An airfoil strength evaluation method and device based on a strength database, an apparatus, and a storage medium

Abstract

This application discloses a method, apparatus, device, and storage medium for wing strength assessment based on a strength database, relating to the field of aircraft structural strength analysis technology. The method includes: dividing the aerodynamic shape data of the wing to be assessed into several mesh elements; mapping and grouping each mesh node to obtain an initial wing skeleton model; calling a preset strength database to assign material and structural properties to the skeleton model and the initial skin model respectively, obtaining a first wing skeleton model and a first skin model; applying aerodynamic loads and boundary constraints to the first skin model and the first wing skeleton model respectively using preset load cards, obtaining a second skin model and a second wing skeleton model; obtaining the model weight to construct a model file; performing simulation calculations through a solver to obtain a result file; extracting stress-strain, wingtip deformation, modal frequency, and element force information for strength assessment, obtaining the corresponding assessment results, thereby improving the efficiency of wing strength assessment.

Description

Technical Field

[0001] This invention relates to the field of aircraft structural strength analysis technology, and in particular to a method, apparatus, equipment and storage medium for wing surface strength assessment based on a strength database. Background Technology

[0002] Currently, in recent years, with the rapid penetration of the drone industry into multiple application scenarios (such as logistics, surveying and mapping, and emergency rescue), users' demands for differentiated drone performance have continued to increase. This has directly driven technological breakthroughs in drone design in terms of lightweighting, high performance, and low cost. However, traditional aerospace structural strength analysis methods have gradually revealed their limitations: 1. Reliance on complete structural models: Existing parametric modeling techniques typically require existing 3D digital models or detailed structural designs as input (such as CAD models). However, in actual R&D processes, the prototyping design of wing structures (such as skeleton layout, skin thickness, etc.) often requires multiple iterations and modifications, making it impossible for traditional parametric modeling to intervene in the early stages of design, thus failing to form a serial "design-modeling-analysis" process and extending the R&D cycle.

[0003] 2. Inefficiency of manual modeling and analysis: Traditional strength analysis relies on engineers manually building finite element models and setting material properties, boundary conditions, and load cases item by item. Furthermore, each structural modification requires remodeling, resulting in high iteration costs. Traditional analysis methods also rely on human experience and judgment, making it difficult to avoid human oversights and calculation errors, leading to rework in the design process.

[0004] 3. Collaboration barriers in the design phase: In the early stages of aircraft design (such as the conceptual design phase), structural parameters are not yet fully determined. Traditional methods, lacking structural models, cannot perform strength assessments, leading to a disconnect between structural design and strength analysis. This results in a passive "design first, analyze later" approach, where, after strength calculations are completed, modifications to unsatisfactory parts are subject to overall constraints, incurring significant costs. Furthermore, for disruptive strength issues, the entire design may need to be scrapped and restarted, greatly extending the development cycle.

[0005] As can be seen from the above, how to improve the efficiency of wing strength assessment in the process of wing strength assessment based on strength database is an urgent problem to be solved. Summary of the Invention

[0006] In view of this, the purpose of this invention is to provide a method, apparatus, device, and storage medium for wing strength evaluation based on a strength database, which can improve the efficiency of wing strength evaluation in the process of wing strength evaluation based on a strength database. The specific solution is as follows: Firstly, this application provides a method for evaluating airfoil strength based on a strength database, including: The aerodynamic shape data of the wing surface to be evaluated is divided into several target grid cells; the lines connecting the grid nodes corresponding to the upper and lower wing surfaces in the target grid cells are perpendicular to the chord plane of the wing surface. Based on preset structural layout parameters, each grid node in the target grid cell is mapped and grouped to obtain an initial wing skeleton model. The preset strength database is called to determine the material properties and structural properties corresponding to the initial wing skeleton model and the initial skin model, respectively, so as to obtain the corresponding first wing skeleton model and first skin model. A pre-set load is applied to the first skin model to obtain a second skin model. Boundary constraints are applied to the first wing skeleton model to obtain a second wing skeleton model. Then, the model weight corresponding to the aerodynamic shape data of the wing to be processed is obtained. A model file is constructed based on the second skin model, the second wing skeleton model, and the model weight. The model file is then simulated using a solver to obtain a result file. Then, the information to be evaluated, including stress and strain data, wingtip deformation, modal frequency, and element force information, is extracted from the result file. The information to be evaluated is then subjected to strength evaluation to obtain a strength evaluation result corresponding to the aerodynamic shape data of the wing to be evaluated.

[0007] Optionally, dividing the aerodynamic shape data of the wing surface to be evaluated into several target grid cells includes: Acquire the aerodynamic shape data of the airfoil to be evaluated corresponding to the airfoil to be evaluated, and use a preset mesh generation technology to perform mesh generation on the aerodynamic shape surface corresponding to the aerodynamic shape data of the airfoil to be evaluated to obtain the initial mesh unit. Each mesh node corresponding to the initial mesh element is determined, and the node connection line between each mesh node corresponding to the upper and lower wing surfaces of the wing to be evaluated is kept perpendicular to the chord plane to obtain the corresponding target mesh elements.

[0008] Optionally, the step of mapping and grouping each grid node in the target grid cell based on preset structural layout parameters to obtain an initial airfoil skeleton model includes: Based on preset structural layout parameters, a node search is performed on each grid node in the target grid cell to obtain the grid nodes to be mapped corresponding to the upper and lower wing surfaces, respectively; the preset structural layout parameters include the arrangement positions of beams and ribs and the joint coordinates of the wing surface to be evaluated. Each of the mesh nodes to be mapped is mapped to obtain a mapping result, and a corresponding geometric axis is generated based on the mapping result. Then, based on the skeleton type of the wing surface to be evaluated, the cross-sectional shape and grouping identifier corresponding to the geometric axis are determined to generate an initial wing surface skeleton model based on the geometric axis, the cross-sectional shape and the grouping identifier.

[0009] Optionally, the step of calling a preset strength database to determine the material and structural properties corresponding to the initial wing frame model and the initial skin model, respectively, to obtain the corresponding first wing frame model and first skin model, includes: Determine the attribute numbers corresponding to the initial wing skeleton model and the initial skin model, and determine the database type based on the attribute numbers; the database type includes a material property database, a composite ply equivalent parameter database, a stiffener equivalent parameter database, and a sandwich structure equivalent parameter database; Based on the database type, a corresponding target strength database is determined, and corresponding data rows are determined in the target strength database. The corresponding material constants, equivalent elastic modulus, ply sequence, stiffener cross-sectional parameters, and core layer parameters are read from each data row. Then, based on the material constants, the equivalent elastic modulus, the ply sequence, the stiffener cross-sectional parameters, the core layer parameters, the initial wing skeleton model, and the initial skin model, the corresponding first wing skeleton model and first skin model are constructed respectively.

[0010] Optionally, the step of applying aerodynamic loads to the first skin model using a preset load card to obtain a second skin model, and applying boundary constraints to the first wing frame model to obtain a second wing frame model, includes: The actual operating conditions of the wing surface corresponding to the wing surface to be evaluated are determined, and aerodynamic analysis is performed on the actual operating conditions of the wing surface to obtain aerodynamic analysis results. Then, the load distribution is determined from the aerodynamic analysis results, and the load distribution is applied to the first skin model in a preset load card format to obtain the second skin model; the load distribution includes pressure distribution, concentrated force and torque. Displacement and rotation constraints are applied to the root of the first wing skeleton model to obtain the second wing skeleton model.

[0011] Optionally, a model file is constructed based on the second skin model, the second wing frame model, and the model weight. A solver is then used to perform simulation calculations on the model file to obtain a result file. Finally, evaluation information, including stress-strain data, wingtip deformation, modal frequencies, and element force information, is extracted from the result file. Determine the first model information and the second model information corresponding to the second skin model and the second wing frame model respectively, and construct a model file based on the first model information, the second model information and the model weight; The model file is simulated using a solver to obtain a result file, and the structure type corresponding to the result file is determined. If the structure type is a metallic structure, stress data including von Mises stress is extracted from the result file. If the structure type is a composite material structure, strain data is extracted from the result file. The strain data includes the maximum principal strain, the minimum principal strain, and the maximum shear strain. The wingtip deformation, modal frequency, and corresponding mode shape of the wingtip of the airfoil to be evaluated in three directions are extracted from the result file. Then, the element force information, including axial force, shear force, bending moment, and torque, corresponding to the airfoil to be evaluated is determined.

[0012] Optionally, the step of performing an intensity assessment on the information to be evaluated to obtain an intensity assessment result corresponding to the aerodynamic shape data of the wing surface to be evaluated includes: The stress data in the information to be evaluated is evaluated based on the first allowable value in the strength design criterion to obtain the corresponding first overall static strength analysis evaluation result, and the strain data in the information to be evaluated is evaluated using the second allowable value in the strength design criterion to obtain the corresponding second overall static strength analysis evaluation result. The wingtip deformation is evaluated based on the deformation range in the strength design criteria to obtain the corresponding overall stiffness analysis evaluation results. The modal frequencies are evaluated based on the frequency range in the strength design criteria to obtain the corresponding preliminary modal evaluation results. The buckling safety margin corresponding to each element force information is determined by using a preset stability analysis program based on model type, boundary conditions and material properties. Then, the buckling safety margin is evaluated to obtain the corresponding stability evaluation results.

[0013] Secondly, this application provides a wing strength evaluation device based on a strength database, comprising: The aerodynamic shape data partitioning module is used to divide the aerodynamic shape data of the airfoil to be evaluated into several target grid cells; the lines connecting the grid nodes corresponding to the upper and lower airfoils in the target grid cells are perpendicular to the chord plane of the airfoil. The wing skeleton model generation module is used to perform up-down mapping and grouping of each grid node in the target grid cell based on preset structural layout parameters to obtain an initial wing skeleton model. The attribute determination module is used to call a preset strength database to determine the material properties and structural properties corresponding to the initial wing skeleton model and the initial skin model, respectively, so as to obtain the corresponding first wing skeleton model and first skin model. The model weight determination module is used to apply aerodynamic loads to the first skin model using a preset load card to obtain the second skin model, and to apply boundary constraints to the first wing skeleton model to obtain the second wing skeleton model. Then, it obtains the model weight corresponding to the aerodynamic shape data of the wing to be processed. The strength assessment result generation module is used to construct a model file based on the second skin model, the second wing skeleton model and the model weight, and to perform simulation calculations on the model file using a solver to obtain a result file. Then, it extracts the information to be evaluated, including stress and strain data, wingtip deformation, modal frequency and element force information, from the result file, performs strength assessment on the information to be evaluated, and obtains the strength assessment result corresponding to the aerodynamic shape data of the wing to be evaluated.

[0014] Thirdly, this application provides an electronic device, comprising: Memory, used to store computer programs; A processor is used to execute the computer program to implement the aforementioned wing strength assessment method based on a strength database.

[0015] Fourthly, this application provides a computer-readable storage medium for storing a computer program, wherein the computer program, when executed by a processor, implements the aforementioned wing strength assessment method based on a strength database.

[0016] As can be seen from the above, before conducting the airfoil strength assessment based on the strength database, this application needs to divide the aerodynamic shape data of the airfoil to be assessed into several target mesh elements; the lines connecting the mesh nodes corresponding to the upper and lower airfoils in the target mesh elements are perpendicular to the chord plane of the airfoil; based on the preset structural layout parameters, the mesh nodes in the target mesh elements are mapped and grouped to obtain the initial airfoil skeleton model; the preset strength database is called to determine the material properties and structural properties corresponding to the initial airfoil skeleton model and the initial skin model, respectively, to obtain the corresponding first airfoil skeleton model and first skin model; using preset loads... Aerodynamic loads are applied to the first skin model to obtain the second skin model. Boundary constraints are then applied to the first airfoil skeleton model to obtain the second airfoil skeleton model. The model weight corresponding to the aerodynamic shape data of the airfoil to be processed is then obtained. A model file is constructed based on the second skin model, the second airfoil skeleton model, and the model weight. The model file is then simulated using a solver to obtain a result file. The information to be evaluated, including stress and strain data, wingtip deformation, modal frequencies, and element force information, is then extracted from the result file. The strength of the information to be evaluated is then assessed to obtain the strength assessment result corresponding to the aerodynamic shape data of the airfoil to be evaluated.

[0017] Therefore, this application first requires dividing the aerodynamic shape data of the wing surface to be evaluated into several target mesh elements; the lines connecting the mesh nodes corresponding to the upper and lower wing surfaces in the target mesh elements are perpendicular to the chord plane of the wing surface; secondly, based on the preset structural layout parameters, the mesh nodes in the target mesh elements are mapped and grouped to obtain the initial wing frame model; the preset strength database is called to determine the material properties and structural properties corresponding to the initial wing frame model and the initial skin model, respectively, to obtain the corresponding first wing frame model and first skin model; then, the preset load is applied to the first skin model. Aerodynamic loads are applied to the first wing frame model to obtain a second skin model. Boundary constraints are then applied to the first wing frame model to obtain a second wing frame model. The model weight corresponding to the aerodynamic shape data of the wing to be processed is then obtained. Finally, a model file is constructed based on the second skin model, the second wing frame model, and the model weight. A solver is used to perform simulation calculations on the model file to obtain a result file. Then, the evaluation information, including stress-strain data, wingtip deformation, modal frequencies, and element force information, is extracted from the result file. Strength evaluation is performed on this information to obtain the strength evaluation result corresponding to the aerodynamic shape data of the wing to be evaluated. This improves the efficiency of wing strength evaluation based on a strength database, thereby enhancing the user experience. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0019] Figure 1 This is a flowchart of a wing strength assessment method based on a strength database disclosed in this application; Figure 2 This application discloses a specific method for evaluating wing strength based on a strength database. Figure 3 This is a schematic diagram illustrating the content hierarchy of a specific intensity database disclosed in this application; Figure 4 This is a schematic diagram illustrating a specific process for parametric modeling disclosed in this application; Figure 5 This is a schematic diagram of a specific process for automated strength analysis disclosed in this application; Figure 6 This is a schematic diagram of the structure of a wing strength evaluation device based on a strength database disclosed in this application; Figure 7 This is a structural diagram of an electronic device disclosed in this application. Detailed Implementation

[0020] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] Currently, in recent years, with the rapid penetration of the drone industry into multiple application scenarios, users' demands for differentiated drone performance have continued to increase. This has directly driven technological breakthroughs in drone design in terms of lightweighting, high performance, and low cost. However, traditional aerospace structural strength analysis methods have gradually revealed limitations: reliance on complete structural models; inefficiency of manual modeling and analysis; and collaborative barriers in the design phase. To address these limitations, this application provides a wing strength evaluation method based on a strength database, which improves the efficiency of wing strength evaluation during the strength database-based wing strength evaluation process.

[0022] See Figure 1 As shown, this embodiment of the invention discloses a method for evaluating airfoil strength based on a strength database, including: Step S11: Divide the aerodynamic shape data of the wing surface to be evaluated into several target grid cells; the lines connecting the grid nodes corresponding to the upper and lower wing surfaces in the target grid cells are perpendicular to the chord plane of the wing surface.

[0023] In this embodiment, a schematic diagram of the process for airfoil strength assessment based on a strength database is shown below. Figure 2 As shown: First, the aerodynamic shape of the airfoil is imported. Then, the imported aerodynamic shape is divided into a standard mesh, and the lines connecting the corresponding mesh nodes of the upper and lower airfoils are perpendicular to the chord plane of the airfoil. Specifically, the aerodynamic shape data of the airfoil to be evaluated is divided into several target mesh elements, which may include: obtaining the aerodynamic shape data of the airfoil to be evaluated corresponding to the airfoil to be evaluated, and using a preset mesh generation technique to mesh the aerodynamic shape surface corresponding to the aerodynamic shape data of the airfoil to be evaluated, to obtain initial mesh elements; determining each mesh node corresponding to the initial mesh element, and keeping the node connections between the corresponding mesh nodes of the upper and lower airfoils of the airfoil to be evaluated perpendicular to the chord plane, to obtain the corresponding target mesh elements.

[0024] Step S12: Based on the preset structural layout parameters, perform up-down mapping and grouping of each grid node in the target grid unit to obtain the initial wing skeleton model.

[0025] In this embodiment, the present application requires automatically generating a skeleton such as beams, ribs, and joints based on the input structural layout parameters. The generation method involves finding mesh nodes at the given parameter positions and generating a skeleton model through top-bottom mapping. Specifically, when generating the skeleton model, the present application groupes the skeletons according to their type and quantity. Specifically, the initial airfoil skeleton model is obtained by top-bottom mapping and grouping each mesh node in the target mesh unit based on preset structural layout parameters. This can include: performing a node search on each mesh node in the target mesh unit based on preset structural layout parameters to obtain the mesh nodes to be mapped corresponding to the upper and lower airfoils, respectively; the preset structural layout parameters include the arrangement positions of beams and ribs and the joint coordinates of the airfoil to be evaluated; mapping each mesh node to be mapped to obtain the mapping result, and generating the corresponding geometric axis based on the mapping result; then determining the cross-sectional shape and grouping identifier corresponding to the geometric axis based on the skeleton type of the airfoil to be evaluated, thereby generating the initial airfoil skeleton model based on the geometric axis, cross-sectional shape, and grouping identifier.

[0026] Step S13: Call the preset strength database to determine the material properties and structural properties corresponding to the initial wing skeleton model and the initial skin model, respectively, so as to obtain the corresponding first wing skeleton model and first skin model.

[0027] In this embodiment, based on the attribute settings of the skin and skeleton in the given parameters, the strength database is invoked to assign unit attributes to the skeleton and skin. The invocation process involves the program determining the database to be invoked based on the input sequence number, and then retrieving the data corresponding to the specified row number within that database. It is worth noting that the strength database includes a material property database, a composite ply equivalent parameter database, a stiffener equivalent parameter database, and a sandwich structure equivalent parameter database. Further, a schematic diagram of the content hierarchy of the strength database is shown below. Figure 3 As shown. Specifically, the process involves calling a preset strength database to determine the material and structural properties corresponding to the initial airfoil skeleton model and the initial skin model, respectively, to obtain the corresponding first airfoil skeleton model and first skin model. This can include: determining the attribute number corresponding to the initial airfoil skeleton model and the initial skin model, and determining the database type based on the attribute number; the database type includes a material performance database, a composite ply equivalent parameter database, a stiffener equivalent parameter database, and a sandwich structure equivalent parameter database; determining the corresponding target strength database based on the database type, identifying the corresponding data rows in the target strength database, and reading the corresponding material constants, equivalent elastic modulus, ply sequence, stiffener cross-sectional parameters, and sandwich layer parameters from each data row; and then constructing the corresponding first airfoil skeleton model and first skin model based on the material constants, equivalent elastic modulus, ply sequence, stiffener cross-sectional parameters, sandwich layer parameters, and the initial airfoil skeleton model and the initial skin model.

[0028] Step S14: Apply aerodynamic loads to the first skin model using a preset load card to obtain a second skin model, and apply boundary constraints to the first wing skeleton model to obtain a second wing skeleton model. Then, obtain the model weight corresponding to the aerodynamic shape data of the wing to be processed.

[0029] In this embodiment, loads are applied to the skin unit and constraints are applied to the skeleton unit. The model weight is extracted and recorded, and the loads are given in the form of load cards. Specifically, aerodynamic loads are applied to the first skin model using preset load cards to obtain the second skin model, and boundary constraints are applied to the first airfoil skeleton model to obtain the second airfoil skeleton model. This can include: determining the actual operating conditions of the airfoil corresponding to the airfoil to be evaluated, performing aerodynamic analysis on the actual operating conditions of the airfoil to obtain aerodynamic analysis results, and then determining the load distribution from the aerodynamic analysis results to apply the load distribution to the first skin model in the format of preset load cards to obtain the second skin model; the load distribution includes pressure distribution, concentrated force, and moment; displacement constraints and rotational constraints are applied to the root of the skeleton in the first airfoil skeleton model to obtain the second airfoil skeleton model.

[0030] Step S15: Construct a model file based on the second skin model, the second wing skeleton model, and the model weight, and use a solver to perform simulation calculations on the model file to obtain a result file. Then, extract the information to be evaluated, including stress and strain data, wingtip deformation, modal frequency, and element force information, from the result file, perform strength evaluation on the information to be evaluated, and obtain the strength evaluation result corresponding to the aerodynamic shape data of the wing to be evaluated.

[0031] In this embodiment, the application requires outputting a model file, which is then submitted to a solver for simulation calculation to obtain a calculation result file. Subsequently, information such as stress and strain, wingtip deformation, main modal frequencies, and element forces are extracted from the calculation result file. This extraction process can be automated by a program, and a flowchart illustrating the parametric modeling process is shown below. Figure 4 As shown.

[0032] Specifically, a model file is constructed based on the second skin model, the second wing frame model, and the model weight. A solver is used to perform simulation calculations on the model file to obtain a result file. Then, the evaluation information, including stress-strain data, wingtip deformation, modal frequencies, and element force information, is extracted from the result file. This includes: determining the first model information and second model information corresponding to the second skin model and the second wing frame model, respectively, and constructing a model file based on the first model information, second model information, and model weight; performing simulation calculations on the model file using a solver to obtain a result file, and determining the structural type corresponding to the result file; if the structural type is a metal structure, stress data including von Mises stress is extracted from the result file; if the structural type is a composite material structure, strain data is extracted from the result file; and the wingtip deformation, modal frequencies, and corresponding mode shapes of the wingtip in three directions are extracted from the result file. Then, element force information, including axial force, shear force, bending moment, and torque, corresponding to the wingtip of the wing to be evaluated, is determined. The strain data includes the maximum principal strain, minimum principal strain, and maximum shear strain.

[0033] Subsequently, embodiments of this application require the separate performance of overall static strength analysis, overall stiffness analysis, preliminary modal assessment, and stability analysis. Figure 5This is a flowchart illustrating the process of automated strength analysis. In one specific implementation, the overall static strength analysis involves finding the output stress-strain results from the results file. Specifically, for metallic structures, the maximum von Mises stress is identified; for composite structures, the maximum principal strain, minimum principal strain, and maximum shear strain are identified. These are then compared to the allowable values ​​required by the strength design criteria; if the values ​​are below the allowable values, the requirements are met. The overall stiffness analysis involves finding the wingtip deformation results from the results file and comparing them to the allowable values ​​required by the strength design criteria; if the values ​​are below the allowable values, the requirements are met. The preliminary modal assessment involves finding the first three modes from the results file and comparing them to the modal requirements in the strength design criteria; if the modes are within the range, the requirements are met. The stability analysis involves extracting element forces from the results file and automatically calculating the safety margin based on the element type and boundary conditions using a stability analysis program.

[0034] Specifically, the strength assessment of the information to be evaluated, to obtain the strength assessment results corresponding to the aerodynamic shape data of the airfoil to be evaluated, may include: assessing the stress data in the information to be evaluated based on the first allowable value in the strength design criteria to obtain the corresponding first overall static strength analysis assessment result, and assessing the strain data in the information to be evaluated based on the second allowable value in the strength design criteria to obtain the corresponding second overall static strength analysis assessment result; assessing the wingtip deformation based on the deformation range in the strength design criteria to obtain the corresponding overall stiffness analysis assessment result, and assessing the modal frequencies based on the frequency range in the strength design criteria to obtain the corresponding preliminary modal assessment result; using a preset stability analysis program and based on the model type, boundary conditions, and material properties to determine the buckling safety margin corresponding to each element force information, and then assessing each buckling safety margin to obtain the corresponding stability assessment result.

[0035] As can be seen from the above, the embodiments of this application first need to divide the aerodynamic shape data of the wing surface to be evaluated into several target mesh elements; the lines connecting the mesh nodes corresponding to the upper and lower wing surfaces in the target mesh elements are perpendicular to the chord plane of the wing surface; secondly, based on the preset structural layout parameters, the mesh nodes in the target mesh elements are mapped and grouped to obtain the initial wing surface skeleton model; the preset strength database is called to determine the material properties and structural properties corresponding to the initial wing surface skeleton model and the initial skin model, respectively, to obtain the corresponding first wing surface skeleton model and first skin model; then, the preset load is applied to the first skin... Aerodynamic loads are applied to the model to obtain the second skin model, and boundary constraints are applied to the first airfoil skeleton model to obtain the second airfoil skeleton model. Then, the model weight corresponding to the aerodynamic shape data of the airfoil to be processed is obtained. Finally, a model file is constructed based on the second skin model, the second airfoil skeleton model, and the model weight. A solver is used to perform simulation calculations on the model file to obtain a result file. Then, the evaluation information, including stress-strain data, wingtip deformation, modal frequencies, and element force information, is extracted from the result file. Strength evaluation is performed on this information to obtain the strength evaluation result corresponding to the aerodynamic shape data of the airfoil to be evaluated. In this way, the efficiency of airfoil strength evaluation is improved in the process of airfoil strength evaluation based on a strength database, thereby enhancing the user experience.

[0036] Accordingly, see Figure 6 As shown, this application also provides a wing strength evaluation device based on a strength database, comprising: The aerodynamic shape data division module 11 is used to divide the aerodynamic shape data of the airfoil to be evaluated into several target grid cells; the lines connecting the grid nodes corresponding to the upper and lower airfoils in the target grid cells are perpendicular to the chord plane of the airfoil. The wing skeleton model generation module 12 is used to perform up-down mapping and grouping of each grid node in the target grid cell based on preset structural layout parameters to obtain an initial wing skeleton model. The attribute determination module 13 is used to call the preset strength database to determine the material properties and structural properties corresponding to the initial wing skeleton model and the initial skin model, respectively, so as to obtain the corresponding first wing skeleton model and first skin model. The model weight determination module 14 is used to apply aerodynamic loads to the first skin model using a preset load card to obtain a second skin model, and to apply boundary constraints to the first wing skeleton model to obtain a second wing skeleton model, and then obtain the model weight corresponding to the aerodynamic shape data of the wing to be processed. The strength assessment result generation module 15 is used to construct a model file based on the second skin model, the second wing frame model and the model weight, and to perform simulation calculations on the model file using a solver to obtain a result file. Then, it extracts the information to be evaluated, including stress and strain data, wingtip deformation, modal frequency and element force information, from the result file, performs strength assessment on the information to be evaluated, and obtains the strength assessment result corresponding to the aerodynamic shape data of the wing surface to be evaluated.

[0037] In some specific embodiments, the aerodynamic shape data division module 11 may specifically include: Mesh generation unit is used to acquire the aerodynamic shape data of the airfoil to be evaluated corresponding to the airfoil to be evaluated, and to perform mesh generation on the aerodynamic shape surface corresponding to the aerodynamic shape data of the airfoil to be evaluated using a preset mesh generation technology to obtain the initial mesh unit. A mesh node determination unit is used to determine each mesh node corresponding to the initial mesh unit, and to keep the node connection line between each mesh node corresponding to the upper and lower wing surfaces of the wing surface to be evaluated perpendicular to the chord plane to obtain the corresponding target mesh units.

[0038] In some specific embodiments, the wing skeleton model generation module 12 may specifically include: A node search unit is used to perform node search on each grid node in the target grid cell based on preset structural layout parameters to obtain the grid nodes to be mapped corresponding to the upper and lower wing surfaces respectively; the preset structural layout parameters include the arrangement positions of beams and ribs and joint coordinates of the wing surface to be evaluated. The mapping result generation unit is used to map each of the mesh nodes to be mapped to obtain the mapping result, and generate the corresponding geometric axis based on the mapping result. Then, based on the skeleton type of the wing surface to be evaluated, it determines the cross-sectional shape and grouping identifier corresponding to the geometric axis, so as to generate an initial wing surface skeleton model based on the geometric axis, the cross-sectional shape and the grouping identifier.

[0039] In some specific embodiments, the attribute determination module 13 may specifically include: The attribute number determination unit is used to determine the attribute number corresponding to the initial wing skeleton model and the initial skin model respectively, and to determine the database type corresponding to the attribute number; the database type includes a material property database, a composite ply equivalent parameter database, a stiffener equivalent parameter database, and a sandwich structure equivalent parameter database; The target strength database determination unit is used to determine the corresponding target strength database based on the database type, to determine the corresponding data rows in the target strength database, and to read the corresponding material constants, equivalent elastic modulus, ply sequence, stiffener cross-sectional parameters and core layer parameters from each data row. Then, based on the material constants, the equivalent elastic modulus, the ply sequence, the stiffener cross-sectional parameters and the core layer parameters, and the initial airfoil skeleton model and the initial skin model, the corresponding first airfoil skeleton model and first skin model are constructed respectively.

[0040] In some specific embodiments, the model weight determination module 14 may specifically include: The actual operating condition determination unit is used to determine the actual operating condition of the wing surface corresponding to the wing surface to be evaluated, and to perform aerodynamic analysis on the actual operating condition of the wing surface to obtain aerodynamic analysis results. Then, the load distribution is determined from the aerodynamic analysis results, and the load distribution is applied to the first skin model in a preset load card format to obtain the second skin model. The load distribution includes pressure distribution, concentrated force and torque. The constraint application unit is used to apply displacement and rotation constraints to the root of the skeleton in the first wing skeleton model to obtain the second wing skeleton model.

[0041] In some specific embodiments, the strength assessment result generation module 15 may specifically include: The model file construction unit is used to determine the first model information and the second model information corresponding to the second skin model and the second wing skeleton model respectively, and to construct a model file based on the first model information, the second model information and the model weight; The structure type determination unit is used to perform simulation calculations on the model file using a solver, obtain a result file, and determine the structure type corresponding to the result file; if the structure type is a metal structure, then stress data including von Mises stress is extracted from the result file. The strain data extraction unit is used to extract strain data from the result file if the structure type is a composite material structure, and to extract the wingtip deformation, modal frequency and corresponding mode shape of the wingtip of the airfoil to be evaluated in three directions from the result file, and then determine the element force information including axial force, shear force, bending moment and torque corresponding to the airfoil to be evaluated; the strain data includes the maximum principal strain, the minimum principal strain and the maximum shear strain.

[0042] In some specific embodiments, the strength assessment result generation module 15 may specifically include: The stress data evaluation unit is used to evaluate the stress data in the information to be evaluated based on the first allowable value in the strength design criterion to obtain the corresponding first overall static strength analysis evaluation result, and to evaluate the strain data in the information to be evaluated using the second allowable value in the strength design criterion to obtain the corresponding second overall static strength analysis evaluation result. The modal frequency evaluation unit is used to evaluate the wingtip deformation based on the deformation range in the strength design criteria to obtain the corresponding overall stiffness analysis evaluation results, and to evaluate the modal frequencies based on the frequency range in the strength design criteria to obtain the corresponding preliminary modal evaluation results. The stability assessment unit is used to determine the buckling safety margin corresponding to the force information of each element based on the preset stability analysis program, model type, boundary conditions and material properties, and then evaluate each buckling safety margin to obtain the corresponding stability assessment results.

[0043] Furthermore, embodiments of this application also disclose an electronic device, Figure 7 This is a structural diagram of an electronic device 20 according to an exemplary embodiment. The content of the diagram should not be construed as limiting the scope of this application. Specifically, the electronic device 20 may include: at least one processor 21, at least one memory 22, a power supply 23, a communication interface 24, an input / output interface 25, and a communication bus 26. The memory 22 stores a computer program, which is loaded and executed by the processor 21 to implement the relevant steps in the wing strength assessment method based on a strength database disclosed in any of the foregoing embodiments. Furthermore, the electronic device 20 in this embodiment may specifically be an electronic computer.

[0044] In this embodiment, the power supply 23 is used to provide operating voltage for each hardware device on the electronic device 20; the communication interface 24 can create a data transmission channel between the electronic device 20 and external devices, and the communication protocol it follows can be any communication protocol applicable to the technical solution of this application, and is not specifically limited here; the input / output interface 25 is used to acquire external input data or output data to the outside world, and its specific interface type can be selected according to specific application needs, and is not specifically limited here.

[0045] In addition, the memory 22, as a carrier for resource storage, can be a read-only memory, random access memory, disk or optical disk, etc. The resources stored thereon can include operating system 221, computer program 222, etc., and the storage method can be temporary storage or permanent storage.

[0046] The operating system 221 is used to manage and control the various hardware devices on the electronic device 20 and the computer program 222, which may be Windows Server, Netware, Unix, Linux, etc. In addition to including a computer program capable of performing the wing strength assessment method based on a strength database executed by the electronic device 20 as disclosed in any of the foregoing embodiments, the computer program 222 may further include computer programs capable of performing other specific tasks.

[0047] Furthermore, this application also discloses a computer-readable storage medium for storing a computer program; wherein, when the computer program is executed by a processor, it implements the aforementioned wing strength assessment method based on a strength database. Specific steps of this method can be found in the corresponding content disclosed in the foregoing embodiments, and will not be repeated here.

[0048] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since it corresponds to the method disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to in the method section.

[0049] Those skilled in the art will further recognize that the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, computer software, or a combination of both. To clearly illustrate the interchangeability of hardware and software, the components and steps of the various examples have been generally described in terms of functionality in the foregoing description. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of this application.

[0050] The steps of the methods or algorithms described in conjunction with the embodiments disclosed herein can be implemented directly by hardware, a software module executed by a processor, or a combination of both. The software module can be located in random access memory (RAM), main memory, read-only memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disk, removable disk, CD-ROM, or any other form of storage medium known in the art.

[0051] Finally, it should be noted that in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0052] The technical solutions provided in this application have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this application. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of this application. Therefore, the content of this specification should not be construed as a limitation of this application.

Claims

1. A method for evaluating airfoil strength based on a strength database, characterized in that, include: The aerodynamic shape data of the wing surface to be evaluated is divided into several target grid cells; The lines connecting the grid nodes corresponding to the upper and lower wing surfaces in the target grid cell are perpendicular to the chord plane of the wing surface. Based on preset structural layout parameters, each grid node in the target grid cell is mapped and grouped to obtain an initial wing skeleton model. The preset strength database is called to determine the material properties and structural properties corresponding to the initial wing skeleton model and the initial skin model, respectively, so as to obtain the corresponding first wing skeleton model and first skin model. A pre-set load is applied to the first skin model to obtain a second skin model. Boundary constraints are applied to the first wing skeleton model to obtain a second wing skeleton model. Then, the model weight corresponding to the aerodynamic shape data of the wing to be processed is obtained. A model file is constructed based on the second skin model, the second wing skeleton model, and the model weight. The model file is then simulated using a solver to obtain a result file. Then, the information to be evaluated, including stress and strain data, wingtip deformation, modal frequency, and element force information, is extracted from the result file. The information to be evaluated is then subjected to strength evaluation to obtain a strength evaluation result corresponding to the aerodynamic shape data of the wing to be evaluated.

2. The airfoil strength assessment method based on a strength database according to claim 1, characterized in that, The process of dividing the aerodynamic shape data of the wing surface to be evaluated into several target grid cells includes: Acquire the aerodynamic shape data of the airfoil to be evaluated corresponding to the airfoil to be evaluated, and use a preset mesh generation technology to perform mesh generation on the aerodynamic shape surface corresponding to the aerodynamic shape data of the airfoil to be evaluated to obtain the initial mesh unit. Each mesh node corresponding to the initial mesh element is determined, and the node connection line between each mesh node corresponding to the upper and lower wing surfaces of the wing to be evaluated is kept perpendicular to the chord plane to obtain the corresponding target mesh elements.

3. The airfoil strength assessment method based on a strength database according to claim 1, characterized in that, The process of mapping and grouping each grid node in the target grid cell based on preset structural layout parameters to obtain an initial wing skeleton model includes: Based on preset structural layout parameters, a node search is performed on each grid node in the target grid cell to obtain the grid nodes to be mapped corresponding to the upper and lower wing surfaces, respectively; the preset structural layout parameters include the arrangement positions of beams and ribs and the joint coordinates of the wing surface to be evaluated. Each of the mesh nodes to be mapped is mapped to obtain a mapping result, and a corresponding geometric axis is generated based on the mapping result. Then, based on the skeleton type of the wing surface to be evaluated, the cross-sectional shape and grouping identifier corresponding to the geometric axis are determined to generate an initial wing surface skeleton model based on the geometric axis, the cross-sectional shape and the grouping identifier.

4. The airfoil strength assessment method based on a strength database according to claim 1, characterized in that, The step of calling a preset strength database to determine the material and structural properties corresponding to the initial wing frame model and the initial skin model, respectively, to obtain the corresponding first wing frame model and first skin model, includes: Determine the attribute numbers corresponding to the initial wing skeleton model and the initial skin model, and determine the database type based on the attribute numbers; the database type includes a material property database, a composite ply equivalent parameter database, a stiffener equivalent parameter database, and a sandwich structure equivalent parameter database; Based on the database type, a corresponding target strength database is determined, and corresponding data rows are determined in the target strength database. The corresponding material constants, equivalent elastic modulus, ply sequence, stiffener cross-sectional parameters, and core layer parameters are read from each data row. Then, based on the material constants, the equivalent elastic modulus, the ply sequence, the stiffener cross-sectional parameters, the core layer parameters, the initial wing skeleton model, and the initial skin model, the corresponding first wing skeleton model and first skin model are constructed respectively.

5. The airfoil strength assessment method based on a strength database according to claim 1, characterized in that, The process of applying aerodynamic loads to the first skin model using a preset load card to obtain a second skin model, and applying boundary constraints to the first wing frame model to obtain a second wing frame model, includes: The actual operating conditions of the wing surface corresponding to the wing surface to be evaluated are determined, and aerodynamic analysis is performed on the actual operating conditions of the wing surface to obtain aerodynamic analysis results. Then, the load distribution is determined from the aerodynamic analysis results, and the load distribution is applied to the first skin model in a preset load card format to obtain the second skin model; the load distribution includes pressure distribution, concentrated force and torque. Displacement and rotation constraints are applied to the root of the first wing skeleton model to obtain the second wing skeleton model.

6. The airfoil strength assessment method based on a strength database according to any one of claims 1 to 5, characterized in that, The model file is constructed based on the second skin model, the second wing frame model, and the model weight. A solver is used to perform simulation calculations on the model file to obtain a result file. Then, evaluation information, including stress-strain data, wingtip deformation, modal frequencies, and element force information, is extracted from the result file, including: Determine the first model information and the second model information corresponding to the second skin model and the second wing frame model respectively, and construct a model file based on the first model information, the second model information and the model weight; The model file is simulated using a solver to obtain a result file, and the structure type corresponding to the result file is determined. If the structure type is a metallic structure, stress data including von Mises stress is extracted from the result file. If the structure type is a composite material structure, strain data is extracted from the result file. The strain data includes the maximum principal strain, the minimum principal strain, and the maximum shear strain. The wingtip deformation, modal frequency, and corresponding mode shape of the wingtip of the airfoil to be evaluated in three directions are extracted from the result file. Then, the element force information, including axial force, shear force, bending moment, and torque, corresponding to the airfoil to be evaluated is determined.

7. The airfoil strength assessment method based on a strength database according to claim 6, characterized in that, The step of performing an intensity assessment on the information to be evaluated to obtain an intensity assessment result corresponding to the aerodynamic shape data of the wing surface to be evaluated includes: The stress data in the information to be evaluated is evaluated based on the first allowable value in the strength design criterion to obtain the corresponding first overall static strength analysis evaluation result, and the strain data in the information to be evaluated is evaluated using the second allowable value in the strength design criterion to obtain the corresponding second overall static strength analysis evaluation result. The wingtip deformation is evaluated based on the deformation range in the strength design criteria to obtain the corresponding overall stiffness analysis evaluation results. The modal frequencies are evaluated based on the frequency range in the strength design criteria to obtain the corresponding preliminary modal evaluation results. The buckling safety margin corresponding to each element force information is determined by using a preset stability analysis program based on model type, boundary conditions and material properties. Then, the buckling safety margin is evaluated to obtain the corresponding stability evaluation results.

8. A wing strength assessment device based on a strength database, characterized in that, include: The aerodynamic shape data partitioning module is used to divide the aerodynamic shape data of the wing surface to be evaluated into several target grid cells; The lines connecting the grid nodes corresponding to the upper and lower wing surfaces in the target grid cell are perpendicular to the chord plane of the wing surface. The wing skeleton model generation module is used to perform up-down mapping and grouping of each grid node in the target grid cell based on preset structural layout parameters to obtain an initial wing skeleton model. The attribute determination module is used to call a preset strength database to determine the material properties and structural properties corresponding to the initial wing skeleton model and the initial skin model, respectively, so as to obtain the corresponding first wing skeleton model and first skin model. The model weight determination module is used to apply aerodynamic loads to the first skin model using a preset load card to obtain the second skin model, and to apply boundary constraints to the first wing skeleton model to obtain the second wing skeleton model. Then, it obtains the model weight corresponding to the aerodynamic shape data of the wing to be processed. The strength assessment result generation module is used to construct a model file based on the second skin model, the second wing skeleton model and the model weight, and to perform simulation calculations on the model file using a solver to obtain a result file. Then, it extracts the information to be evaluated, including stress and strain data, wingtip deformation, modal frequency and element force information, from the result file, performs strength assessment on the information to be evaluated, and obtains the strength assessment result corresponding to the aerodynamic shape data of the wing to be evaluated.

9. An electronic device, characterized in that, include: Memory, used to store computer programs; A processor for executing the computer program to implement the wing strength assessment method based on a strength database as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, Used to store a computer program, wherein the computer program, when executed by a processor, implements the wing strength assessment method based on a strength database as described in any one of claims 1 to 7.

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