Conversion method of architecture model data of aero-engine and computer equipment

Abstract

The invention relates to the technical field of digital data processing of aero-engines, in particular to a conversion method of architecture model data of an aero-engine and computer equipment. The method comprises the steps that a hierarchical relation and a structural relation in an initial model are mapped into a model of a target format, a mapped initial conversion model is obtained, and the initial model is an architecture model constructed based on a SysML language; wherein the components are constituent units of the aero-engine, and the components are constituent units of the components; the structural relationship represents the connection relationship among the components and the connection relationship among the components forming the same component; determining a component list comprising components forming the initial model; and matching structure description data of a target format for each component in the component list, and writing the structure description data into the initial conversion model to obtain a target conversion model. By adopting the method, the design cost of the aero-engine can be reduced.

Description

Technical Field

[0001] This application relates to the technical field of digital data processing for aero-engines, and particularly to a method for converting architecture model data of aero-engines and a computer device. Background Art

[0002] Aero-engines are composed of numerous components and parts, and all parts are interrelated and interact with each other. During the design process of aero-engines, the Model-based Systems Engineering (MBSE) method is adopted to establish a system model, so that these scattered information can be integrated into a unified framework. The system model includes a requirements model, a function model, an architecture model, etc., and the SysML language (Systems Modeling Language) is used to express the solutions of each system in a graphical form.

[0003] The architecture model expressed in the SysML language can completely express the architecture information and can effectively support the development of subsequent research and development work. However, the architecture model is saved in a file with a specific format, and it is difficult for other software to directly obtain the data therein, resulting in the inability to establish a connection between the SysML architecture model and the subsequent design process; this requires designing other format files for the architecture model separately in the subsequent design process, thus increasing the design cost.

[0004] Therefore, how to reduce the design cost of aero-engines is an urgent problem to be solved. Summary of the Invention

[0005] Based on this, in view of the above technical problems, it is necessary to provide a method for converting architecture model data of aero-engines and a computer device that can reduce the design cost of aero-engines.

[0006] In a first aspect, this application provides a method for converting architecture model data of aero-engines, including:

[0007] Mapping the hierarchical relationship and structural relationship in the initial model to the model in the target format to obtain the initially transformed model after mapping, where the initial model is an architecture model constructed based on the SysML language; the hierarchical relationship represents the dependency relationship between components and aero-engines, and the dependency relationship between parts and components; wherein, the component is a constituent unit of the aero-engine, and the part is a constituent unit of the component; the structural relationship represents the connection relationship between the components and the connection relationship between the parts that make up the same component;

[0008] Determining a parts list including all the parts that make up the initial model;

[0009] Match the structural description data in the target format for each of the components in the component list, and write the structural description data into the initial transformation model to obtain a target transformation model.

[0010] In one embodiment, the process of constructing the initial model includes:

[0011] Create a module definition diagram, and construct a main element, a component element, and a sub-component element in the module definition diagram, where the main element is the module element corresponding to the aero-engine, the component element is the module element corresponding to the component, and the sub-component element is the module element corresponding to the component;

[0012] Establish a dependency association between each of the component elements and the main element, and establish a dependency association between each of the component elements that depend on the component element and the component element, to construct the hierarchical relationship;

[0013] Construct an internal module diagram inside each target element, and map the elements corresponding to the respective constituent units of the target element in the internal module diagram; the target element is the main element or the component element;

[0014] Based on the structural information of the aero-engine, establish a connection association between the component elements that depend on the same component element, and establish a connection association between the component elements, to construct the structural relationship;

[0015] Construct the initial model based on the hierarchical relationship and the structural relationship.

[0016] In one embodiment, the establishing a connection association between the component elements that depend on the same component element, and establishing a connection association between the component elements includes:

[0017] Add a proxy port to each of the component elements, and add a proxy port to each of the component elements;

[0018] Connect the proxy ports of the component elements through a connector, and connect the proxy ports of the component elements through the connector.

[0019] In one embodiment, the component list includes the identity identifier of each of the components, and the matching the structural description data in the target format for each of the components in the component list includes:

[0020] For each of the components in the component list, based on the identity of the component, match the corresponding structural description data of the component from the structural model library; the structural model library includes the correspondence between the structural description data and the identity of each component.

[0021] In one embodiment, the structural description data at least includes attribute definitions, geometric features, and dimensional parameters; the target format is XML format.

[0022] In one embodiment, the writing of the structural description data into the initial transformation model includes:

[0023] For each of the components, determine the target position of the component element corresponding to the component in the initial transformation model;

[0024] Replace the original data corresponding to the target position with the structural description data.

[0025] In a second aspect, the present application also provides a conversion device for the architecture model data of an aeroengine, including a mapping module, a list determination module, and a data matching module, where:

[0026] The mapping module is used to map the hierarchical relationship and structural relationship in the initial model to the model in the target format to obtain the mapped initial transformation model, and the initial model is an architecture model constructed based on the SysML language; the hierarchical relationship represents the dependency relationship between components and the aeroengine, and the dependency relationship between components and sub-components; where the component is a constituent unit of the aeroengine, and the sub-component is a constituent unit of the component; the structural relationship represents the connection relationship between the components and the connection relationship between the sub-components that make up the same component;

[0027] The list determination module is used to determine a component list including each of the sub-components that make up the initial model;

[0028] The data matching module is used to match the structural description data in the target format for each of the sub-components in the component list and write the structural description data into the initial transformation model to obtain the target transformation model.

[0029] In a third aspect, the present application also provides a computer device, including a memory and a processor, the memory stores a computer program, and when the processor executes the computer program, the following steps are implemented:

[0030] Map the hierarchical relationship and structural relationship in the initial model to the model in the target format to obtain the mapped initial transformation model, where the initial model is an architecture model constructed based on the SysML language; the hierarchical relationship represents the dependency relationship between components and aeroengines, and the dependency relationship between parts and components; wherein, the component is a constituent unit of the aeroengine, and the part is a constituent unit of the component; the structural relationship represents the connection relationship between the components and the connection relationship between the parts that make up the same component;

[0031] Determine a parts list including all the parts that make up the initial model;

[0032] Match the structural description data in the target format for each part in the parts list and write the structural description data into the initial transformation model to obtain the target transformation model.

[0033] In a fourth aspect, the present application also provides a computer-readable storage medium, on which a computer program is stored, and when the computer program is executed by a processor, the following steps are implemented:

[0034] Map the hierarchical relationship and structural relationship in the initial model to the model in the target format to obtain the mapped initial transformation model, where the initial model is an architecture model constructed based on the SysML language; the hierarchical relationship represents the dependency relationship between components and aeroengines, and the dependency relationship between parts and components; wherein, the component is a constituent unit of the aeroengine, and the part is a constituent unit of the component; the structural relationship represents the connection relationship between the components and the connection relationship between the parts that make up the same component;

[0035] Determine a parts list including all the parts that make up the initial model;

[0036] Match the structural description data in the target format for each part in the parts list and write the structural description data into the initial transformation model to obtain the target transformation model.

[0037] In a fifth aspect, the present application also provides a computer program product, including a computer program, and when the computer program is executed by a processor, the following steps are implemented:

[0038] Map the hierarchical relationship and structural relationship in the initial model to the model in the target format to obtain the initial transformed model after mapping. The initial model is an architecture model constructed based on the SysML language. The hierarchical relationship represents the dependency relationship between components and the aero-engine, as well as the dependency relationship between parts and components. Among them, the component is a constituent unit of the aero-engine, and the part is a constituent unit of the component. The structural relationship represents the connection relationship between the components and the connection relationship between the parts that make up the same component.

[0039] Determine a list of parts that includes all the parts that make up the initial model.

[0040] Match the structural description data in the target format for each part in the list of parts and write the structural description data into the initial transformed model to obtain the target transformed model.

[0041] In the above conversion method, device, computer device, storage medium, and program product for the architecture model data of the aero-engine, first map the hierarchical relationship and structural relationship in the initial model to the model in the target format to obtain the initial transformed model. The initial transformed model contains the core data of the hierarchical relationship and structural relationship between components and parts in the aero-engine, and uses the hierarchical relationship and structural relationship as the core framework to represent the structure of the aero-engine. Then, based on the determined list of parts, match the standardized structural description data for each part in the list of parts, and write the structural description data corresponding to each part into the initial transformed model. Finally, generate the target transformed model in the target format that describes the overall structure information of the aero-engine. Since the target transformed model is in the target format, compared with the initial model constructed by the SysML language, the target transformed model in the target format is more convenient to be read and parsed by other software, which is more conducive to data transfer with other software, ensures the input of systematic and complete architecture information, improves the efficiency of collaborative design, and reduces the cost in the design process. At the same time, the standardized structural description information of parts improves the generation efficiency and accuracy of the overall XML structural description model. Description of the Drawings

[0042] In order to more clearly illustrate the technical solutions in the embodiments of the present application or related technologies, the following will briefly introduce the drawings required for use in the description of the embodiments or related technologies. Obviously, the following drawings are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0043] Figure 1 It is a schematic flowchart of the conversion method for the architecture model data of the aero-engine in an embodiment.

[0044] Figure 2 Schematic diagram of the construction process of the initial model in an embodiment;

[0045] Figure 3 Relationship between the main elements and component elements of a turbofan engine in an embodiment;

[0046] Figure 4 Schematic diagram of the hierarchical relationship of each component in the fan component in an embodiment;

[0047] Figure 5 Schematic diagram of the structural relationship between components in the fan component in an embodiment;

[0048] Figure 6 Schematic diagram of the structural relationship between the fan component and the intermediate casing component in an embodiment;

[0049] Figure 7 Schematic diagram of the mapping result of the hierarchical relationship in the initial model in an embodiment;

[0050] Figure 8 Schematic diagram of the mapping result of the structural relationship in the initial model in an embodiment;

[0051] Figure 9 Schematic diagram of the steps of writing structural description data into the initial conversion model in an embodiment;

[0052] Figure 10 Example of the structural description data of the disk-associated bearing housing in an embodiment;

[0053] Figure 11 Schematic diagram after writing the structural description data of the disk-associated bearing housing into the initial conversion model in an embodiment;

[0054] Figure 12 Schematic diagram of the core logic of the conversion method of the architecture model data of an aeroengine in an embodiment;

[0055] Figure 13 Schematic diagram of the structure of the conversion device for the architecture model data of an aeroengine in an embodiment;

[0056] Figure 14 Internal structure diagram of a computer device in an embodiment. Detailed implementation manners

[0057] In order to make the objectives, technical solutions and advantages of the present application clearer and more understandable, the present application will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0058] The conversion method of the architecture model data of an aeroengine provided by an embodiment of the present application is executed by a computer device; wherein, the computer device can be, but is not limited to, various personal computers, laptop computers, smart phones, tablet computers, servers, etc.; the server can be implemented by an independent server or a server cluster composed of multiple servers.

[0059] In an exemplary embodiment, as Figure 1 shown, a conversion method of the architecture model data of an aeroengine is provided, including the following steps 110 to 130, wherein:

[0060] Step 110: Map the hierarchical relationship and structural relationship in the initial model to the model in the target format to obtain the initially converted model after mapping.

[0061] For the embodiment of the present application, the initial model is an architecture model constructed based on the SysML language; the hierarchical relationship represents the dependency relationship between components and the aeroengine, as well as the dependency relationship between parts and components; wherein, the component is the constituent unit of the aeroengine, and the part is the constituent unit of the component; the structural relationship represents the connection relationship between components and the connection relationship between parts that make up the same component.

[0062] Specifically, the initial model can be pre-established or constructed in real time; in the embodiment of the present application, the initial model can be a model of any type of aeroengine. In the embodiment of the present application, the initial model described in the subsequent content is exemplified by the model of a turbofan engine; the process of constructing the initial model based on the SysML (Systems Modeling Language) language will be elaborated in more detail in the following content.

[0063] A turbofan engine is composed of various components. For example, a turbofan engine is composed of components such as a fan, an intermediate case, a compressor, a combustor, a turbine, a rear case, and a jet pipe; each component is further disassembled into parts. For example, the fan component is composed of parts such as 2 rotor blades, 2 stator blades, a neckless rotor disc, a base cone rotor disc, a flange hinge, an entry, and a low shaft.

[0064] Furthermore, the target format can be any format that is convenient for other software or devices to obtain. In the embodiments of the present application, the target format is taken as an example of XML (eXtensible Markup Language) format to elaborate the solution. In one possible implementation manner, the mapping method can be performed through the components embedded in the software for building the initial model, that is, in the software for building the initial model, the first format conversion component embedded in the software itself is used to read and convert the file of the initial model into an initial conversion model in XML format. In the initial model, each component is represented by a component element corresponding to the component, and each sub-component is represented by a component element corresponding to the sub-component; the structural relationship between the elements is connected in the form of a connector. Therefore, in another implementation manner, the second format conversion component can also be pre-configured to identify the identity of each element (component or sub-component) in the initial model, and identify the relationship (structural relationship) between the elements through the connector, and then express the identified data in XML format data, so as to obtain the initial conversion model.

[0065] Step 120: Determine a sub-component list including each sub-component constituting the initial model.

[0066] For the embodiments of the present application, the sub-component list includes the identity identifiers of each sub-component constituting the initial model, that is, includes the identity identifiers of each sub-component corresponding to each component. Among them, the sub-component list can be extracted from the hierarchical relationship of the initial model. Each sub-component and component corresponds to a unique identity identifier. The identity identifier can be the name of the sub-component or component, or can also be a predefined unique number. The specific type of the identity identifier is not specifically limited in the embodiments of the present application.

[0067] Step 130: Match the structural description data in the target format for each sub-component in the sub-component list, and write the structural description data into the initial conversion model to obtain the target conversion model.

[0068] For the embodiments of the present application, a structural model library can be pre-constructed. The structural model library includes the structural description data of various sub-components of various types of aero-engines. The structural model library includes the corresponding relationship between the structural description data of each sub-component and the identity identifier; among them, the structural description data includes various detailed parameters of the sub-component, such as attribute definition, geometric features, and dimensional parameters, etc. The specific parameter type of the structural description data is not specifically limited in the embodiments of the present application. For each sub-component in the sub-component list, based on the identity identifier of the sub-component, the corresponding structural description data of the sub-component is matched from the structural model library.

[0069] Further, the structure description data can be expressed in other forms in the initial model, such as graphical expression; the structure description data of each component may not exist in the initial model either. Therefore, in order to make the parameter information in the converted model more complete, in the embodiments of the present application, after obtaining the initial conversion model, the structure description data of each component in the component list is written into the initial conversion model, so as to obtain the target conversion model with more complete parameter information.

[0070] In the above method for converting the architecture model data of an aero-engine, first, the hierarchical relationship and structural relationship in the initial model are mapped to the model in the target format to obtain the initial conversion model. The initial conversion model contains the core data of the hierarchical relationship and structural relationship of the components and parts in the aero-engine, and the hierarchical relationship and structural relationship are used as the core framework to represent the structure of the aero-engine. Then, based on the determined component list, normalized structure description data is matched for each component in the component list, and the structure description data corresponding to each component is written into the initial conversion model, and finally, the target conversion model in the target format describing the overall structure information of the aero-engine is generated. Since the target conversion model is in the target format, compared with the initial model constructed by the SysML language, the target conversion model in the target format has the convenience of being read and parsed by other software, which is more conducive to data transfer with other software, ensuring the input of systematic and complete architecture information, improving the efficiency of collaborative design, and reducing the cost in the design process. At the same time, the standardized component structure description information improves the generation efficiency and accuracy of the overall machine XML structure description model.

[0071] Further, referring to Figure 2 , the construction process of the initial model may specifically include step 010-step 050, where:

[0072] Step 010: Create a module definition diagram, and construct a main element, a part element, and a component element in the module definition diagram.

[0073] Specifically, create a module definition diagram (Block Definition Diagram, BDD) based on the SysML language, and create a module (Block) element in the BDD diagram to represent the turbofan engine and its various parts; among them, the module element specifically includes a main element, a part element, and a component element, that is: create a main element for the aero-engine (turbofan engine) in the BDD diagram, create a corresponding part element for each part that makes up the aero-engine (turbofan engine), and create a corresponding component element for the components of each part. Among them, the main element is the module element corresponding to the aero-engine, the part element is the module element corresponding to the part, and the component element is the module element corresponding to the component.

[0074] Step 020: Establish dependency associations between each component element and the main body element, and establish dependency associations between the component element and each component element that depends on the component element to construct a hierarchical relationship.

[0075] Further, create a Directed Composition relationship in the BDD diagram between the main body element and each component element it contains. The Directed Composition relationship is also known as a dependency association, which characterizes which component elements the main body element consists of and also which component elements depend on the main body element.

[0076] Among them, the dependency association between the main body element and the component element can be represented by a connected line with an arrow. The end where the arrow points is connected to the component element, and the end with the black diamond is connected to the main body element. In one example, the relationship between the main body element of a turbofan engine and each component element is as Figure 3 shown; from Figure 3 it can be seen that the main body element of the turbofan engine consists of component elements corresponding to components such as a fan, an intermediate case, a compressor, a combustor, a turbine, a rear support, and a jet pipe.

[0077] Further, define the inclusion relationship between the component element and the component element in the BDD diagram, that is, use the Directed Composition relationship to express which components each component consists of. The association relationship between the component element and the component element is also represented by a connected line with an arrow. Among them, the end where the arrow points is the component element, and the end with the black diamond is connected to the component element. In one example, the relationship between the component element of a fan and each component element is as Figure 4 shown. From Figure 4 it can be seen that the component element corresponding to the fan component consists of component elements corresponding to components such as 2 rotor blades, 2 stator blades, a neckless rotor disc, a base cone rotor disc, a flange hinge, an entry section, and a low-pressure shaft.

[0078] Step 030: Construct an internal module diagram inside each target element and map the elements corresponding to each constituent unit of the target element in the internal module diagram.

[0079] Step 040: Based on the structural information of the aero-engine, establish connection associations between component elements that depend on the same part element, and establish connection associations between each part element to construct a structural relationship.

[0080] Specifically, the target element is the main element or the part element. The main element of the turbofan engine and the part element of each part are taken as a target element. Thus, for each target element, an internal block diagram (IBD) based on the SysML language is created inside the target element, and the components of the target element are automatically mapped to the part properties of the part element. The type of the part property is each component element that constitutes the part element. Since the type of the part property is unique, the one-to-one correspondence between the part property and each component element it contains is realized.

[0081] Furthermore, establishing connection associations between component elements that depend on the same part element and establishing connection associations between each part element may specifically include: adding proxy ports to each component element and adding proxy ports to each part element; then connecting the proxy ports of the component elements through a connector, and connecting the proxy ports of the part elements through a connector.

[0082] Specifically, create proxy ports in the part element and the component element. The proxy port is displayed as an edge target shape attached to the part property in the IBD diagram, where the target shape is a rectangle; in the embodiment of the present application, taking the target shape as a square as an example, however, the target shape can also be other rectangles such as a rectangle or a rhombus, and the present application does not specifically limit this. Use a connector to connect the proxy ports. The connector is displayed as a connection line between small squares in the IBD diagram. The connector indicates that there is a structural connection between the parts or components to which the proxy ports at both ends belong. In one example, the IBD diagram between each component element in the fan part of the aero-engine is as Figure 5 shown; from Figure 5 it can be seen the structural connection relationship between each component in the fan part. Furthermore, in another example, the connection relationship between each component element in the part element of the fan part, the connection relationship between each component element in the intermediate casing part element, and the connection relationship between the part element of the fan part and the intermediate casing part element are as Figure 6 shown; from Figure 6It can be seen that there are 4 structural connections between the fan component and the intermediate case, and it can be intuitively characterized which components between them have structural connections. For example, there are structural connections between the low shaft of the fan and the top center bearing, the middle bearing, and the disc associated bearing seat of the intermediate case, and there is also a structural connection between the disc associated bearing seat of the intermediate case and the base cone rotor disc of the fan.

[0083] Step 050: Construct an initial model based on the hierarchical relationship and the structural relationship.

[0084] The above steps not only elaborate on how to construct an architecture model (initial model) of an aero-engine based on SysML, but also describe the structure of the architecture model and the hierarchical relationship and structural relationship between the elements it contains. In the embodiments of the present application, the initial model can be constructed in real time based on the above steps 010-050, or can be a pre-constructed model of the structure characterized by the above steps 010-step 050. It can be determined that the initial model in the embodiments of the present application can be processed by the computer device executing steps 110-step 130 to obtain the target conversion model.

[0085] Furthermore, the mapping process of the hierarchical relationship and the structural relationship in step 110 is analyzed. Among them, for the mapping process of the hierarchical relationship, that is, mapping the composition relationship (hierarchical relationship) in the initial model (architecture model based on SysML) to the model in the target format (XML model): identifying the composition relationship (hierarchical relationship) between the main element of the turbofan engine and the component elements of each component in the SysML architecture model, and the composition relationship (hierarchical relationship) between the component elements of each component and the component elements of the corresponding components through a preset second format conversion component, and then mapping the identified composition relationship to the XML model. The mapping result is as Figure 7 shown. Among them, the second format conversion component can be an independent component, that is, a component not embedded in the software for constructing the initial model.

[0086] From Figure 7It can be known that in the XML model, the turbofan is the root element, and the component elements of each component such as the fan and the intermediate case are the child elements of the root element. The component elements of components such as the disc-associated bearing seat, the top center bearing, and the middle bearing are the child elements of the component elements of the intermediate case. The information expressed by the parent-child relationship (hierarchical relationship) between the elements in the XML model is completely consistent with the architectural information expressed by the composition relationship between the elements in the SysML architecture model.

[0087] The mapping process of the structural relationship, that is, mapping the structural connection information in the SysML architecture model to the XML model: identifying the connection relationships between the component elements and component elements in the SysML architecture model through a preset second format conversion component, and mapping the identified connection relationships to the XML model. The mapping result is as Figure 8 shown. It can be known from Figure 8 that in the XML model, the structural connection (connection relationship) between components is represented by "Clearances", and "Clearances" is also a child element of the root element; the "Clearances" element has two child elements, namely "From" and "To", and the element content represents that the structural connection exists between the fan and the intermediate case.

[0088] Specifically, the "Clearances" element also has 4 parallel child elements, indicating that there are 4 structural connections between the fan and the intermediate case; the name of each child element is "Clearance"; inside each "Clearance" element, there are two child elements, "From" and "To", and the element content represents between which components of their respective internal the structural connection between the two components is defined.

[0089] Taking the Figure 8 uppermost "Clearance" element as an example, the content of its child element "From" represents the base cone rotor disc of the fan, and the content of the other child element "To" represents the disc-associated bearing seat of the intermediate case. The information expressed by this "Clearance" element is that there is a structural connection between these two components. The meanings expressed by the remaining "Clearance" elements are similar and will not be elaborated here.

[0090] In one of the embodiments, referring toFigure 9 , in step 130, write the structure description data into the initial transformation model, which may specifically include step 131 and step 132, where:

[0091] Step 131: For each component, determine the target position of the component element corresponding to the component in the initial transformation model;

[0092] Step 132: Replace the original data corresponding to the target position with the structure description data.

[0093] Specifically, the corresponding XML structure description data can be obtained from the structure model library according to the identity identifier of each component element in each component list; Figure 10 is an example of the structure description data of the disc associated bearing seat in the structure model library. The structure description data contains a detailed description of the attribute definition, geometric features, and dimensional parameters of the disc associated bearing seat. Fill the structure description data of the disc associated bearing seat in the structure model library into the XML model, as Figure 11 shown. It can be seen from Figure 11 that the structure description data "DiscAssociatedBearingSeat" element of the disc associated bearing seat obtained from the structure model library replaces the homonymous sub-element of the intermediate case in the XML model.

[0094] In summary, the main logic of the method for converting the architecture model data of the aeroengine provided in this application is as Figure 12 shown, including: constructing a SysML architecture model of the aeroengine, defining the composition structure, hierarchical relationship, and structural connections of the relevant components (parts and components) of the aeroengine therein. Then, map the SysML architecture model to an XML model, and the XML model completely carries the information from the SysML architecture model. According to the information of the components of the aeroengine in the architecture model, extract the standardized structure description data (detailed description of the attribute definition, geometric features, and dimensional parameters of the components) of the corresponding components of the aeroengine expressed in XML language from the structure model library, and fill the structure description data into the specific data structure of the XML model, and finally generate an XML structure description model describing the overall structure information of the aeroengine.

[0095] It should be understood that although the steps in the flowcharts involved in the above embodiments are shown in sequence according to the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless specifically stated herein, there is no strict order restriction for the execution of these steps, and these steps can be executed in other orders. Moreover, at least some of the steps in the flowcharts involved in the above embodiments may include multiple steps or multiple stages. These steps or stages are not necessarily executed at the same time, but can be executed at different times. The execution order of these steps or stages is not necessarily sequential, but can be executed alternately or in rotation with at least some of the steps or stages in other steps or other steps.

[0096] Based on the same inventive concept, an embodiment of the present application further provides a conversion device for the architecture model data of an aeroengine for implementing the conversion method of the architecture model data of the aeroengine involved above. The solution provided by this device for solving problems is similar to the solution described in the above method. Therefore, the specific limitations in one or more embodiments of the conversion device for the architecture model data of the aeroengine provided below can refer to the limitations on the conversion method of the architecture model data of the aeroengine in the above text, and will not be repeated here.

[0097] In an exemplary embodiment, as Figure 13 shown, a conversion device for the architecture model data of an aeroengine is provided. The device includes a mapping module 1301, a list determination module 1302, and a data matching module 1303, where:

[0098] The mapping module 1301 is configured to map the hierarchical relationship and structural relationship in the initial model to the model in the target format, and obtain the initially converted model after mapping. The initial model is an architecture model constructed based on the SysML language; the hierarchical relationship represents the dependency relationship between components and the aeroengine, and the dependency relationship between parts and components; wherein, a component is a constituent unit of the aeroengine, and a part is a constituent unit of a component; the structural relationship represents the connection relationship between components and the connection relationship between parts that make up the same component.

[0099] The list determination module 1302 is configured to determine a list of parts including each part that makes up the initial model.

[0100] The data matching module 1303 is configured to match the structural description data in the target format for each part in the list of parts, and write the structural description data into the initially converted model to obtain the target converted model.

[0101] In the conversion device for the architecture model data of the above-mentioned aeroengine, first, the hierarchical relationship and structural relationship in the initial model are mapped into the model in the target format to obtain the initial conversion model. The initial conversion model contains the core data of the hierarchical relationship and structural relationship of the components and parts in the aeroengine, and the hierarchical relationship and structural relationship are used as the core framework to characterize the structure of the aeroengine. Then, based on the determined parts list, normalized structural description data is matched for each part in the parts list, and the structural description data corresponding to each part is written into the initial conversion model, and finally, the target conversion model in the target format describing the overall structure information of the aeroengine is generated. Since the target conversion model is in the target format, compared with the initial model built with the SysML language, the target conversion model in the target format has the convenience of being read and parsed by other software, which is more conducive to data transfer with other software, ensuring the input of systematic and complete architecture information, improving the efficiency of collaborative design, and reducing the cost in the design process. At the same time, the standardized structural description information of the parts improves the generation efficiency and accuracy of the overall machine XML structure description model.

[0102] In one embodiment, the device further includes a construction module. When constructing the initial model, the construction module is specifically used for:

[0103] The creation module defines a module diagram and constructs a main element, a part element, and a component element in the module diagram. Among them, the main element is the module element corresponding to the aeroengine, the part element is the module element corresponding to the part, and the component element is the module element corresponding to the part.

[0104] A dependency association is established between each part element and the main element, and a dependency association is established between each part element and each component element that depends on the part element to construct a hierarchical relationship.

[0105] An internal module diagram is constructed inside each target element, and the elements corresponding to each constituent unit of the target element are mapped in the internal module diagram. The target element is the main element or the part element.

[0106] Based on the structural information of the aeroengine, a connection association is established between the component elements that depend on the same part element, and a connection association is established between the part elements to construct a structural relationship.

[0107] The initial model is constructed based on the hierarchical relationship and the structural relationship.

[0108] In one embodiment, the construction module is specifically used for:

[0109] Add a proxy port to each component element and add a proxy port to each part element.

[0110] Connect the proxy ports of component elements through a connector, and connect the proxy ports of part elements through a connector.

[0111] In one embodiment, the data matching module 1303 is specifically configured to:

[0112] For each component in the component list, based on the identity identifier of the component, match the corresponding structure description data of the component from the structure model library; the structure model library includes the correspondence between the structure description data of each component and the identity identifier.

[0113] In one embodiment, the structure description data includes at least attribute definitions, geometric features, and dimensional parameters; the target format is XML format.

[0114] In one embodiment, the data matching module 1303 is specifically configured to:

[0115] For each component, determine the target position of the corresponding component element of the component in the initial conversion model;

[0116] Replace the original data corresponding to the target position with the structure description data.

[0117] Each module in the above conversion device for the architecture model data of the aeroengine can be implemented in whole or in part by software, hardware, and their combination. The above modules can be embedded in the processor of the computer device in hardware form or independent of it, or stored in the memory of the computer device in software form, so that the processor can call and execute the operations corresponding to the above modules.

[0118] In an exemplary embodiment, a computer device is provided. The computer device can be a terminal, and its internal structure diagram can be as Figure 14As shown in the figure. The computer device includes a processor, a memory, an input / output interface, a communication interface, a display unit, and an input device. Among them, the processor, the memory, and the input / output interface are connected through a system bus, and the communication interface, the display unit, and the input device are connected to the system bus through the input / output interface. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The input / output interface of the computer device is used to exchange information between the processor and external devices. The communication interface of the computer device is used to communicate with external terminals in a wired or wireless manner, and the wireless manner can be implemented through WIFI, a mobile cellular network, NFC (Near Field Communication), or other technologies. When the computer program is executed by the processor, it implements a method for converting architecture model data of an aero-engine. The display unit of the computer device is used to form a visually visible picture, which can be a display screen, a projection device, or a virtual reality imaging device. The display screen can be a liquid crystal display screen or an electronic ink display screen. The input device of the computer device can be a touch layer covering the display screen, or a button, a trackball, or a touchpad provided on the computer device housing, or an external keyboard, touchpad, or mouse, etc.

[0119] Those skilled in the art can understand that Figure 14 the structure shown in the figure is only a block diagram of some structures related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine some components, or have different component arrangements.

[0120] In an exemplary embodiment, a computer device is provided, including a memory and a processor. A computer program is stored in the memory, and when the processor executes the computer program, any step in the embodiment of the method for converting architecture model data of an aero-engine as described above is implemented.

[0121] In an embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by the processor, any step in the embodiment of the method for converting architecture model data of an aero-engine as described above is implemented.

[0122] In an embodiment, a computer program product is provided, including a computer program. When the computer program is executed by the processor, any step in the embodiment of the method for converting architecture model data of an aero-engine as described above is implemented.

[0123] It should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data for analysis, stored data, displayed data, etc.) involved in this application are all information and data authorized by the user or fully authorized by all parties, and the collection, use, and processing of relevant data need to comply with relevant regulations.

[0124] Those of ordinary skill in the art can understand that all or part of the processes in the methods of the above embodiments can be completed by instructing relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above methods. Among them, any reference to a memory, database, or other medium used in the embodiments provided in this application can include at least one of non-volatile and volatile memories. Non-volatile memory can include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random-access memory (ReRAM), magnetoresistive random-access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc. Volatile memory can include random access memory (RAM) or external cache memory, etc. By way of illustration and not limitation, RAM can be in various forms, such as static random access memory (SRAM) or dynamic random access memory (DRAM), etc. The databases involved in the embodiments provided in this application can include at least one of relational databases and non-relational databases. Non-relational databases can include distributed databases based on blockchain, etc., without limitation. The processors involved in the embodiments provided in this application can be general-purpose processors, central processors, graphics processors, digital signal processors, programmable logic devices, data processing logics based on quantum computing, etc., without limitation.

[0125] The technical features of the above embodiments can be combined arbitrarily. For the sake of brevity of description, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, it should be considered to be within the scope described in this specification.

[0126] The above embodiments merely illustrate several implementation manners of the present application. The description thereof is relatively specific and detailed, but it should not be construed as a limitation to the patent scope of the present application. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present application, several variations and improvements can still be made, and these all belong to the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the appended claims.

Claims

1. A method for converting architecture model data of an aircraft engine, characterized in that: The method comprises: The hierarchical relationship and structural relationship in the initial model are mapped to the model in the target format to obtain the mapped initial conversion model, wherein the initial model is an architecture model constructed based on the SysML language; the hierarchical relationship represents the dependency relationship between the components and the aircraft engine, and the dependency relationship between the components and the components; wherein the components are the constituent units of the aircraft engine, and the components are the constituent units of the components; the structural relationship represents the connection relationship between the components, and the connection relationship between the components constituting the same component; Determining a parts list including each of the parts constituting the initial model; The target format structural description data is matched for each component in the component list, and the structural description data is written into the initial conversion model to obtain a target conversion model.

2. The method according to claim 1, characterized in that The process of constructing the initial model includes: Creating a module definition diagram, and constructing a main element, a component element, and an assembly element in the module definition diagram, wherein the main element is a module element corresponding to the aircraft engine, the component element is a module element corresponding to the component, and the assembly element is a module element corresponding to the component; Establishing a dependency association between each of the component elements and the main element, and establishing a dependency association between the component element and each of the assembly elements that depend on the component element, to construct the hierarchical relationship; Constructing an internal module diagram inside each target element, and mapping the elements corresponding to each constituent unit of the target element in the internal module diagram; the target element is a main element or a component element; Based on the structural information of the aircraft engine, establishing a connection association between the component elements that depend on the same component element, and establishing a connection association between the component elements, so as to construct the structural relationship; The initial model is constructed based on the hierarchical relationship and the structural relationship.

3. The method according to claim 2, characterized in that The step of establishing a connection association between the component elements that are dependent on the same component element, and establishing a connection association between the component elements, includes: Adding a proxy port for each of the component elements, and adding a proxy port for each of the part elements; The proxy ports of the component elements are connected via a connector, and the proxy ports of the part elements are connected via the connector.

4. The method according to claim 1, characterized in that The component list includes the identity of each component, and the structure description data matching the target format for each component in the component list includes: For each component in the component list, based on the identity identifier of the component, the structural description data corresponding to the component is matched from a structural model library; the structural model library includes the correspondence between the structural description data of each component and the identity identifier.

5. The method according to claim 1 or 4, characterized in that: The structural description data at least includes attribute definition, geometric features and size parameters; the target format is XML format.

6. The method according to claim 2, characterized in that The step of writing the structure description data into the initial conversion model comprises: For each of the components, determining a target position of the component element corresponding to the component in the initial transformation model; The original data corresponding to the target position is replaced with the structure description data.

7. A conversion device for architecture model data, characterized in that: The device comprises a mapping module, a list determination module and a data matching module, wherein: A mapping module is used to map the hierarchical relationship and structural relationship in the initial model to the model in the target format to obtain the mapped initial conversion model, wherein the initial model is an architecture model constructed based on the SysML language; the hierarchical relationship represents the dependency relationship between the component and the aircraft engine, and the dependency relationship between the component and the component; wherein the component is a constituent unit of the aircraft engine, and the component is a constituent unit of the component; the structural relationship represents the connection relationship between the components, and the connection relationship between the components constituting the same component; A list determination module, used to determine a parts list including each of the parts constituting the initial model; The data matching module is used to match the structure description data in the target format for each component in the component list, and write the structure description data into the initial conversion model to obtain the target conversion model.

8. A computer device comprising a memory and a processor, wherein the memory stores a computer program, wherein: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 6 are implemented.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

10. A computer program product, comprising a computer program, characterized in that When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

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