Method, device, equipment and medium for generating structural flexibility matrix based on structural finite element model

Abstract

The present application discloses a method, device, equipment and medium for generating a structural flexibility matrix based on a structural finite element model, and relates to the field of aerospace aircraft technology, including: generating a structural finite element calculation grid based on a discrete unit type, discrete unit size and discrete unit distribution corresponding to a target component in a target aircraft to create a structural finite element model of the target component; selecting surface grid points from the structural finite element model, selecting a number of target surface grid points from the surface grid points to obtain a target grid point set; respectively obtaining the displacement responses of all target surface grid points in the target grid point set under different preset degrees of freedom, and assembling each displacement response based on a preset degree of freedom order to obtain a structural flexibility matrix of the target component; and performing static aeroelastic coupling simulation on the target component based on the structural flexibility matrix. The flexibility and ease of obtaining the structural flexibility matrix are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aerodynamic elastic numerical simulation of aerospace vehicles, and in particular to a method, device, equipment and medium for generating a structural flexibility matrix based on a structural finite element model. Background Art

[0002] There are three main methods for calculating structural deformation in static-aeroelastic coupling simulation of aerospace vehicles: structural finite element solution, modal superposition, and flexibility matrix solution. Among them, structural finite element solution has the advantages of high analysis accuracy and wide application range, but the finite element solution has large computational complexity and complex interface, and is generally used in the case of relatively complex structures; the modal superposition method decomposes the structural displacement into the modal space, and obtains the deformation of the structure through linear weighting between different modes. It has the advantages of small computational complexity and simple algorithm, but the prediction accuracy of structural deformation depends on the selection of the structural modal order, which has a certain degree of experience; the flexibility matrix method constructs the flexibility matrix of the structural model, and directly obtains the structural deformation by matrix operation according to the applied load vector. It has the characteristics of small computational complexity and easy implementation, and is the most commonly used method for linear structural deformation calculation in static-aeroelastic coupling simulation.

[0003] The structural flexibility matrix is ​​the inverse matrix of the stiffness matrix, so it can be obtained based on the inversion of the stiffness matrix. Some commercial structural simulation software provides an output interface for the stiffness matrix, such as Nastran. The flexibility matrix of the structure can be obtained by extracting the stiffness matrix and performing an inversion operation. There are two problems with this method of generating the structural flexibility matrix. First, this method generates the flexibility matrix under all structural degrees of freedom. When the number of structural degrees of freedom is very large, not only is the amount of inversion calculation huge, but also the large condition number of the stiffness matrix will cause obvious calculation errors, and the huge matrix size also brings inconvenience to the storage and use of the flexibility matrix; second, some commercial software closes the interface for extracting the stiffness matrix for the sake of technical confidentiality, so that the structural flexibility matrix cannot be directly obtained based on the finite element model of such commercial software.

[0004] From the above, it can be seen that how to improve the flexibility and ease of obtaining the structural flexibility matrix is ​​a problem to be solved in this field. Summary of the invention

[0005] In view of this, the purpose of the present invention is to provide a method, device, equipment and medium for generating a structural flexibility matrix based on a structural finite element model, which can improve the flexibility and ease of obtaining the structural flexibility matrix. The specific scheme is as follows:

[0006] In a first aspect, the present application discloses a method for generating a structural flexibility matrix based on a structural finite element model, comprising:

[0007] Generate a structural finite element calculation grid based on a discrete element type, discrete element size, and discrete element distribution corresponding to a target component in a target aircraft, and create a structural finite element model of the target component based on the structural finite element calculation grid, a corresponding solution type, and solution parameters;

[0008] Filtering surface grid points from the structural finite element model, and filtering a plurality of target surface grid points from the surface grid points based on a preset flexibility matrix scale and a preset load transfer loading requirement to obtain a target grid point set;

[0009] The displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom are respectively obtained, and each of the displacement responses is assembled based on a preset degree of freedom order to obtain a structural flexibility matrix of the target component, so as to perform aerostatic and aeroelastic coupling simulation on the target component based on the structural flexibility matrix.

[0010] Optionally, before generating the structural finite element calculation grid based on the discrete unit type, discrete unit size and discrete unit distribution corresponding to the target component, the method further includes:

[0011] Based on the geometric characteristics of the target component and the analysis accuracy requirements, the discrete unit type, discrete unit size and discrete unit distribution corresponding to the target component are determined.

[0012] Optionally, the creating the structural finite element model of the target component based on the structural finite element calculation grid, the corresponding solution type and solution parameters includes:

[0013] Determining the constitutive relationship of the structural finite element model using the material parameters of the target component, and adding corresponding constraint boundary conditions on the nodes of the structural finite element calculation grid;

[0014] A corresponding solution type and solution parameters are selected, and a structural finite element model of the target component is created based on the constitutive relationship, the constraint boundary conditions, the solution type and the solution parameters.

[0015] Optionally, the step of selecting surface grid points from the structural finite element model includes:

[0016] Surface mesh points are selected from the structural finite element model using the surface unit connection relationship analysis method;

[0017] Alternatively, the surface grid points are screened out from the structural finite element model using a surface element normal feature analysis method.

[0018] Optionally, respectively obtaining the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom includes:

[0019] The displacement responses of all the target surface grid points in the target grid point set are obtained when each target surface grid point in the target grid point set is in the x direction, the y direction, and the z direction respectively.

[0020] Optionally, the obtaining of the displacement responses of all the target surface grid points in the target grid point set when each target surface grid point in the target grid point set is in the x direction, the y direction, and the z direction, respectively, includes:

[0021] arbitrarily selecting the current target surface grid point from the target grid point set;

[0022] Applying a unit load in the x-direction to the current target surface grid point, and obtaining the first displacement response of all the target surface grid points in the target grid point set based on a preset statics solution algorithm, and then clearing the unit load in the x-direction of the current target surface grid point;

[0023] Applying a unit load in the y direction to the current target surface grid point, and obtaining the second displacement response of all the target surface grid points in the target grid point set based on a preset statics solution algorithm, and then clearing the unit load in the y direction of the current target surface grid point;

[0024] A unit load in the z direction is applied to the current target surface grid point, and a third displacement response of all the target surface grid points in the target grid point set is obtained based on a preset statics solution algorithm, and then the unit load in the z direction of the current target surface grid point is cleared.

[0025] Optionally, after assembling each of the displacement responses based on a preset degree of freedom order to obtain a structural flexibility matrix of the target component, the method further includes:

[0026] Under different preset load conditions, a plurality of first structural displacements and a plurality of corresponding second structural displacements are calculated using the structural finite element model and the flexibility matrix method, and a plurality of displacement differences between the plurality of first structural displacements and the plurality of corresponding second structural displacements are calculated, and then a target displacement difference that meets the preset conditions is selected from the plurality of displacement differences;

[0027] Determine whether the target displacement difference is greater than a preset difference threshold. If not, determine that the structural flexibility matrix meets the preset requirements; if yes, determine that the structural flexibility matrix does not meet the preset requirements, and jump again to the step of generating a structural finite element calculation grid based on the discrete unit type, discrete unit size and discrete unit distribution corresponding to the target component.

[0028] In a second aspect, the present application discloses a structural flexibility matrix generation device based on a structural finite element model, comprising:

[0029] A model creation module, for generating a structural finite element calculation grid based on a discrete element type, discrete element size and discrete element distribution corresponding to a target component in a target aircraft, and creating a structural finite element model of the target component based on the structural finite element calculation grid, a corresponding solution type and solution parameters;

[0030] A grid point set acquisition module, used for selecting surface grid points from the structural finite element model, and selecting a plurality of target surface grid points from the surface grid points based on a preset flexibility matrix scale and a preset load transfer loading requirement, so as to obtain a target grid point set;

[0031] The matrix acquisition module is used to respectively acquire the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom, and assemble each of the displacement responses based on a preset degree of freedom order to obtain the structural flexibility matrix of the target component, so as to perform static aeroelastic coupling simulation on the target component based on the structural flexibility matrix.

[0032] In a third aspect, the present application discloses an electronic device, comprising:

[0033] Memory, used to store computer programs;

[0034] A processor is used to execute the computer program to implement the steps of the aforementioned disclosed method for generating a structural flexibility matrix based on a structural finite element model.

[0035] In a fourth aspect, the present application discloses a computer-readable storage medium for storing a computer program; wherein, when the computer program is executed by a processor, the steps of the aforementioned method for generating a structural flexibility matrix based on a structural finite element model are implemented.

[0036] It can be seen that the present application generates a structural finite element calculation grid based on the discrete unit type, discrete unit size and discrete unit distribution corresponding to the target component in the target aircraft, and creates a structural finite element model of the target component based on the structural finite element calculation grid, the corresponding solution type and solution parameters; screens out surface grid points from the structural finite element model, and screens out a number of target surface grid points from the surface grid points based on a preset flexibility matrix scale and preset load transfer loading requirements to obtain a target grid point set; respectively obtains the displacement response of each target surface grid point in the target grid point set under different preset degrees of freedom, and assembles the displacement response of each target surface grid point based on a preset degree of freedom order to obtain the structural flexibility matrix of the target component, so as to perform static aeroelastic coupling simulation of the target component based on the structural flexibility matrix. It can be seen that the present application generates a structural finite element calculation grid based on the relevant information of the discrete units of the target component, and creates a structural finite element model of the target component based on the structural finite element calculation grid, the corresponding solution type and solution parameters, and then assembles the displacement responses of the target grid point set in the structural finite element model to obtain the structural flexibility matrix of the target component. There is no need to calculate the inverse matrix of the stiffness matrix to obtain the structural flexibility matrix of the target component, which improves the flexibility and ease of obtaining the structural flexibility matrix of the target component. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0038] Figure 1 A flow chart of a method for generating a structural flexibility matrix based on a structural finite element model disclosed in this application;

[0039] Figure 2 A flow chart of a specific method for generating a structural flexibility matrix based on a structural finite element model disclosed in this application;

[0040] Figure 3 A schematic diagram of a specific target component disclosed in this application;

[0041] Figure 4 A schematic diagram of a specific structural finite element calculation grid disclosed in this application;

[0042] Figure 5 A schematic diagram of a specific structural finite element model disclosed in this application;

[0043] Figure 6 A specific target surface node selection schematic diagram disclosed in this application;

[0044] Figure 7 A schematic diagram of a specific structural flexibility matrix verification disclosed in this application;

[0045] Figure 8 A schematic diagram of a structural flexibility matrix generating device based on a structural finite element model disclosed in this application;

[0046] Fig. 9 This is a structural diagram of an electronic device disclosed in this application. DETAILED DESCRIPTION

[0047] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0048] The structural flexibility matrix is ​​the inverse matrix of the stiffness matrix, so it can be obtained based on the inversion of the stiffness matrix. Some commercial structural simulation software provides an output interface for the stiffness matrix, such as Nastran. The flexibility matrix of the structure can be obtained by extracting the stiffness matrix and performing an inversion operation. There are two problems with this method of generating the structural flexibility matrix. First, this method generates the flexibility matrix under all structural degrees of freedom. When the number of structural degrees of freedom is very large, not only is the amount of inversion calculation huge, but also the large condition number of the stiffness matrix will cause obvious calculation errors, and the huge matrix size also brings inconvenience to the storage and use of the flexibility matrix; second, some commercial software closes the interface for extracting the stiffness matrix for the sake of technical confidentiality, so that the structural flexibility matrix cannot be directly obtained based on the finite element model of such commercial software.

[0049] To this end, the present application accordingly provides a structural flexibility matrix generation solution based on a structural finite element model, which can improve the flexibility and ease of obtaining the structural flexibility matrix.

[0050] See also Figure 1 As shown, the embodiment of the present application discloses a structural flexibility matrix generating device based on a structural finite element model, comprising:

[0051] Step S11: Generate a structural finite element calculation grid based on the discrete element type, discrete element size and discrete element distribution corresponding to the target component in the target aircraft, and create a structural finite element model of the target component based on the structural finite element calculation grid, corresponding solution type and solution parameters.

[0052] In this embodiment, before generating a structural finite element calculation grid based on the discrete unit type, discrete unit size and discrete unit distribution corresponding to the target component in the target aircraft, it is necessary to determine the discrete unit type, discrete unit size and discrete unit distribution of the target component according to the geometric characteristics of the target component in the target aircraft and the analysis accuracy requirements. When generating a structural finite element calculation grid, a subdivision algorithm can be used to generate a structural finite element calculation grid. Based on the structural material used by the target component, accurate material parameters are selected to determine the constitutive relationship of the structural finite element model. Based on the constraint relationship between the target component and the environment, correct constraint boundary conditions are added to the corresponding structural finite element grid nodes, and statics solution can be selected as the solution type of the structural finite element model, and the selection of solution parameters is completed based on the analysis requirements, thereby completing the creation of the structural finite element model.

[0053] Step S12: Filtering out surface grid points from the structural finite element model, and filtering out a number of target surface grid points from the surface grid points based on a preset flexibility matrix scale and a preset load transfer loading requirement to obtain a target grid point set.

[0054] In this embodiment, the surface grid points are selected from the structural finite element model, specifically including: selecting the surface grid points from the structural finite element model using a surface unit connection relationship analysis method; or selecting the surface grid points from the structural finite element model using a surface unit normal feature analysis method. Based on a preset flexibility matrix scale and a preset load transfer loading requirement, a number of target surface grid points P are selected from the surface grid points by manual selection or algorithm selection. i , to obtain the target grid point set P, where the target surface grid point P i are the grid points used for transferring loads.

[0055] Step S13: respectively obtaining the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom, and assembling each of the displacement responses based on a preset degree of freedom order to obtain a structural flexibility matrix of the target component, so as to perform aerostatic-aeroelastic coupling simulation on the target component based on the structural flexibility matrix.

[0056] In this embodiment, a grid point can be arbitrarily selected from the target grid point set P as the current target surface grid point P i , in P i Apply a unit load in the x direction, perform a preset static solution, obtain and store the displacement response dXYZ1 of all grid points in the target grid point set P, and then clear all loads;

[0057] In P iApply a unit load in the y direction, perform a preset static solution, obtain and store the displacement response dXYZ2 of all grid points in the target grid point set P, and then clear all loads; i Apply a unit load in the z direction, perform a preset statics solution, obtain and store the displacement response dXYZ3 of all grid points in the target grid point set P, and then clear all loads. It can be understood that all grid points in the target grid point set P are traversed, and at each grid point in the target grid point set P, a unit load is applied in the x, y, and z degrees of freedom directions in turn, and a preset statics analysis is performed to obtain the displacement response of all grid points in the target grid point set P under the corresponding load.

[0058] In this embodiment, based on the preset degree of freedom order, the displacement responses dXYZ1, dXYZ2, and dXYZ3 of each target surface grid point are assembled to obtain the structural flexibility matrix C of the target component, wherein the assembly relationship is as follows:

[0059] C=[dXYZ 1 dX w dX N ];

[0060] dX w =[dXYZ1 dXYZ2 dXYZ3] w ;

[0061]

[0062] Where dx, dy, and dz represent the displacement responses in the x, y, and z degrees of freedom directions, respectively; N represents the number of all grid points in the target grid point set P; w represents the application of a unit load on the wth grid point in the target grid point set P; i represents the displacement response at the i-th grid point in the target grid point set P; and xForce, yForce, and zForce represent the displacement responses of the grid points obtained by applying unit loads in the x, y, and z degrees of freedom directions, respectively.

[0063] In this embodiment, the generated structural flexibility matrix can be output as a structural flexibility matrix file in a specific data format, which can be used as an input data file for other software modules so that other software modules can perform relevant calculations based on the structural flexibility matrix file. For example, it can be used as an input data file for performing static aeroelastic coupling simulation so as to perform static aeroelastic coupling simulation on target components in a target aircraft.

[0064] It can be seen that the present application generates a structural finite element calculation grid based on the discrete unit type, discrete unit size and discrete unit distribution corresponding to the target component in the target aircraft, and creates a structural finite element model of the target component based on the structural finite element calculation grid, the corresponding solution type and solution parameters; screens out surface grid points from the structural finite element model, and screens out a number of target surface grid points from the surface grid points based on a preset flexibility matrix scale and preset load transfer loading requirements to obtain a target grid point set; respectively obtains the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom, and assembles each of the displacement responses based on a preset degree of freedom order to obtain the structural flexibility matrix of the target component, so as to perform static aeroelastic coupling simulation of the target component based on the structural flexibility matrix. It can be seen that the present application generates a structural finite element calculation grid based on the relevant information of the discrete units of the target component, and creates a structural finite element model of the target component based on the structural finite element calculation grid, the corresponding solution type and solution parameters, and then assembles the displacement responses of the target grid point set in the structural finite element model to obtain the structural flexibility matrix of the target component. There is no need to calculate the inverse matrix of the stiffness matrix to obtain the structural flexibility matrix of the target component, which improves the flexibility and ease of obtaining the structural flexibility matrix of the target component.

[0065] See also Figure 2 As shown, the embodiment of the present application discloses a specific method for generating a structural flexibility matrix based on a structural finite element model, including:

[0066] Step S21: Based on the geometric characteristics and analysis accuracy requirements of the target component in the target aircraft, determine the discrete unit type, discrete unit size and discrete unit distribution corresponding to the target component.

[0067] In this embodiment, based on the geometric characteristics of the target component and the analysis accuracy requirements, the discrete unit type, discrete unit size and discrete unit distribution target component corresponding to the target component are determined. Figure 3 A specific schematic diagram of a target component is shown, where the target component is a flat plate component 1 in a target aircraft.

[0068] Step S22: generating a structural finite element calculation grid based on the discrete element type, the discrete element size and the discrete element distribution, and creating a structural finite element model of the target component based on the structural finite element calculation grid, the corresponding solution type and solution parameters.

[0069] In this embodiment, for example Figure 4A specific schematic diagram of a structural finite element calculation grid is shown. The structural finite element calculation grid is generated based on the type, size and distribution of the discrete unit 2. The flat plate component 1 is set with 17 grid points in the length direction, 5 grid points in the width direction, and 2 grid points in the thickness direction. The grid points 3 in the three directions are uniformly distributed. After the grid points 3 are defined, the structural finite element calculation grid of the flat plate component 1 is generated through a mapping partitioning algorithm.

[0070] In this embodiment, the creation of the structural finite element model of the target component based on the structural finite element calculation grid, the corresponding solution type and the solution parameters includes: determining the constitutive relationship of the structural finite element model using the material parameters of the target component, and adding corresponding constraint boundary conditions to the nodes of the structural finite element calculation grid; selecting the corresponding solution type and the solution parameters, and creating the structural finite element model of the target component based on the constitutive relationship, the constraint boundary conditions, the solution type and the solution parameters. For example, based on the use of steel material to define material parameters such as elastic modulus, Poisson's ratio, density, etc. for the flat plate component 1, the constitutive relationship of the material of the structural finite element model is determined, for example Figure 5 A specific schematic diagram of a structural finite element model is shown. Based on the fixation at the right end of the flat plate component 1, a fixation constraint 4 is added to the corresponding right end surface grid point of the structural finite element calculation grid. Statics solution can be selected as the solution type of the structural finite element model, and the selection of solution parameters such as the iterative method is completed according to the analysis requirements to complete the creation of the structural finite element model.

[0071] Step S23: Filtering out surface grid points from the structural finite element model, and filtering out a number of target surface grid points from the surface grid points based on a preset flexibility matrix scale and a preset load transfer loading requirement to obtain a target grid point set.

[0072] In this embodiment, all 170 surface grid points of the flat plate component 1 are selected from all grid points of the structural finite element model of the flat plate component 1 by using the surface unit connection relationship analysis method or the surface unit normal feature analysis method. Figure 6 A specific schematic diagram of target surface node selection is shown. Based on the preset flexibility matrix scale and the preset load transfer loading requirements, 70 target surface nodes are selected from 170 surface grid points by manual selection or algorithm screening to form a target grid point set P for solving the structural flexibility matrix of the flat component 1.

[0073] Step S24: respectively obtaining the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom, and assembling each of the displacement responses based on a preset degree of freedom order to obtain a structural flexibility matrix of the target component, so as to perform aerostatic-aeroelastic coupling simulation on the target component based on the structural flexibility matrix.

[0074] In this embodiment, respectively obtaining the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom specifically includes: obtaining the displacement responses of all the target surface grid points in the target grid point set when each target surface grid point in the target grid point set is respectively in the x direction, y direction and z direction.

[0075] In this embodiment, the step of obtaining the displacement response of all the target surface grid points in the target grid point set when each target surface grid point in the target grid point set is in the x direction, the y direction, and the z direction, specifically includes: arbitrarily selecting the current target surface grid point from the target grid point set; applying a unit load in the x direction to the current target surface grid point, and obtaining a first displacement response of all the target surface grid points in the target grid point set based on a preset statics solution algorithm, and then clearing the unit load of the current target surface grid point in the x direction; applying a unit load in the y direction to the current target surface grid point, and obtaining a second displacement response of all the target surface grid points in the target grid point set based on a preset statics solution algorithm, and then clearing the unit load of the current target surface grid point in the y direction; applying a unit load in the z direction to the current target surface grid point, and obtaining a third displacement response of all the target surface grid points in the target grid point set based on a preset statics solution algorithm, and then clearing the unit load of the current target surface grid point in the z direction.

[0076] In this embodiment, after assembling each of the displacement responses based on the preset degree of freedom order to obtain the structural flexibility matrix of the target component, it also includes: under different preset load loading conditions, using the structural finite element model and the flexibility matrix method to calculate a number of first structural displacements and a number of corresponding second structural displacements, and respectively calculating a number of displacement differences between a number of the first structural displacements and a number of corresponding second structural displacements, and then screening out target displacement differences that meet the preset conditions from the several displacement differences; judging whether the target displacement difference is greater than a preset difference threshold, if not, determining that the structural flexibility matrix meets the preset requirements; if yes, determining that the structural flexibility matrix does not meet the preset requirements, and re-jumping to the step of generating a structural finite element calculation grid based on the discrete unit type, discrete unit size and discrete unit distribution corresponding to the target component. Figure 7A specific structural flexibility matrix verification schematic diagram is shown. Under a preset load loading condition 1, the first structural displacement 1 and the second structural displacement 1 are calculated using the structural finite element model and the flexibility matrix method respectively; under a preset load loading condition 2, the first structural displacement 2 and the second structural displacement 2 are calculated using the structural finite element model and the flexibility matrix method respectively; under a preset load loading condition N, the first structural displacement N and the second structural displacement N are calculated using the structural finite element model and the flexibility matrix method respectively; the displacement difference 1 between the first structural displacement 1 and the second structural displacement 1 is calculated, and the displacement difference 1 between the first structural displacement 2 and the second structural displacement 2 is calculated. The displacement difference 2 between the first structure displacement N and the second structure displacement N is calculated; the maximum displacement difference is determined from the displacement difference 1, the displacement difference 2, ... the displacement difference N as the target displacement difference, and it is judged whether the target displacement difference is greater than the preset difference threshold; if not, it is determined that the structural flexibility matrix meets the preset requirements, that is, the correct structural flexibility matrix is ​​generated; if yes, it is determined that the structural flexibility matrix does not meet the preset requirements, that is, an incorrect structural flexibility matrix is ​​generated, and it is jumped again to the step of generating a structural finite element calculation grid based on the discrete unit type, discrete unit size and discrete unit distribution corresponding to the target component. By judging whether the target displacement difference is greater than the preset difference threshold, it is determined whether the correctness of the generated structural flexibility matrix meets the preset requirements, thereby ensuring the reliability of the subsequent static aeroelastic coupling simulation using the structural flexibility matrix.

[0077] It can be seen that the structural flexibility matrix generation method in the present application is not only applicable to all grid node degrees of freedom, but also to the degrees of freedom of selected grid nodes, so as to facilitate the adjustment of the scale of the flexibility matrix, and further improve the ease of generating the structural flexibility matrix based on the structural finite element model. In addition, the present application can also verify the correctness of the structural flexibility matrix, so as to avoid the situation where the simulation results are erroneous due to incorrect structural flexibility matrix when the structural flexibility matrix is ​​used for subsequent static aeroelastic coupling simulation.

[0078] See also Figure 8 As shown, the embodiment of the present application discloses a structural flexibility matrix generating device based on a structural finite element model, comprising:

[0079] The model creation module 11 is used to generate a structural finite element calculation grid based on the discrete element type, discrete element size and discrete element distribution corresponding to the target component in the target aircraft, and to create a structural finite element model of the target component based on the structural finite element calculation grid, the corresponding solution type and solution parameters;

[0080] A grid point set acquisition module 12 is used to select surface grid points from the structural finite element model, and select a number of target surface grid points from the surface grid points based on a preset flexibility matrix scale and a preset load transfer loading requirement to obtain a target grid point set;

[0081] The matrix acquisition module 13 is used to respectively acquire the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom, and assemble each of the displacement responses based on a preset degree of freedom order to obtain the structural flexibility matrix of the target component, so as to perform static aeroelastic coupling simulation on the target component based on the structural flexibility matrix.

[0082] It can be seen that the present application generates a structural finite element calculation grid based on the discrete unit type, discrete unit size and discrete unit distribution corresponding to the target component in the target aircraft, and creates a structural finite element model of the target component based on the structural finite element calculation grid, the corresponding solution type and solution parameters; screens out surface grid points from the structural finite element model, and screens out a number of target surface grid points from the surface grid points based on a preset flexibility matrix scale and preset load transfer loading requirements to obtain a target grid point set; respectively obtains the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom, and assembles each of the displacement responses based on a preset degree of freedom order to obtain the structural flexibility matrix of the target component, so as to perform static aeroelastic coupling simulation of the target component based on the structural flexibility matrix. It can be seen that the present application generates a structural finite element calculation grid based on the relevant information of the discrete units of the target component, and creates a structural finite element model of the target component based on the structural finite element calculation grid, the corresponding solution type and solution parameters, and then assembles the displacement responses of the target grid point set in the structural finite element model to obtain the structural flexibility matrix of the target component. There is no need to calculate the inverse matrix of the stiffness matrix to obtain the structural flexibility matrix of the target component, which improves the flexibility and ease of obtaining the structural flexibility matrix of the target component.

[0083] Fig. 9 A schematic diagram of the structure of an electronic device provided in an embodiment of the present application. Specifically, it 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 is used to store a computer program, which is loaded and executed by the processor 21 to implement the relevant steps in the method for generating a structural flexibility matrix based on a structural finite element model performed by the electronic device disclosed in any of the aforementioned embodiments.

[0084] In this embodiment, the power supply 23 is used to provide working voltage for each hardware device on the electronic device; the communication interface 24 can create a data transmission channel between the electronic device and the external device, and the communication protocol it follows is any communication protocol that can be applied to the technical solution of the present application, and is not specifically limited here; the input and output interface 25 is used to obtain 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.

[0085] Among them, the processor 21 may include one or more processing cores, such as a 4-core processor, an 8-core processor, etc. The processor 21 can be implemented in at least one hardware form of DSP (Digital Signal Processing), FPGA (Field-Programmable Gate Array), and PLA (Programmable Logic Array). The processor 21 may also include a main processor and a coprocessor. The main processor is a processor for processing data in the awake state, also known as a CPU (Central Processing Unit); the coprocessor is a low-power processor for processing data in the standby state. In some embodiments, the processor 21 may be integrated with a GPU (Graphics Processing Unit), which is responsible for rendering and drawing the content to be displayed on the display screen. In some embodiments, the processor 21 may also include an AI (Artificial Intelligence) processor, which is used to process computing operations related to machine learning.

[0086] In addition, the memory 22, as a carrier for storing resources, can be a read-only memory, a random access memory, a disk or an optical disk, etc. The resources stored thereon include an operating system 221, a computer program 222 and data 223, etc. The storage method can be temporary storage or permanent storage.

[0087] Among them, the operating system 221 is used to manage and control the hardware devices and computer programs 222 on the electronic device to realize the operation and processing of the massive data 223 in the memory 22 by the processor 21, which can be Windows, Unix, Linux, etc. In addition to including a computer program that can be used to complete the structural flexibility matrix generation method based on the structural finite element model executed by the electronic device disclosed in any of the aforementioned embodiments, the computer program 222 can also further include a computer program that can be used to complete other specific tasks. In addition to data transmitted from an external device received by the electronic device, the data 223 can also include data collected by its own input and output interface 25, etc.

[0088] Furthermore, an embodiment of the present application also discloses a computer-readable storage medium, in which a computer program is stored. When the computer program is loaded and executed by a processor, the method steps performed in the process of generating a structural flexibility matrix based on a structural finite element model disclosed in any of the aforementioned embodiments are implemented.

[0089] Finally, it should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0090] The above is a detailed introduction to the structural flexibility matrix generation method, device, equipment and medium based on the structural finite element model provided by the present invention. Specific examples are used in this article to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea; at the same time, for general technical personnel in this field, according to the idea of ​​the present invention, there will be changes in the specific implementation method and application scope. In summary, the content of this specification should not be understood as a limitation on the present invention.

Claims

1. A method for generating a structural flexibility matrix based on a structural finite element model, characterized in that: include: Generate a structural finite element calculation grid based on a discrete element type, discrete element size, and discrete element distribution corresponding to a target component in a target aircraft, and create a structural finite element model of the target component based on the structural finite element calculation grid, a corresponding solution type, and solution parameters; Filtering surface grid points from the structural finite element model, and filtering a plurality of target surface grid points from the surface grid points based on a preset flexibility matrix scale and a preset load transfer loading requirement to obtain a target grid point set; Respectively obtaining displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom, and assembling each of the displacement responses based on a preset degree of freedom order to obtain a structural flexibility matrix of the target component, so as to perform aerostatic and aeroelastic coupling simulation on the target component based on the structural flexibility matrix; The step of respectively obtaining displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom includes: The current target surface grid point is arbitrarily selected from the target grid point set; a unit load in the x direction is applied to the current target surface grid point, and a first displacement response of all the target surface grid points in the target grid point set is obtained based on a preset statics solution algorithm, and then the unit load of the current target surface grid point in the x direction is cleared; a unit load in the y direction is applied to the current target surface grid point, and a second displacement response of all the target surface grid points in the target grid point set is obtained based on a preset statics solution algorithm, and then the unit load of the current target surface grid point in the y direction is cleared; a unit load in the z direction is applied to the current target surface grid point, and a third displacement response of all the target surface grid points in the target grid point set is obtained based on a preset statics solution algorithm, and then the unit load of the current target surface grid point in the z direction is cleared; Among them, the assembly relationship of the displacement response is: C=[dXYZ 1 … dXYZ w … dXYZ N ]; dXYZ w =[dXYZ1 dXYZ2 dXYZ3] w ; Wherein, dXYZ1, dXYZ2, dXYZ3dx represent displacement responses, C represents the structural flexibility matrix, dy and dz represent the displacement responses in the x, y, and z degrees of freedom directions, respectively, N represents the number of all grid points in the target grid point set P, w represents the application of unit load on the w-th grid point in the target grid point set P, i represents the displacement response on the i-th grid point in the target grid point set P, and xForce, yForce, and zForce represent the displacement responses of the grid points obtained by applying unit loads in the x, y, and z degrees of freedom directions, respectively.

2. The method for generating a structural flexibility matrix based on a structural finite element model according to claim 1, characterized in that: Before generating the structural finite element calculation grid based on the discrete unit type, discrete unit size and discrete unit distribution corresponding to the target component, the method further includes: Based on the geometric characteristics of the target component and the analysis accuracy requirements, the discrete unit type, discrete unit size and discrete unit distribution corresponding to the target component are determined.

3. The method for generating a structural flexibility matrix based on a structural finite element model according to claim 1, characterized in that: The step of creating a structural finite element model of the target component based on the structural finite element calculation grid, the corresponding solution type and solution parameters includes: Determining the constitutive relationship of the structural finite element model using the material parameters of the target component, and adding corresponding constraint boundary conditions on the nodes of the structural finite element calculation grid; A corresponding solution type and solution parameters are selected, and a structural finite element model of the target component is created based on the constitutive relationship, the constraint boundary conditions, the solution type and the solution parameters.

4. The method for generating a structural flexibility matrix based on a structural finite element model according to claim 1, characterized in that: The step of selecting surface grid points from the structural finite element model includes: Surface mesh points are selected from the structural finite element model using the surface unit connection relationship analysis method; Alternatively, the surface grid points are screened out from the structural finite element model using a surface element normal feature analysis method.

5. The method for generating a structural flexibility matrix based on a structural finite element model according to any one of claims 1 to 4, characterized in that: After assembling each of the displacement responses based on the preset degree of freedom order to obtain the structural flexibility matrix of the target component, the method further includes: Under different preset load conditions, a plurality of first structural displacements and a plurality of corresponding second structural displacements are calculated using the structural finite element model and the flexibility matrix method, and a plurality of displacement differences between the plurality of first structural displacements and the plurality of corresponding second structural displacements are calculated, and then a target displacement difference that meets the preset conditions is selected from the plurality of displacement differences; Determine whether the target displacement difference is greater than a preset difference threshold. If not, determine that the structural flexibility matrix meets the preset requirements; if yes, determine that the structural flexibility matrix does not meet the preset requirements, and jump again to the step of generating a structural finite element calculation grid based on the discrete unit type, discrete unit size and discrete unit distribution corresponding to the target component.

6. A structural flexibility matrix generation device based on a structural finite element model, characterized in that: include: A model creation module, for generating a structural finite element calculation grid based on a discrete element type, discrete element size and discrete element distribution corresponding to a target component in a target aircraft, and creating a structural finite element model of the target component based on the structural finite element calculation grid, a corresponding solution type and solution parameters; A grid point set acquisition module, used for selecting surface grid points from the structural finite element model, and selecting a plurality of target surface grid points from the surface grid points based on a preset flexibility matrix scale and a preset load transfer loading requirement, so as to obtain a target grid point set; a matrix acquisition module, for respectively acquiring displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom, and assembling each of the displacement responses based on a preset degree of freedom order to obtain a structural flexibility matrix of the target component, so as to perform aerostatic and aeroelastic coupling simulation on the target component based on the structural flexibility matrix; The matrix acquisition module is specifically used for: Randomly select the current target surface grid point from the target grid point set; apply a unit load in the x direction to the current target surface grid point, and obtain the first displacement response of all the target surface grid points in the target grid point set based on a preset statics solution algorithm, and then clear the unit load of the current target surface grid point in the x direction; Applying a unit load in the y direction to the current target surface grid point, and obtaining the second displacement response of all the target surface grid points in the target grid point set based on a preset statics solution algorithm, and then clearing the unit load in the y direction of the current target surface grid point; Applying a unit load in the z direction to the current target surface grid point, and obtaining a third displacement response of all the target surface grid points in the target grid point set based on a preset statics solution algorithm, and then clearing the unit load in the z direction of the current target surface grid point; Among them, the assembly relationship of the displacement response is: C=[dXYZ 1 … dXYZ w … dXYZ N ]; dXYZ w =[dXYZ1 dXYZ2 dXYZ3] w ; Wherein, dXYZ1, dXYZ2, dXYZ3dx represent displacement responses, C represents the structural flexibility matrix, dy and dz represent the displacement responses in the x, y, and z degrees of freedom directions, respectively, N represents the number of all grid points in the target grid point set P, w represents the application of unit load on the w-th grid point in the target grid point set P, i represents the displacement response on the i-th grid point in the target grid point set P, and xForce, yForce, and zForce represent the displacement responses of the grid points obtained by applying unit loads in the x, y, and z degrees of freedom directions, respectively.

7. An electronic device, characterized in that: include: Memory, used to store computer programs; A processor is used to execute the computer program to implement the steps of the method for generating a structural flexibility matrix based on a structural finite element model as described in any one of claims 1 to 5.

8. A computer-readable storage medium, characterized in that: Used to store computer programs; wherein, when the computer program is executed by a processor, the steps of the method for generating a structural flexibility matrix based on a structural finite element model as described in any one of claims 1 to 5 are implemented.

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