An Integrated Simulation Modeling Method for Digital Twin Models of Airfoil Structures

Abstract

This invention proposes an integrated simulation modeling method for digital twin models of wing structures, belonging to the field of structural modeling and simulation. It includes: constructing a tree-like integrated simulation framework for the wing, encapsulating multi-level simulation models of the wing, online integrated simulation of the wing structure, structural performance prediction and evaluation, and updating the integrated simulation model. This invention expands upon the construction of a multi-level wing model, building a tree-like integrated simulation framework based on the multi-level structural characteristics of the wing. Then, based on the open standard functional prototype interface (FMI), the multi-level wing model is unified into functional prototype unit (FMU) models. Subsequently, the FMUs are integrated in the system simulation software to establish an online integrated simulation model of the wing structure, while simultaneously predicting the mechanical response of key structural components in real time. This invention can improve the modeling efficiency of the system simulation model.

Description

Technical Field

[0001] This invention belongs to the field of structural modeling and simulation, and specifically relates to an integrated simulation modeling method for digital twin models of wing structures. Background Technology

[0002] Aircraft structures consist of numerous components. Traditional finite element method (FEM) simulation models typically possess extremely high degrees of freedom, leading to lengthy analysis and computation times. This poses a challenge to rapidly and accurately acquiring the mechanical responses of detailed structural parts and assessing aircraft structural safety using digital twin models. To address this challenge, it is necessary to fully leverage the multi-level characteristics of aircraft structures—from "whole aircraft / components to assemblies to parts"—to construct lightweight digital twin models. Generally, the whole aircraft / component level can employ simplified beam / shell models based on multi-scale analysis, enabling rapid response analysis through model simplification. For the assembly and part levels, the detailed structural responses directly depend on local boundary conditions. Directly using the full finite element method results in an excessively large number of input and output degrees of freedom, necessitating model reduction to significantly decrease the degrees of freedom for problem solving. Using the above method to establish a multi-level wing structure model enables real-time analysis of the wing structure response. However, integrated simulation after establishing multi-level models requires establishing the interrelationships and coupling between various models to achieve a unified model description and interface. Currently, different simulation models originate from different modeling and simulation methods and software, resulting in inconsistent interfaces.

[0003] Based on the Open Standard Functional Prototype Interface (FMI), standardized Functional Unit (FMU) models can be exported from different modeling and simulation software, and have been widely used in the field of integrated simulation. In 2010, the FMI standard was defined by the MODELISAR project proposed by the European Information Technology Development Program (ITEA2). This standard encapsulates models from software supporting the FMI standard into FMU models and effectively integrates them into other simulation software that supports the standard to achieve co-simulation, thus greatly improving model interactivity and reusability. Researchers have provided detailed introductions to version 1.0 of the FMI standard, including API usage, how to handle discrete events, and the design of co-simulation architectures, making significant contributions to the promotion and application of the FMI standard. Some researchers have proposed a method for packaging and integrating Co-Simulation type FMU models under the HLA architecture to achieve co-simulation with models from multiple simulation platforms with different semantics.

[0004] Once the FMI standard was proposed, domestic research began on it, but initially it did not receive much attention. Some researchers provided detailed explanations of FMI version 1.0, making significant contributions to its development and promotion in my country. Other researchers used the FMI standard to model and perform integrated simulations of hydraulic systems; still others used the domestically developed MWORKS platform by Tongyuan Soft Control to conduct integrated simulations of digital flight tracking models. Therefore, building models based on unified standards such as FMI is an effective way to achieve integrated simulations of multidisciplinary models.

[0005] Current methods for analyzing the mechanical response of airfoil structures and evaluating their structural performance lack effective integrated simulation methods, and the reuse rate of multi-level models is very low, resulting in low modeling and simulation efficiency. Therefore, there is an urgent need to develop an integrated simulation modeling method for digital twin models of airfoil structures. Summary of the Invention

[0006] To address the aforementioned technical problems, this invention provides an integrated simulation modeling method for digital twin models of wing structures. Based on the characteristics of multi-level simulation modeling of wing structures, a tree-like integrated simulation modeling framework for wing structures is proposed. The FMI standard is used to encapsulate each model and build an integrated digital twin simulation model of the wing structure, thereby improving the efficiency of model simulation. At the same time, thanks to the modularity of FMU, the versatility and development agility of the system simulation model are greatly improved.

[0007] This invention is based on multi-level reduced-order modeling of wing structures. Level 0 is a one-dimensional simplified beam model, level 1 is a unit cell model, and level 2 is a data-driven sub-model for detailed parts (multiple structural detail levels can be set according to the complexity of the model). Based on the characteristics of wing structure simulation modeling, a tree-like integrated simulation framework for wing structures is proposed. This framework can be extended to multi-level modeling applications of other complex structures, demonstrating good versatility. The multi-level models and structural performance evaluation models are encapsulated based on the FMI standard and ultimately integrated into a system simulation model, balancing model development agility and applicability. Furthermore, thanks to the modular and standardized characteristics of FMU, the utilization rate of existing models can be improved when adding new areas of interest, thereby increasing the modeling efficiency of the system simulation model.

[0008] To achieve the above objectives, the present invention adopts the following technical solution:

[0009] A method for integrated simulation modeling of a digital twin model of an airfoil structure includes the following steps:

[0010] Step 1: Construct a tree-like integrated simulation framework based on the "wing-unit cell-detailed parts" hierarchy of the wing, forming a hierarchical topological relationship. The tree-like integrated simulation framework includes: a level 0 one-dimensional simplified beam model, a level 1 unit cell model, and a level 2 detailed parts data-driven sub-model.

[0011] Step 2: Based on the open standard functional prototype interface standard, the level 0 one-dimensional simplified beam model, the level 1 unit cell model, and the level 2 detailed part data-driven sub-model are encapsulated into functional prototype units to achieve the unification of the interface of each level of model;

[0012] Step 3: Interconnect all functional prototype units step by step according to the tree-like integrated simulation framework to establish an online integrated simulation model of the wing structure and complete the real-time transmission of loads and displacements at each level.

[0013] Step 4: Based on the requirements for structural detail performance evaluation, add the necessary functional prototype units for structural performance prediction, connect them with the functional prototype units of the second-level detail parts, and complete the structural performance evaluation using structural detail loads.

[0014] Step 5: When new areas of interest or local parameter evolution occur, only the corresponding level 2 detail data-driven sub-model is retrained and a new functional prototype unit is generated and inserted under the original parent node to achieve rapid updating of the online integrated simulation model of the wing structure.

[0015] The present invention also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the steps of the above-described integrated simulation modeling method for a digital twin model of an airfoil structure.

[0016] The present invention also provides a non-transitory computer-readable storage medium storing a computer program thereon, which, when executed by a processor, implements the steps of the above-described method for integrated simulation modeling of a digital twin model of an airfoil structure.

[0017] Beneficial effects:

[0018] This invention builds upon the construction of a multi-level wing model, constructing a tree-like integrated simulation framework based on the wing structure's hierarchy. Then, using an open standard functional prototype interface (FMI), the multi-level wing model is unified into functional prototype units (FMUs). Subsequently, these FMUs are integrated in the system simulation software to establish an online integrated simulation model of the wing structure. Furthermore, based on real-time prediction of the mechanical response of key structural components, structural performance evaluation FMUs for these key components can be added to the tree-like integrated simulation framework. In addition, within this system simulation framework, each model is encapsulated according to a unified standard. If additional components of interest are needed, corresponding FMUs can be constructed separately and integrated into the simulation framework. Moreover, it facilitates updates to relevant modules in the event of component replacements or parameter evolution. Currently, wing structural mechanical response analysis and structural performance evaluation lack effective integrated simulation methods, and the reuse rate of multi-level models is very low, resulting in low modeling and simulation efficiency. This invention proposes an effective solution to this problem. Attached Figure Description

[0019] Figure 1 This is a flowchart of an integrated simulation modeling method for a digital twin model of an airfoil structure according to the present invention;

[0020] Figure 2a This is a geometric model diagram of the wing of a certain UAV.

[0021] Figure 2b This is a dimensional drawing of a drone wing model.

[0022] Figure 3 This is a schematic diagram of the tree-like integrated simulation framework for an airfoil.

[0023] Figure 4 This is a comparison of the simulated stress cloud diagrams of the front beam flange root joint sub-model obtained from the integrated simulation model and the finite element simulation model; where 'a' represents the stress in the X direction of the local coordinate system from the integrated simulation model result. Cloud diagram, b represents the stress in the X direction of the local coordinate system of the finite element model result. Cloud diagram, c represents the stress in the X direction of the local coordinate system of the integrated simulation model and the finite element model. Error contour plot, where d represents the stress in the Y-direction of the local coordinate system from the integrated simulation model results. Cloud diagram, e represents the stress in the Y direction of the local coordinate system of the finite element model result. Cloud diagram, f represents the stress in the Y direction of the local coordinate system of the integrated simulation model and the finite element model. Error contour plot, where g represents the stress in the Z-direction of the local coordinate system from the integrated simulation model results. Cloud diagram, h represents the stress in the Z-direction of the local coordinate system of the finite element model result. Cloud diagram, where i represents the stress in the Z-direction of the local coordinate system of the integrated simulation model and the finite element model. Error cloud map;

[0024] Figure 5 This is a comparison of the simulated stress cloud diagrams of the front beam-rib connection obtained from the integrated simulation model and the finite element simulation model. Figure a shows the shear force along the Z direction in the local coordinate system XY plane of the integrated simulation model results. Cloud diagram, b represents the shear force along the Z direction in the local coordinate system XY plane of the finite element model result. Cloud diagram, c represents the shear force along the Z direction in the local coordinate system XY plane of the integrated simulation model and finite element model results. Error contour plot, where d represents the shear force along the Y direction in the local coordinate system XZ plane of the integrated simulation model results. Cloud diagram, e represents the shear force along the Y direction in the local coordinate system XZ plane of the finite element model result. Cloud diagram, f represents the shear force along the Y direction in the local coordinate system XZ plane of the integrated simulation model and finite element model results. Error contour plot, where g represents the shear force along the Z direction in the local coordinate system YZ plane of the integrated simulation model results. Cloud diagram, h represents the shear force along the Z direction in the local coordinate system YZ plane of the finite element model result. Cloud diagram, where i represents the shear force along the Z-direction in the local coordinate system YZ plane of the integrated simulation model and finite element model results. Error cloud map;

[0025] Figure 6 This is a comparison of the simulated stress cloud diagrams of the rib-front beam connection at the unit cell of wing segment 10, obtained from the integrated simulation model and the finite element simulation model. Figure a shows the stress in the X-direction of the local coordinate system from the integrated simulation model results. Cloud diagram, b represents the stress in the X direction of the local coordinate system of the finite element model result. Cloud diagram, c represents the stress in the X-direction of the local coordinate system of the integrated simulation model and finite element model results. Error contour plot, where d represents the stress in the Y-direction of the local coordinate system from the integrated simulation model results. Cloud diagram, e represents the stress in the Y direction of the local coordinate system of the finite element model result. Cloud diagram, f represents the stress in the Y-direction of the local coordinate system from the integrated simulation model and finite element model results. Error contour plot, where g represents the shear force along the Z direction in the local coordinate system XY plane of the integrated simulation model results. Cloud diagram, h represents the shear force along the Z direction in the local coordinate system XY plane of the finite element model result. Cloud diagram, where i represents the shear force along the Z direction in the local coordinate system XY plane of the integrated simulation model and finite element model results. Error cloud map;

[0026] Figure 7aA comparison of the results of the integrated simulation model and the finite element calculation of the maximum paradigm equivalent stress of the front beam flange root joint;

[0027] Figure 7b A comparison of the results of the Zei-Hill criterion factor for the front beam-wing rib connection between the integrated simulation model and the finite element calculation. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of this invention clearer, the invention 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 merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0029] like Figure 1 As shown, the integrated simulation modeling method for digital twin models of wing structures of the present invention is based on multi-level simplified modeling of wing structures. Level 0 is a one-dimensional simplified beam model, Level 1 is a unit cell model, and Level 2 is a data-driven sub-model for detailed parts. The method specifically includes the following steps:

[0030] Step 1: Construction of the wing-shaped tree-like integrated simulation framework:

[0031] Based on the characteristics of the wing structure, multi-level modeling is adopted to balance simulation efficiency and accuracy. The tree-like integrated simulation framework of the wing can be divided into three levels. The entire wing is simplified into a one-dimensional simplified beam model. Then, the entire wing is divided into several structural units, each unit being the next level. Within each wing structural unit, there are several structural details. These structural details models constitute the next level, thus building the multi-level wing structure model into a tree-like integrated simulation model.

[0032] Step 2: Encapsulation of the multi-level simulation model of the wing, including:

[0033] Step 2.1, FMU construction of the 0-level one-dimensional simplified beam model:

[0034] A simplified wing beam model with reduced order was constructed using a multi-level model, and a vector interface-based FMU for the simplified wing beam was established.

[0035] ;

[0036] in, External load data is used as input; This is the column vector of element node displacements. For each wing structural unit cell (RVE), the generalized deformation matrix is ​​denoted as , and both are outputs. Here, is the stiffness matrix, and are the model parameters. The simplified beam model of the wing is constructed using the FMPy library in Python. It is encapsulated as an FMU to enable the export and sharing of existing models.

[0037] Step 2.2, FMU construction of a level 1 unit cell model:

[0038] Within the wing tree-structured integrated simulation framework, the system simulation model contains multiple reduced-order wing unit cell models. A vector interface-based flow unit (FMU) for the wing unit cell is established. The FMU established in step 2.1 can obtain the corresponding element node displacement column vectors. Further utilize the unit node displacement column vector Solving for the generalized strain of beam elements and generalized load This step can be implemented in general-purpose finite element software:

[0039] ;

[0040] ;

[0041] in, The displacement-strain transformation matrix is ​​given, where S represents the equivalent cross-sectional properties of the wing unit cell. Then, a generalized load is applied to the beam element containing the target unit cell. and required external load (Including structural self-weight, distributed aerodynamic forces, etc.), finite element analysis can be performed to obtain the actual deformation of the target unit cell.

[0042] With generalized deformation matrix and external load data For input, the following are the R-order orthogonal eigenvalue (POD) coefficient vectors of the boundary conditions for each sub-model. The output is the mode vector of the first R-order POD. For model parameters, This indicates the order of principal components in the POD model. The FMPy library in Python is used to convert the wing unit cell model... Encapsulated as an FMU, enabling export and sharing, as shown in the following formula:

[0043] ;

[0044] Subsequently, The POD approximation of the boundary conditions can then be obtained. As shown in the following formula:

[0045] ;

[0046] Step 2.3, FMU construction of data-driven sub-models for 2-level details:

[0047] Within the tree-like integrated simulation framework of the wing, each wing unit cell contains multiple critical structural components, such as areas prone to stress concentration and structural damage. In this embodiment, the wing root front spar joint and the wing rib-front spar connection are selected as critical components for modeling and analysis. The sub-model boundary condition POD coefficient vector is used. As input, the stress field of each key component is used as the input. POD coefficient vector of order Output, model parameters are the first Modal vectors of order POD We built a Functional Model (FMU) for the key structural components and used the FMPy library in Python to drive the sub-model with data from the detailed components. Encapsulated as an FMU, enabling export and sharing, as shown in the following formula:

[0048] ;

[0049] Subsequently, the POD approximation of the key parts can be obtained. As shown in the following formula:

[0050] ;

[0051] Where r is the order.

[0052] Step 3: Integrated simulation of the wing structure model:

[0053] Step 1 establishes a tree-like integrated simulation framework for the wing. Step 2 constructs various FMUs for the multi-level wing model. Different FMUs can be assembled as subsystems in integrated simulation tools such as Simulink and Dymola. Finally, an online integrated simulation model of the wing structure is established to achieve real-time prediction of structural details.

[0054] Step 4: Online prediction of performance of structural details:

[0055] Step 3 has established an online integrated simulation model of the wing structure, which can quickly and accurately obtain the mechanical response of the structural details. Thanks to the agility of the system simulation framework development, more FMUs can be added to the online integrated simulation model of the wing structure, which can then be provided to other subsequent analysis models, such as strength criterion models and fracture mechanics models, to quickly achieve the prediction and evaluation of structural performance.

[0056] Step 5: Integrated simulation model update:

[0057] Under the wing tree-like integrated simulation framework proposed in this invention, due to the use of clearly defined interlayer relationships, for newly added areas of interest during online use, the parent node can be found more easily, and the model can be quickly modeled and supplemented. For example, if structural damage is found in a certain wing segment and it is identified as a critical damaged area, the wing segment of interest can be quickly located. The model above the parent node does not need to be remodeled. Then, the reduced-order model of the critical area is retrained and encapsulated as an FMU, which is inserted under the corresponding parent node to quickly realize the modeling of critical parts and the rapid updating of the online integrated simulation model of the wing structure.

[0058] Example:

[0059] In this embodiment, integrated simulation modeling is performed on a multi-level wing model of a UAV. The wing length in the model is 3.6m, and the load on each wing is approximately 4kg. The wing mainly consists of a main sparsity, a rear sparsity, and ribs, all made of T300 composite material. The skin is made of polypropylene film. The wing model is as follows: Figure 2a , Figure 2b As shown, d=730mm is the wing chord length, L=3490mm is the span of the selected wing, and RVE10 represents the unit cell number of the wing structure.

[0060] Based on the characteristics of multi-level modeling of wing structures, the wing was divided into 13 wing structure units according to the wing box during modeling, forming a tree-like integrated simulation framework for the wing, as shown below. Figure 3 As shown, it includes a 0-level one-dimensional simplified beam model, a 1-level unit cell model, a 2-level detailed part data-driven sub-model, and finally sets the strength criterion.

[0061] In this embodiment, the input and output interfaces of the online integrated simulation model of the wing structure are directly defined as matrices. The input of the level 0 one-dimensional simplified beam model is the average load acting on each wing unit cell, which is a... The matrix outputs the generalized internal forces actually experienced by each wing unit cell, which is a single matrix. The matrix, while also outputting the simplified nodal displacement field of the beam, is used to observe the overall response of the structure, and is a... The matrix. After extracting the components of the generalized internal force matrix, the predicted FMU for the boundary condition POD coefficients of the sub-model can be provided. Taking the front beam flange root joint as an example, the POD coefficients can be obtained. The dimension vector is then provided to the prediction FMU of the deformation POD coefficients of the sub-model to obtain the final POD coefficients of the joint end face deformation field. The dimensional matrix is ​​then used to recover the deformed field.

[0062] The input to the online integrated simulation model of the wing structure built in Simulink is the sequence of external loads borne by the wing, including lift, drag, gravity, and inertial forces. The external load data is... The entire wing structure's online integrated simulation model consists of multiple beam elements, under which multiple sub-models can be integrated. The input to the FMU of the level 0 one-dimensional simplified beam is external load data. The output is the column vector of element node displacements and the generalized deformation matrix of each RVE. The input of the FMU for the 1-level unit cell model is the generalized deformation vector and the external load vector, and the output is the boundary condition POD coefficient vector of each sub-model. The input to the FMU of the two-level detailed part data-driven sub-model is the boundary condition POD coefficient vector of the sub-model, and the output is the POD coefficient vector of the stress field of the critical parts. Based on the online integrated simulation model of the wing structure, the stress field of the critical parts can be quickly recovered, and then provided to other subsequent analysis models, such as strength criterion models and fracture mechanics models.

[0063] In this embodiment, uniformly distributed pressure is used to simplify the load borne by the wing. The results are compared between the wing root front spars joint and the wing rib-front spars connection at the unit cell of wing segment 10. Figure 4 , Figure 5 , Figure 6 As shown, the POD coefficients calculated from the integrated simulation model can effectively recover the deformation field of the wing structure of interest. Among them, Figure 4 'a' represents the stress contour plot in the X-direction of the local coordinate system from the integrated simulation model results. Figure 4 b represents the stress contour plot in the X-direction of the local coordinate system from the finite element model results. Figure 4 c represents the stress error contour plot in the X direction of the local coordinate system of the integrated simulation model and the finite element model. Figure 4 d represents the stress contour plot in the Y-direction of the local coordinate system from the integrated simulation model results. Figure 4 'e' represents the stress contour plot in the Y-direction of the local coordinate system from the finite element model results. Figure 4 f represents the stress error contour plot in the Y direction of the local coordinate system of the integrated simulation model and the finite element model. Figure 4 g represents the stress contour plot in the Z-direction of the local coordinate system from the integrated simulation model results. Figure 4 h represents the stress contour plot in the Z-direction of the local coordinate system from the finite element model results. Figure 4 i represents the stress error cloud diagram in the Z direction of the local coordinate system of the integrated simulation model and the finite element model; Figure 5 'a' represents the shear force contour plot along the Z direction in the local coordinate system XY plane of the integrated simulation model results. Figure 5 b represents the shear force contour plot along the Z direction in the local coordinate system XY plane of the finite element model results. Figure 5c represents the shear force error contour plot along the Z direction in the local coordinate system XY plane of the integrated simulation model and finite element model results. Figure 5 d represents the shear force contour plot along the Y direction in the local coordinate system XZ plane of the integrated simulation model results. Figure 5 'e' represents the shear force contour plot along the Y direction in the local coordinate system XZ plane of the finite element model results. Figure 5 f is the shear force error contour plot along the Y direction in the local coordinate system XZ plane of the integrated simulation model and finite element model results. Figure 5 'g' represents the shear force contour plot along the Z direction in the local coordinate system YZ plane of the integrated simulation model results. Figure 5 h represents the shear force contour plot along the Z direction in the local coordinate system YZ plane of the finite element model results. Figure 5 i represents the shear force error contour plot along the Z direction in the local coordinate system YZ plane of the integrated simulation model and finite element model results; Figure 6 'a' represents the stress contour plot in the X-direction of the local coordinate system from the integrated simulation model results. Figure 6 b represents the stress contour plot in the local coordinate system X direction of the finite element model results. Figure 6 c represents the stress error contour plot in the local coordinate system X direction of the integrated simulation model and finite element model results. Figure 6 d represents the stress contour plot in the local coordinate system Y direction of the integrated simulation model results. Figure 6 'e' represents the stress contour plot in the Y-direction of the local coordinate system of the finite element model results. Figure 6 f is the stress error contour plot in the local coordinate system Y direction of the integrated simulation model and finite element model results. Figure 6 'g' represents the shear force contour plot along the Z direction in the local coordinate system XY plane of the integrated simulation model results. Figure 6 h represents the shear force contour plot along the Z direction in the local coordinate system XY plane of the finite element model results. Figure 6 'i' represents the shear force error contour plot along the Z direction in the local coordinate system XY plane of the integrated simulation model and finite element model results.

[0064] Based on accurate deformation results of the wing structure of interest, existing empirical strength criteria can be used for structural safety assessment. By adding a decision FMU (Focus Unit) to the online integrated simulation model of the wing structure, an alarm can be triggered when the stress level of the recovered stress field at the interest location reaches the strength criterion limit. For the front spars-wing rib connection, which is a composite material layup, the Zei-Hill criterion is used. For the front spars wing root joint, which is an isotropic metallic material, the maximum normal equivalent stress is selected as the judgment quantity.

[0065] To verify the simulation efficiency and safety assessment accuracy of the integrated simulation model, the aforementioned pressure load was set as a time-varying random sequence within twice the range of the aforementioned load conditions. The average error between the maximum normal equivalent stress at the front beam wing root joint and the finite element results was 0.35%, and the average error of the Zei-Hill criterion factor for the front beam-wing rib connection sub-model was 3.97%. The results are comparable to... Figure 7a , Figure 7b As shown, the simulation results of the integrated model are in good agreement with the finite element method. It can be seen that the equivalent stress value of the paradigm reaches the strength limit in some time periods. At this time, the integrated simulation model can provide an early warning and take measures to reduce the stress level.

[0066] In terms of analysis speed, the online integrated simulation model of the wing structure greatly reduces the number of degrees of freedom, thereby reducing the time spent on integrated simulation. In this embodiment, the full-size finite element model has 6,505,719 degrees of freedom, and each analysis step takes 596.1 seconds. The established digital twin integrated simulation model has 2,192 degrees of freedom, and each analysis step takes 0.062 seconds, which greatly improves the simulation efficiency.

[0067] The present invention also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the steps of the above-described integrated simulation modeling method for a digital twin model of an airfoil structure.

[0068] The present invention also provides a non-transitory computer-readable storage medium storing a computer program thereon, which, when executed by a processor, implements the steps of the above-described method for integrated simulation modeling of a digital twin model of an airfoil structure.

[0069] Those skilled in the art will understand that embodiments of the present invention can be provided as methods, systems, or computer program products. Therefore, the present invention can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present invention can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code. The solutions in the embodiments of the present invention can be implemented using various computer languages, such as the object-oriented programming language Java and the interpreted scripting language JavaScript.

[0070] This invention is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart illustrations and / or block diagrams. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0071] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0072] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0073] Although preferred embodiments of the invention have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the invention.

[0074] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

Claims

1. A method for integrated simulation modeling of digital twin models of airfoil structures, characterized in that, Includes the following steps: Step 1: Construct a tree-like integrated simulation framework based on the "wing-unit cell-detailed parts" hierarchy of the wing, forming a hierarchical topological relationship. The tree-like integrated simulation framework includes: a level 0 one-dimensional simplified beam model, a level 1 unit cell model, and a level 2 detailed parts data-driven sub-model. Step 2: Based on the open standard functional prototype interface standard, the level 0 one-dimensional simplified beam model, the level 1 unit cell model, and the level 2 detailed part data-driven sub-model are encapsulated into functional prototype units to achieve the unification of the interface of each level of model; Step 3: Interconnect all functional prototype units step by step according to the tree-like integrated simulation framework to establish an online integrated simulation model of the wing structure and complete the real-time transmission of loads and displacements at each level. Step 4: Based on the requirements for structural detail performance evaluation, add the necessary functional prototype units for structural performance prediction, connect them with the functional prototype units of the second-level detail parts, and complete the structural performance evaluation using structural detail loads. Step 5: When new areas of interest or local parameter evolution occur, only the corresponding level 2 detail data-driven sub-model is retrained and a new functional prototype unit is generated and inserted under the original parent node to achieve rapid updating of the online integrated simulation model of the wing structure.

2. The integrated simulation modeling method for a digital twin model of an airfoil structure as described in claim 1, characterized in that, Step 1 involves simplifying the entire wing into a one-dimensional beam and dividing it into several unit cells, then specifying several detailed parts within each unit cell to form a multi-layered tree structure.

3. The integrated simulation modeling method for a digital twin model of an airfoil structure as described in claim 1, characterized in that, Step 2 uses the Python FMPy library to export the models at each level as functional prototype unit files.

4. The integrated simulation modeling method for a digital twin model of an airfoil structure as described in claim 1, characterized in that, Step 2 includes establishing a functional prototype unit of the wing cell based on a vector interface, based on multiple reduced-order wing cell models.

5. The integrated simulation modeling method for a digital twin model of an airfoil structure as described in claim 1, characterized in that, In step 4, a prototype module for strength criterion function is added to the key parts of the structure to achieve real-time safety assessment.

6. The integrated simulation modeling method for a digital twin model of an airfoil structure as described in claim 1, characterized in that, The local parameter evolution in step 5 includes material degradation, geometric damage, or component replacement.

7. The integrated simulation modeling method for a digital twin model of an airfoil structure as described in claim 1, characterized in that, In step 5, during the update, keep the model above the parent node unchanged, and only replace or add child node functional prototype units.

8. The integrated simulation modeling method for a digital twin model of an airfoil structure as described in claim 1, characterized in that, In step 3, the hierarchical interconnection uses a matrix to define the input and output interfaces, thereby achieving consistent data transmission between levels.

9. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the program, it implements the steps of the integrated simulation modeling method for digital twin models of wing structures as described in any one of claims 1 to 8.

10. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the steps of the integrated simulation modeling method for a digital twin model of a wing structure as described in any one of claims 1 to 8.

Images