Structural automated modeling method and computer program product at the conceptual stage

Abstract

The present disclosure relates to the field of aero-engine modeling, and proposes a method for automated structural modeling at the scheme stage and a computer program product. The method for automated structural modeling at the scheme stage comprises: step one: obtaining a central structured data file, wherein the central structured data file is used to describe the structure at the scheme stage in a digital manner; step two: creating an automated script, wherein the automated script can parse the central structured data file when running, and interact the data of the structure at the scheme stage obtained by the parsing with the modeling software; step three: calling the modeling software by running the automated script, and outputting a three-dimensional visualization model of the structure at the scheme stage. According to various aspects of the present disclosure, the interaction between the central structured data and the modeling software is realized through the automated script, opening up the digital main line of automated rapid modeling and automated iteration of the structure at the scheme stage.

Description

Technical Field

[0001] The present disclosure relates to the field of aircraft engine modeling, and in particular to a structural automation modeling method and a computer program product at a scheme stage. Background Art

[0002] With the continuous development of digital twin technology and the continuous advancement of the digitalization process, the application demand for digital twins in all walks of life has become more and more urgent, and has crossed the boundaries of aerospace and manufacturing. The aircraft engine is a highly complex system involving multiple disciplines and fields. It is difficult to develop, has a long cycle, high investment, and high risk. The emergence of digital engines has greatly shortened the design cycle, accelerated design efficiency, and reduced design costs. Among them, data fusion and model construction are the core technical elements of digital engines. Realizing rapid modeling and automated iteration is an inevitable trend in the development of digital engines in the design stage, especially for the structural automation modeling technology of the engine in the scheme design stage. Higher requirements are put forward.

[0003] The future development of aero-engines is oriented towards the standardization, intelligence, platformization, and ecologicalization of unified software. The traditional aero-engine structural design based on direct modeling of general software itself can no longer meet the requirements of digital engine development. In order to open up the digital main line and realize rapid modeling, automated iteration, and state data synchronization, the technical realization of structural automated modeling methods has become a possibility.

[0004] The development of digital engine technology is no longer satisfied with data management and control, but requires a software platform that can interact with the central expression data reflecting the logical relationship and dependency relationship of the data and the modeling software. At present, there are literature studies that can use the VB (Visual Basic) programming language to simultaneously perform secondary development of Excel and UG (Unigraphics, a popular computer-aided design (CAD / computer-aided manufacturing (CAM) / computer-aided engineering (CAE) software) to achieve mutual interaction. Although structural parametric modeling can be achieved, the dependency and logical relationship between model elements cannot be established, and the model can only be created and expressed within the software, and the full process of automated modeling cannot be achieved, and scalability to the same field cannot be achieved. Summary of the invention

[0005] In view of this, the present disclosure proposes a structural automation modeling method and computer program product in the scheme stage, which can overcome the shortcomings of the existing technology and meet the needs of digital engine development.

[0006] According to one aspect of the present disclosure, a structural automation modeling method in a scheme stage is provided, comprising:

[0007] Step 1: Obtain a central structured data file, wherein the central structured data file is used to describe the structure of the scheme stage in a digital manner;

[0008] Step 2: creating an automated script, which can parse the central structured data file when running, and interact the structure data of the solution stage obtained by parsing with the modeling software;

[0009] Step 3: By running the automation script, calling the modeling software, and outputting a three-dimensional visual model of the structure in the scheme stage.

[0010] In a possible implementation, for the structural automation modeling method in the scheme stage described in the present invention, the central structured data file is a structural semantic model file of the aircraft engine obtained by digitizing the overall structural information of the aircraft engine through the extensible markup language XML, including: declaration, aircraft engine header information and aircraft engine main model structure.

[0011] In a possible implementation, for the structural automated modeling method in the scheme stage described in the present disclosure, the declaration is used to express the version and encoding format of the structural semantic model file of the aircraft engine, and in the engine header information, common attributes of the structural assembly of the aircraft engine are set, and the common attributes include name, function, author, creation date, and version. The main model structure of the aircraft engine includes: attribute definitions and dependency descriptions for structural assemblies obtained by dividing the main structure of the aircraft engine into N levels according to the hierarchy, where N is an integer greater than 2.

[0012] In a possible implementation, for the structural automation modeling method at the scheme stage described in the present disclosure, the automation script is an exe program file obtained by secondary development of NX modeling software by VC# programming language integration software.

[0013] In one possible implementation, for the structural automation modeling method in the scheme stage described in the present invention, in the step three, the program of the automation script is run through external commands, and the central structured data file is automatically read within the program, and the standardized model library established in the NX modeling software is automatically called to automatically complete the entire process of modeling the structure in the scheme stage.

[0014] In a possible implementation, for the structural automation modeling method at the scheme stage described in the present disclosure, the central structured data file is an XML file, and the secondary development of the NX modeling software includes:

[0015] Establishing a standardized template for aero-engine structural assembly parts in the NX modeling software to form a structural parameterized model library;

[0016] Set global variables, including XML file path;

[0017] Set the exe program file so that when the exe program file is running, it can:

[0018] Based on the global variable, calling the XML file;

[0019] Initializing the operating environment of the NX modeling software;

[0020] Parsing the XML file to extract data required for model creation;

[0021] Model creation is performed based on the extracted data and the structural parameterized model library.

[0022] In a possible implementation, for the structure automatic modeling method in the scheme stage described in the present disclosure, in the step 3, the automatic modeling is realized by calling and executing the exe program and performing the following process:

[0023] Initializing the operating environment of the NX modeling software;

[0024] Parse XML file path;

[0025] Reading an XML file based on the parsed XML file path;

[0026] Parsing the XML file to extract data required for model creation;

[0027] Based on the data extracted from the XML file, start creating the model, including:

[0028] The structural parametric model library established in the NX modeling software is accessed, and based on the data extracted from the XML file, the template in the structural parametric model library is cloned, and the model parameter information of the cloned template is defined to complete the creation of the model.

[0029] According to another aspect of the present disclosure, a computer program product is provided, including a computer-readable code, or a non-volatile computer-readable storage medium carrying the computer-readable code. When the computer-readable code runs in a processor of an electronic device, the processor in the electronic device executes the above method.

[0030] Through automated scripts, the central structured data can interact with the modeling software. According to the structural automation modeling method and computer program product in the scheme stage of various aspects of the present invention, a digital main line for rapid structural automation modeling and automated iteration in the scheme stage is opened up.

[0031] Further features and aspects of the present disclosure will become apparent from the following detailed description of exemplary embodiments with reference to the attached drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate exemplary embodiments, features, and aspects of the disclosure and, together with the description, serve to explain the principles of the disclosure.

[0033] Figure 1 is a flowchart showing a method for automatic structural modeling in a scheme phase according to an embodiment of the present disclosure;

[0034] Figure 2 is a schematic diagram showing a central structured data file used by a structure automation modeling method in a solution phase according to an embodiment of the present disclosure;

[0035] Figure 3 is another schematic diagram showing a central structured data file used by the structure automation modeling method in the solution phase according to an embodiment of the present disclosure;

[0036] Figure 4 is another schematic diagram showing a central structured data file used by the structure automation modeling method in the solution phase according to an embodiment of the present disclosure;

[0037] Figure 5 is a framework diagram showing a VC# script development procedure for an aircraft engine in a structural automation modeling method at a scheme stage according to an embodiment of the present disclosure;

[0038] Figure 6 is a schematic diagram showing a standardized template of a complete aircraft engine established in a structural automation modeling method at a scheme stage according to an embodiment of the present disclosure;

[0039] Figure 7 is a schematic diagram showing a VC# script development procedure for a certain aircraft engine in a structural automation modeling method at a scheme stage according to an embodiment of the present disclosure;

[0040] Figure 8 It is a schematic diagram showing the process of structural automation modeling for a certain aircraft engine according to the structural automation modeling method in the scheme stage of one embodiment of the present disclosure. DETAILED DESCRIPTION

[0041] Various exemplary embodiments, features and aspects of the present disclosure will be described in detail below with reference to the accompanying drawings. The same reference numerals in the accompanying drawings represent elements with the same or similar functions. Although various aspects of the embodiments are shown in the accompanying drawings, the drawings are not necessarily drawn to scale unless otherwise specified.

[0042] The word “exemplary” is used exclusively herein to mean “serving as an example, example, or illustration.” Any embodiment described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments.

[0043] In addition, in order to better illustrate the present disclosure, numerous specific details are given in the following specific embodiments. It should be understood by those skilled in the art that the present disclosure can also be implemented without certain specific details. In some examples, methods, means, components and circuits well known to those skilled in the art are not described in detail in order to highlight the subject matter of the present disclosure.

[0044] Figure 1 FIG. 1 is a flow chart showing a method for automatic structural modeling in the solution phase according to an embodiment of the present disclosure. Figure 1 As shown in the figure, the structural automation modeling method in this scheme stage includes:

[0045] Step 1: Obtain a central structured data file, wherein the central structured data file is used to describe the structure of the scheme stage in a digital way. The scheme stage can also be called the design stage, i.e., the stage of designing the structure to be manufactured. This step is the starting point of automated modeling, wherein the central structured data file can be a file in XML or JSON format, which contains a detailed description of the scheme stage structure, for example, it can include the key design parameters such as the dimensions, material properties, geometric features, assembly relationships, etc. of the components / assemblies / parts included in the scheme stage structure.

[0046] Step 2: creating an automation script, which can parse the central structured data file when running, and interact the structure data of the solution stage obtained by parsing with the modeling software;

[0047] Step 3: By running the automation script, calling the modeling software, and outputting a three-dimensional visual model of the structure in the scheme stage.

[0048] It can be considered that the above steps can achieve rapid iteration and accurate expression of the structure in the scheme stage from the conceptual design to the detailed design stage. First, the designer preliminarily determines the main form of the structure in the scheme stage, and then describes them in a digital form as a central structured data file. Finally, the automated script reads and parses the central structured data file, and passes the parsed data to the modeling software, and finally the modeling software outputs the 3D visualization model of the structure in the scheme stage, thus completing the modeling. The 3D visualization model output by the modeling software not only provides intuitive visual feedback, but can also be used for further analysis, simulation and manufacturing processes.

[0049] In this way, the modeling method of the above-mentioned embodiment of the present disclosure realizes the interaction between the central structured data and the modeling software through the automated script, thereby opening up the digital main line of automated rapid modeling and automated iteration of the structure in the scheme stage.

[0050] The aircraft engine in the embodiment of the present disclosure is, for example, a turbofan engine.

[0051] In a possible implementation, the present disclosure can realize the automatic modeling of the whole structure of an aircraft engine in the scheme design stage. In this implementation, the central structured data file can be a structural semantic model file of the aircraft engine obtained by digitizing the whole structure information of the aircraft engine through the extensible markup language XML, including: declaration, aircraft engine header information and aircraft engine main model structure.

[0052] The declaration is used to express the version and encoding format of the structural semantic model file of the aircraft engine. In the engine header information, common attributes of the structural assembly of the aircraft engine are set, and the common attributes include name, function, author, creation date, and version. The main model structure of the aircraft engine includes: attribute definitions and descriptions of dependencies for structural assemblies obtained by hierarchically dividing the main structure of the aircraft engine into N levels (N can be an integer greater than 2, for example).

[0053] In one possible implementation, Figure 2 As shown, the central structured data file is an XML file. For an XML file, it is usually necessary to use a document declaration in the first line of the document to declare the XML file, so as to tell the XML processing program that the file is a standard XML file, and declare the XML version followed by the file syntax, the encoding format of the document content, and whether there is a dependency relationship with other external files.

[0054] The aircraft engine header information and the aircraft engine main model structure are written in the root element of the XML file. The root element is the main part of the XML document, which contains the key data of the document and the information describing the data structure. The aircraft engine header information written in the root element can be considered as an explanatory information of the XML document, which is used to indicate that this XML file is a data structure file related to aircraft engines.

[0055] Since the common attributes of the structural assembly parts of the aircraft engine are set in the engine header information, including name, function, author, creation date, and version, it can be widely used in the research and development design of different models of aircraft engines and the research and development design of products in other fields.

[0056] The declaration and the aircraft engine header information are mainly described to adapt to the structural specifications of XML itself, and the aircraft engine main model structure is a semantic expression of the structure of the aircraft engine. As described above, the aircraft engine main model structure can be, for example, a description of the attribute definition and dependency relationship of the structural assembly obtained by dividing the main structure of the aircraft engine into N levels according to the hierarchy.

[0057] For example, Figure 2 As shown in FIG. 1 , the main structure of the aircraft engine can be divided into three levels: components, assemblies, and parts. In this case, first, as Figure 3 As shown in the figure, the main structure of the aircraft engine is divided into fan components, intermediate casing components, compressor components, combustion chamber components, turbine components, rear support components, and tail nozzle components according to the component level. There is no order restriction between the components, and they are not affected by the arrangement order.

[0058] Then, the components (or parts) are divided into levels in the component level. Among them, the fan components can be divided into 2-stage rotor-stator components, low-pressure shaft components, flange hinge components, air intake section components, etc.; the intermediate casing components can be divided into duct line components, bearing components, bearing seat components, etc.; the compressor components can be divided into 8-stage rotor-stator components, 1-stage sealing disc components, high-pressure front shaft components, high-pressure rear shaft components, inner casing components, etc.; the combustion chamber components can be divided into compressor outlet blade components, flame tube components, diffuser components, inner casing components, outer casing components, etc.; the turbine components can be divided into 2-stage turbine components, high turbine shaft components, low turbine shaft components, bearing components, bearing seat components, flange hinge components, inner casing components, main shaft components, etc.; the rear support components can be divided into duct line components, flange hinge components, support plate journals, flange journals, etc.; the tail nozzle components can be divided into inner duct line components, outer duct line components, etc. Among them, there is no order restriction between the components and they are not affected by the arrangement order.

[0059] In a possible implementation, the attribute definitions of the structural assemblies in each level include but are not limited to: name, type, model, serial number, material specification, size, weight, functional description, performance parameters, interface type, connection method, manufacturing and assembly requirements. The components / assemblies (or parts) in each level can be identified by a unique identifier (English: Unique Identifier; abbreviation: UID). In this way, different models can be combined with the same elements.

[0060] In addition, when describing the dependency relationship between structural assemblies, multiple aspects need to be considered. For example, the description of the dependency relationship of the components in each divided level may include: describing the assembly relationship between the structural assembly of the current level and the structural assembly of the previous level and / or the next level, the assembly relationship between structural assemblies of the same level, and the parameter information of the primary interface and the secondary interface.

[0061] Among them, the description of the assembly relationship between the structural assembly parts of the current level and the structural assembly parts of the previous level and / or the next level can be used to explain which structural assemblies of the next level are assembled from the structural assembly parts of the previous level. For example, it can be: an aircraft engine is assembled from a fan component, an intermediate casing component, a compressor component, a combustion chamber component, a turbine component, a rear support component, and a tail nozzle component as a second-level component. The fan component as a second-level component is assembled from a second-level rotor and stator assembly, a low-pressure shaft assembly, a flange hinge assembly, and an air intake section assembly as third-level components (or parts). The duct line assembly of the third-level assembly of the intermediate casing component as a second-level component includes an inner duct line, an outer duct line, a bent duct line, and a support plate duct line. The assembly relationship between structural assemblies at the same level can be used to explain how to assemble structural assemblies at the same level, which may involve positioning, alignment, and fixing methods. For example, structural assemblies at the same level can be assembled by welding, screw connection, flange hinge, slot buckle connection, bearing connection, suspension arm sliding connection, etc., to form structural assemblies at the upper level. These assembly relationships are designed by aircraft engine designers and semantically expressed in XML.

[0062] The primary interface is the main contact point between various structural assemblies, and usually bears the main load and function. Therefore, the description of the parameter information of the primary interface may include: the size, shape, fit type (such as fastening, sliding, rotation, etc.) and load capacity of the primary interface. The secondary interface is an auxiliary connection point, which may be used for auxiliary support, cable connection or signal transmission, etc. Therefore, the description of the parameter information of the secondary interface may include: the position, size, type and function of the secondary interface. For example, the primary interface between the fan component and the intermediate casing component is controlled by the axial assembly clearance parameter, and the secondary interface is described by the radial height difference parameter. The blade stage clearance in the fan is its primary interface, which controls the axial distance between the stages. For examples of parameter information of primary and secondary interfaces between other components, please refer to further. Figure 3 These parameter information are also designed by aircraft engine designers and semantically expressed using XML.

[0063] In addition, the main model structure of the aircraft engine can also include: description of the geometric features and dimensional parameters of the lowest-level components. For example, for the inner duct line in the intermediate casing, the description of the association relationship and other information can be appropriately added, the axial position of the given base point is used as a reference for the global coordinates, and the geometric feature position is given the starting point and the end point positioning, where the starting point uses the base point as a reference to give the axial distance and radial height dimensional parameters; the end point also uses the base point as a reference to give the axial distance and radial height dimensional parameters; the geometric shape uses the polynomial interpolation method to establish the curve. This information is also designed by the aircraft engine designer and expressed semantically by XML.

[0064] Figure 4 A schematic diagram showing a central structured data file used in a structural automation modeling method in a scheme phase according to an embodiment of the present disclosure is shown. Figure 4 In the document, the central structured data file is a structural semantic model file of the aircraft engine obtained by describing the overall structure information of the aircraft engine in a digital way through XML. However, it should be noted that the above uses a turbofan engine as an example to illustrate the establishment of the main model structure of the aircraft engine in the XML document, but the present disclosure is not limited to turbofan engines, and the main model structure of other aircraft engines and other structures in the scheme stage can also be established. Moreover, the present disclosure is not limited to XML documents, as long as the structure in the scheme stage can be described in a digital way, it can be used as the central structured data file.

[0065] The automated modeling method of the present invention is exemplarily described below.

[0066] The automated modeling method according to an embodiment of the present disclosure acquires the input of the central structured data through the development of automated scripts, and can automatically model the entire structure of an aircraft engine. In one possible implementation, the automated script is secondary developed by VC# (Visual C#) programming language integration software for NX modeling software (such as Siemens NX), forms an exe program file, establishes mutual interaction between the central structured data XML file and the NX modeling software, and transmits information between them. The VC# script development program snippet for a certain aircraft engine in the structural automated modeling method at the scheme stage according to an embodiment of the present disclosure can be found in Figure 7 .like Figure 5 As shown, the process of program development is as follows:

[0067] Step S100: Establish standardized templates for aircraft engine structural assemblies in NX modeling software to form a universal and extensible structural parametric model library. Among them, structural assemblies can include the above-mentioned components, parts, and components, which are a general term for the various parts that constitute the aircraft engine. These created templates can include parameterizable model elements to facilitate subsequent automated adjustment and expansion. The structural characteristics and design requirements of the aircraft engine can be deeply analyzed according to actual application needs to determine what types of templates need to be established. Figure 6 As shown, the established standardized template preferably covers all major structural parts of an aircraft engine, such as a low-pressure turbine shaft, blades, blisks, a fan shaft, a combustion chamber, and the like.

[0068] In addition, the parametric modeling function of NX modeling software can be used to define adjustable parameters for each template, which can include size, shape, material properties, etc. And, considering possible changes in future needs, the template is extensible so that new functions can be easily added or existing functions can be modified in the future.

[0069] In this step, standardized templates are established to ensure that all templates follow unified design standards and specifications to facilitate collaboration and communication between different designers. In addition, by establishing a centralized model library to manage these templates, the consistency and accessibility of the templates can be determined. In addition, for the convenience of users, an intuitive user interface can be designed for the model library so that users can quickly find and apply the required templates.

[0070] Step S200: Set global variables to provide necessary paths and configuration information for the entire modeling process. Global variables may include XML file paths. They may also include one or more of the root directory where software is placed, the software application directory, the parts storage directory, the template file directory, etc.

[0071] By setting these global variables, you can ensure that the automated script can correctly find the required resources when it is executed, improving the portability and maintainability of the script. In addition, the setting of global variables also helps to simplify script writing because they provide a unified way to reference these key paths and settings instead of hard coding these values ​​in multiple locations in the script. In this way, if the path or setting needs to be changed, it only needs to be updated once in the global variable without modifying each instance in the script.

[0072] Set the exe program file so that when the exe program file is running, it can:

[0073] 1) Based on the global variable, call the XML file (ie Figure 5 For example, when the exe program file is running, it can read the XML file from the set XML file path. The XML file read is a central structured data XML file for digitally describing the structure of the scheme stage, for example, it can be a structural semantic model file of an aircraft engine.

[0074] 2) Initialize the operating environment of the NX modeling software (i.e. Figure 5 For example, the exe program file can be set to load the environment initialization of the NX modeling software during operation to ensure that all necessary components have been initialized.

[0075] 3) Parse the XML file to extract the data needed to create the model (i.e. Figure 5 The exe program file can be set to parse the transmission parameters of the XML file when it is running to extract the required parameters and instructions, such as creating parts, names of created parts, applied materials, defining dimensions, etc., so as to be used in the NX modeling software. Here, it is preferred that the central structured data XML file is automatically read when the exe program is running and the NX modeling software is automatically started to realize the full automation of the modeling process. Of course, if necessary, a user interface can also be designed to allow the user to select the XML file and start the modeling process.

[0076] 4) Based on the extracted data and the structural parameterized model library, create a model (which may include Figure 5 , (i) step S600 to step S900 in FIG.

[0077] Among them, when the exe program file is running, the overall structure of the aircraft engine can be defined according to the digital description in the XML file of the central structured data, that is, step S600, based on the data parsed from the XML file, the model in the parameterized model library formed in step S100 is used to represent the overall structure of the aircraft engine. Step S700 can also be performed to define common basic objects, such as bolts, nuts, etc., which can be reused in multiple models. Step S800 can also be performed to define the engine structure assembly parts, such as defining the engine casing, blades, bearing seats, etc., and these structural assemblies can be customized based on the standardized template established in step S100. Finally, step S900 can be performed to create a model based on the defined overall structure of the aircraft engine, common basic objects, and structural assemblies.

[0078] When the exe program file is running, you can create a definition based on the specified model, that is, select an existing model template according to the actual application requirements, or create a new model from scratch. This may require calling the API (application programming interface) in the NX software to determine all key parameters of the model such as geometry, application material properties, etc., and can create basic geometric shapes such as cuboids, cylinders, spheres, etc., or add more complex features to the basic shapes, such as chamfers, fillets, holes, threads, etc. In addition, parametric technology can be applied to enable the model to be dynamically adjusted according to the input parameters. If the model consists of multiple components, the model can be generated based on the assembly relationship between the components. In this way, the structural design concept in the scheme stage can be converted into a specific three-dimensional representation. The exe program file can be set up so that it can achieve the above functions when it is running.

[0079] According to an embodiment of the present disclosure, the automatic creation of the structural model can be completed by calling and running the automation script exe program file. The automation script can run the program through external commands, automatically read the central structured data file inside the program, and automatically call the standardized model library established in the modeling software, so as to automatically complete the modeling of the structure (such as an aircraft engine such as a turbofan engine) at the scheme stage. Figure 8 As shown, the automated modeling process is as follows:

[0080] 1) Call the exe program. The user can start the automation script by double-clicking the icon or entering the command line.

[0081] 2) Execute the exe program. As mentioned above, the automation script is loaded and executed by the operating system as a compiled executable file (exe).

[0082] The following steps are performed during the execution of the exe program: initializing the operating environment of the NX modeling software; parsing the XML file path; reading the XML file based on the parsed XML file path; parsing the XML file to extract the data required for model creation; and starting to create the model based on the data extracted from the XML file, including: accessing the structural parametric model library established in the NX modeling software, cloning the template in the structural parametric model library based on the data extracted from the XML file, and defining the model parameter information for the cloned template to complete the creation of the model and initialize the operating environment of the NX modeling software.

[0083] As an example, Figure 8 The above steps are implemented in the manner shown, specifically:

[0084] 3) Determine whether the environment variables of the NX modeling software are set. If not, end; otherwise, proceed to 4). For running the NX modeling software, the environment variables play a core role in the running and path specification of the software.

[0085] 4) Initialize the operating environment of the NX modeling software to ensure that all necessary services and components are ready.

[0086] 5) Parse XML path parameters. The exe program can read the path of the XML file from the configuration file or command line parameters.

[0087] 6) Determine whether there is an XML file in the parsed path, or whether the XML file in the path is readable. If not, end; otherwise, go to 7).

[0088] 7) Serialize the XML file, that is, parse the XML file and convert its content into the form of an internal data structure. In one embodiment, the XML file read is a central structured data XML file used to describe the structure in the scheme stage in a digital way, so that all data required for model creation can be extracted from the XML file, including attribute information such as size, shape, material, etc. of the structural assembly, as well as the dependency relationship between the structural assemblies, etc., for subsequent processing.

[0089] 8) Start creating the model based on the data extracted from the XML file.

[0090] 9) Accessing the structural parametric model library established in the NX modeling software, cloning templates based on the data extracted from the XML file. Standardized templates stored in the model library can be accessed, and if there are standardized templates corresponding to the structural assemblies described in the XML file, these templates are cloned as the basis for the new model. If there are no ready-made templates, a new model can be created based on the detailed parameters of the structural assembly extracted from the XML file.

[0091] 10) Define the model parameter information for the cloned template. When using the standardized template in the model library, the model parameter information, such as size, shape, etc., can be defined according to the data in the XML file to meet the design requirements.

[0092] 11) Determine the type of model created. If it is a part, modify the definition parameters according to the information represented by the XML file; if it is a component, assemble it. Parameters can be defined or assembled according to the type of model created. For parts, adjust the model parameters according to the XML file information, and modify the definition parameters so that the size or shape meets the specific design requirements; for components, assemble according to the dependency relationship described in the XML file, and combine different parts according to the design requirements.

[0093] 12) The creation is completed and a 3D visual model of a scheme-stage structure (such as an aircraft engine such as a turbofan engine) is finally output.

[0094] Automating the modeling process is an efficient way of working that allows models to be automatically created or modified through a series of predefined steps. This process can greatly improve the efficiency and consistency of modeling and reduce human errors, especially when a large number of similar models need to be created. Through automation, time can be saved, allowing designers to focus on more complex design tasks.

[0095] As in the above modeling process, after the automated script exe program is run, the automated creation of the structural model of the aero-engine scheme phase of an embodiment of the present disclosure can be completed. Throughout the process, the XML file acts as a data source, providing all the information required to create and assemble the model. The automated script reads and parses this data, and then performs the corresponding modeling and assembly operations. This method improves design efficiency, reduces human errors, and allows for rapid iteration and modification of the design.

[0096] According to the structural automation modeling method in the scheme stage of the above-mentioned embodiment of the present disclosure, at least one of the following beneficial effects can be achieved: 1. The interaction between the central structured data and the modeling software is realized. 2. The interaction between the structural data and the modeling software can be realized through less integrated software. 3. The automatic creation of the structural model can be realized by running the program externally. 4. The digital main line of rapid structural automation modeling and automatic iteration in the scheme stage is opened up. 5. It can be widely used in the research and development design of different models of aircraft engines, as well as the research and development design of products in other fields.

[0097] The embodiments of the present disclosure also provide a computer program product, which includes a computer-readable code, or a non-volatile computer-readable storage medium carrying the computer-readable code. When the computer-readable code runs in a processor of an electronic device, the processor in the electronic device executes the above method.

[0098] The embodiments of the present disclosure have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The selection of terms used herein is intended to best explain the principles of the embodiments, practical applications, or technical improvements in the market, or to enable other persons of ordinary skill in the art to understand the embodiments disclosed herein.

Claims

1. A structural automation modeling method in the scheme stage, characterized in that: include: Step 1: obtaining a central structured data file, wherein the central structured data file is used to describe the main structure of the aircraft engine in the scheme stage in a digital manner; Step 2: creating an automated script, which can parse the central structured data file when running, and interact the parsed data of the main structure of the aircraft engine at the scheme stage with the modeling software; Step 3: By running the automation script, calling the modeling software, outputting a three-dimensional visualization model of the main structure of the aircraft engine in the scheme stage, The central structured data file is a structural semantic model file of the aircraft engine obtained by describing the whole structure information of the aircraft engine in a digital manner using the extensible markup language XML, including: declaration, aircraft engine header information and aircraft engine main model structure, The statement is used to describe the version and encoding format of the structural semantic model file of the aircraft engine. In the aircraft engine header information, common attributes of the structural assembly of the aircraft engine are set, and the common attributes include name, function, author, creation date, and version. The main model structure of the aircraft engine includes: a description of attribute definitions and dependency relationships for structural assemblies obtained by dividing the main structure of the aircraft engine into N levels according to levels, wherein N is an integer greater than 2, The automation script is an exe program file obtained by secondary development of NX modeling software by VC# programming language integration software. In step three, the program of the automation script is run through external commands, and the central structured data file is automatically read within the program, and the standardized model library established in the NX modeling software is automatically called to automatically complete the entire process of modeling the main structure of the aircraft engine in the scheme stage.

2. The method for automatic structural modeling in the scheme stage according to claim 1, characterized in that: The central structured data file is an XML file, and the secondary development of the NX modeling software includes: Establishing a standardized template for aero-engine structural assembly parts in the NX modeling software to form a structural parameterized model library; Set global variables, including XML file path; Set the exe program file so that when the exe program file is running, it can: Based on the global variable, calling the XML file; Initializing the operating environment of the NX modeling software; Parsing the XML file to extract data required for model creation; Model creation is performed based on the extracted data and the structural parameterized model library.

3. The method for automatic structural modeling in the scheme stage according to claim 2, characterized in that: In step 3, by calling and executing the exe program, the following process is performed to realize automated modeling: Initializing the operating environment of the NX modeling software; Parse XML file path; Reading an XML file based on the parsed XML file path; Parsing the XML file to extract data required for model creation; Based on the data extracted from the XML file, start creating the model, including: The structural parametric model library established in the NX modeling software is accessed, and based on the data extracted from the XML file, the template in the structural parametric model library is cloned, and the model parameter information of the cloned template is defined to complete the creation of the model.

4. A computer program product, comprising a computer-readable code, or a non-volatile computer-readable storage medium carrying the computer-readable code, wherein when the computer-readable code is executed in a processor of an electronic device, the processor in the electronic device executes the method according to any one of claims 1 to 3.

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