data retrieval scheme, data source, and logical rules of the process parameters used in the component assembly process, a multi-dimensional input / output data format for constructing a hole-making process parameter library is constructed, represented as follows:

[0073] CLASS1{IN1;OUT1}, CLASS2{IN1,IN2,…INn;OUT1}, CLASS3{IN1;OUT1,OUT2,OUT3,…OUTn}, CLASS4{IN1,IN2, IN3,…INn;OUT1,OUT2,OUT3,…OUTn}.

[0074] Among them, CLASS1 supports unified program recognition of initial data; CLASS2 supports logical reasoning to derive a unique result after multiple condition inputs; CLASS3 supports multi-dimensional definition after data input, and outputs results of different dimensions that can be applied to different scenarios; CLASS4 supports logical reasoning to derive results of different dimensions after multiple condition inputs that can be applied to different scenarios.

[0075] Based on the assembly requirements involved in the hole-making process of component assembly, each assembly requirement is summarized and reasoned to form process knowledge and process rules. In order to reduce data redundancy and increase the coherence between data, seven hole-making process parameter libraries are constructed: material library, standard parts library, main material database, hole-making type library, connector hole diameter library, hole-making tool library, and cold extrusion parameter library.

[0076] in:

[0077] Material library {Input: Connector drawing number, connector name, interlayer part material grade; Output: Connector drawing number, interlayer part material grade}.

[0078] Standard parts library {Input: Connector drawing number; Output: Connector drawing number feature, Connector type}.

[0079] Material Master Database {Input: Material grade of sandwich component; Output: Material type of sandwich component}.

[0080] Hole type library {Input: Connector type, sandwich part material type; Output: Hole type}.

[0081] Connector hole diameter library {Input: Connector drawing number feature, hole type; Output: Connector drawing number feature, cold extrusion hole diameter code}.

[0082] Hole-making tool library {Input: Material type of sandwich part, drawing number and characteristics of connector; Output: Hole-making tool, hole diameter inspection tool}.

[0083] Cold extrusion parameter library {Input: cold extrusion orifice code; Output: initial hole size for cold extrusion, cold extrusion tool}.

[0084] S022. Establish the relationship between the component assembly hole-making process parameters and the hole-making process parameter library.

[0085] Based on the structure of the hole-making process parameter library and the input / output data format of the design, the correlation between the hole-making process parameters of component assembly and the seven hole-making process parameter libraries is established. This allows for the acquisition of process parameters used in the hole-making process design, such as "hole diameter," "hole-making tool," and "cold extrusion initial hole size," etc. Figure 2 As shown.

[0086] Step S03: Establish the relationship between component assembly elements and component assembly drilling process flow, and design the component assembly drilling process flow; including:

[0087] S031. Analyze the impact of the following four component assembly elements on the component assembly hole-making process: whether the hole-making type is cold extrusion hole-making, whether the connector is a double-line bolt, whether the sandwich part material is a composite material, and whether the connector needs countersinking.

[0088] 1) Establish the relationship between "whether the hole type is cold extrusion hole making" and the hole making process of component assembly, and design the cold extrusion hole making process.

[0089] Cold extrusion hole making requires, before ordinary hole making, the initial hole to be made according to the specifications. After the initial hole is inspected and approved, the cold extrusion strengthening operation is carried out, and finally the final hole making operation is completed.

[0090] 2) Establish the relationship between "whether the connector is a double-line bolt" and the component assembly hole-making process, and design the hole-making process for standard double-line bolt parts.

[0091] For drilling holes in standard double-line bolt parts, after the final hole drilling operation is completed in the drilling stacked parts, the drilling stacked parts need to be disassembled, and then the enlargement drilling and countersinking operations for the double-line bolt bushing mounting holes need to be performed separately and sequentially on the stacked parts for installing double-line bolt bushings.

[0092] 3) Establish the relationship between "whether the sandwich part material is a composite material" and the component assembly hole-making process, and design the hole-making process for composite material sandwich parts.

[0093] When the sandwich component is made of composite material, the hole-making performance of the composite material is affected. Therefore, after the final hole-making operation is completed, non-destructive testing needs to be performed on the hole-making area of ​​the composite material component to ensure the connection strength of the composite material.

[0094] 4) Establish the relationship between "whether the connector needs countersinking" and the component assembly hole-making process, and design the hole-making process for countersinking standard parts.

[0095] The shape of the nail head of the connector affects the hole-making process. After the final hole-making operation is completed, the corresponding countersinking operation needs to be performed according to the shape and size of the nail head.

[0096] S032. Design of component assembly hole drilling process

[0097] Based on the three common hole-making processes—hole making, removal of excess material, and hole quality inspection—and considering the influence of the four component assembly elements on the component assembly hole-making process, the design of the component assembly hole-making process is completed, such as... Figure 3 The process flow for drilling holes in component assembly is obtained.

[0098] Step S04: Construct the judgment logic for component assembly elements that affect the component assembly hole drilling process; including:

[0099] 1) Construct the judgment logic for "whether the hole type is cold extrusion hole making".

[0100] Whether the holes in the connectors need to be cold-extruded for strengthening depends on the type of connector, the material type of the sandwich parts, and the type of hole. The judgment logic is as follows: Figure 4 As shown.

[0101] like Figure 4 The system retrieves the material grade of the sandwich part and the drawing number of the connector from the material library. Based on the material grade of the sandwich part, it retrieves the material type of the sandwich part from the main material database. Based on the drawing number of the connector, it outputs the connector type from the standard parts library. Based on the material type of the sandwich part and the connector type, it retrieves the hole type from the hole type library and determines whether to perform cold extrusion hole making based on the hole type.

[0102] 2) Construct the logic for determining whether the connector is a double-bolt.

[0103] By obtaining the drawing number of the connector in the design model, matching the material type in the standard parts library, and obtaining the connector type, it is determined whether the material type is a double-threaded bolt. The determination logic is as follows: Figure 5 As shown.

[0104] like Figure 5 Based on the connector drawing number obtained from the material library, the connector type is obtained from the standard parts library, and the connector type is used to determine whether the connector is a double-line bolt.

[0105] 3) Construct the judgment logic for "whether the material of the sandwich component is a composite material".

[0106] By obtaining the material grade of the sandwich component in the design digital model, and matching the material type in the main material database, it is determined whether composite materials are included. The determination logic is as follows: Figure 6 As shown.

[0107] like Figure 6 Based on the material grade of the sandwich part obtained from the material library, the material type is obtained from the main material database, and the material type is used to determine whether the sandwich part material is a composite material.

[0108] 4) Construct the logic for determining whether the connector needs countersinking.

[0109] By obtaining the drawing number of the connector in the design model, matching the material type in the standard parts library, the connector type is obtained. Then, the countersinking information in the connector bore library is matched to determine whether the connector needs countersinking. The judgment logic is as follows: Figure 7 As shown.

[0110] like Figure 7 Based on the connector drawing number obtained from the material library, the connector drawing number feature is obtained from the standard parts library. Based on the connector drawing number feature, the countersinking information is obtained from the connector bore diameter library. Based on the countersinking information, it is determined whether the connector needs countersinking.

[0111] Step S05: Define the expression form of the component assembly hole-making process parameters, formulate the logic for obtaining the component assembly hole-making process parameters, and obtain the relevant process parameters to complete the process design of aircraft component assembly hole-making; including:

[0112] S051. Define the expression form of the component assembly hole drilling process parameters.

[0113] The drilling process for aircraft component assembly involves numerous process parameters, encompassing different connector types and assembly requirements, each corresponding to different drilling parameters, drilling tools, and inspection tools. Based on the timing and storage location of process parameter requirements within the component assembly drilling process flow, we define the types and expressions of process parameters that meet the process flow requirements.

[0114] The storage location of process parameters refers to the distribution of process parameters in the process design result document. For example, different process parameters exist in the process parameters of different processes.

[0115] For example, the countersink angle parameter appears in the countersink process parameters when the "countersink" process is programmed.

[0116] S052. Develop the logic for obtaining the component assembly hole-making process parameters.

[0117] Based on the data relationships between the hole-making process parameter libraries, the relationships between each library are categorized, forming one-to-one, one-to-many, and many-to-one correspondences, as well as single-parameter matching and multi-parameter matching relationships. The logic for obtaining hole-making process parameters for component assembly is then established. Figure 8 As shown.

[0118] Based on the correlation between component assembly drilling process parameters and the drilling process parameter library, and the judgment logic of component assembly elements affecting the component assembly drilling process, the logic for obtaining component assembly drilling process parameters is derived; including:

[0119] Combination Figure 8 When it is determined that cold extrusion hole making is required, the cold extrusion hole diameter code is output from the connector hole diameter library, and the cold extrusion hole diameter parameters and cold extrusion tools are obtained from the cold extrusion parameter library according to the cold extrusion hole diameter code.

[0120] Based on the hole type, obtain the hole diameter parameters and countersink angle parameters from the connector hole diameter library;

[0121] Based on the hole type and connector drawing number characteristics, retrieve the connector drawing number characteristics from the connector hole diameter library. Based on the connector drawing number characteristics corresponding to the hole type, retrieve the hole-making tool, countersinking tool, and inspection tool from the hole-making tool library.

[0122] By establishing data relationships between the hole-making process parameter libraries, reasoning rules are formed. The seven hole-making process parameter libraries in step S02 above are retrieved according to the rules. Based on the materials in the material library involved in the actual aircraft component assembly hole-making process, relevant process parameters such as hole diameter, hole-making tooling, and countersink angle in the assembly hole-making process parameters are obtained and pushed to the corresponding process specification template to complete the process design for aircraft component assembly hole-making.

[0123] On the other hand, the present invention also provides an electronic device, comprising:

[0124] Processor; and,

[0125] Memory for storing the executable instructions of the processor;

[0126] The processor is configured to execute the aircraft component assembly hole-making process design method by executing the executable instructions.

[0127] On the other hand, the present invention also provides a computer-readable storage medium having a computer program stored thereon, wherein the computer program, when executed by a processor, implements the aforementioned method for designing the drilling process for assembling aircraft components.

[0128] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A method for designing drilling processes for aircraft component assembly, characterized in that, Includes the following steps: S01. Define the component assembly elements that affect the component assembly hole drilling process; The component assembly factors that affect the component assembly hole-making process include whether the hole-making type is cold extrusion hole-making, whether the connector is a double-line bolt, whether the sandwich part is made of composite material, and whether the connector needs countersinking. S02. Construct the data format of the hole-making process parameter library, establish a hole-making process parameter library based on knowledge and rules, and establish the association between the hole-making process parameters of component assembly and the hole-making process parameter library; the established hole-making process parameter library includes a material library, a standard parts library, a main material database, a hole-making type library, a connector hole diameter library, a hole-making tool library, and a cold extrusion parameter library; the input / output data format of the hole-making process parameter library is: Material library {Input: connector drawing number, connector name, sandwich part material grade; Output: Connector drawing number, interlayer part material grade}; Standard parts library { Input: Connector drawing number; Output: Connector drawing number and feature, connector type}; Material master database { Input: Sandwich part material grade; Output: Material type of sandwich part; Hole type library { Input: Connector type, Material type of sandwich part; Output: Hole type}; Connector Hole Diameter Library {Input: Connector drawing number, feature, hole type;} Output: Connector drawing number characteristics, cold extrusion bore diameter code}; Hole making tool library { Input: Sandwich part material type, connector drawing number characteristics; Output: Hole-making tool, hole diameter inspection tool; Cold extrusion parameter library {Input: Cold extrusion hole diameter code; Output: Initial hole dimensions for cold extrusion, cold extrusion tools; S03. Analyze the impact of component assembly elements on the component assembly hole-making process, establish the correlation between component assembly elements and component assembly hole-making process, and design the component assembly hole-making process. S04. Based on the hole-making process parameter library, analyze the component assembly elements that affect the component assembly hole-making process flow under the condition that the component assembly element conditions are met. S05. Based on the relationship between the component assembly hole-making process parameters and the hole-making process parameter library, and the judgment logic of the component assembly elements that affect the component assembly hole-making process, obtain the logic for obtaining the hole-making process parameters. Based on the component assembly hole-making process flow and the analytical information of the aircraft component assembly digital model, the hole-making process parameters are obtained, and the process design for aircraft component assembly hole-making is carried out.

2. The aircraft component assembly hole-making process design method according to claim 1, characterized in that, In step S02, based on the structure of the hole-making process parameter library and the input / output data format, the association between the component assembly hole-making process parameters and the seven hole-making process parameter libraries is established.

3. The aircraft component assembly hole-making process design method according to claim 2, characterized in that, Step S04 involves constructing the judgment logic for component assembly elements that affect the component assembly hole-making process; including: The logic for determining whether the constructed hole type is cold extrusion hole making is as follows: obtain the material grade of the sandwich part and the drawing number of the connector from the material library; obtain the material type of the sandwich part from the main material database based on the material grade of the sandwich part; output the connector type from the standard parts library based on the connector drawing number; obtain the hole type from the hole type library based on the material type of the sandwich part and the connector type; and determine whether to perform cold extrusion hole making based on the hole type. The logic for determining whether a connector is a double-wire bolt is as follows: based on the connector drawing number obtained from the material library, the connector type is obtained from the standard parts library, and the connector type is used to determine whether the connector is a double-wire bolt. The logic for determining whether the material of the sandwich component is a composite material is as follows: based on the material grade of the sandwich component obtained from the material library, the material type is obtained from the main material database, and the sandwich component material is determined to be a composite material based on the material type. The logic for determining whether a connector needs countersinking is as follows: based on the connector drawing number obtained from the material library, the connector drawing number feature is obtained from the standard parts library; based on the connector drawing number feature, the countersinking information is obtained from the connector aperture library; and based on the countersinking information, it is determined whether the connector needs countersinking.

4. The aircraft component assembly hole-making process design method according to claim 3, characterized in that, Step S05 involves obtaining the logic for acquiring the process parameters for hole drilling in component assembly; including: Output the cold extrusion orifice code from the connector orifice library, and obtain the cold extrusion orifice parameters and cold extrusion tool from the cold extrusion parameter library based on the cold extrusion orifice code; Based on the hole type, obtain the hole diameter parameters and countersink angle parameters from the connector hole diameter library; Based on the hole type and connector drawing number characteristics, retrieve the connector drawing number characteristics from the connector hole diameter library. Based on the connector drawing number characteristics corresponding to the hole type, retrieve the hole-making tool, countersinking tool, and inspection tool from the hole-making tool library.

5. The aircraft component assembly hole-making process design method according to claim 4, characterized in that, In step S05, the assembly hole-making process parameters are obtained and pushed to the corresponding process content of the process specification template to complete the process design for assembling holes of aircraft components.

6. An electronic device, characterized in that, include: processor; as well as, Memory for storing the executable instructions of the processor; The processor is configured to execute the aircraft component assembly hole-making process design method according to any one of claims 1-5 by executing the executable instructions.

7. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the aircraft component assembly hole-making process design method as described in any one of claims 1-5.

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