CN115099095A - Generating method of structural compliance matrix based on structural finite element model and related components - Google Patents

Abstract

The application discloses a method, a device, equipment and a medium for generating a structure flexibility matrix based on a structure finite element model, which relate to the technical field of aerospace aircrafts and comprise the following steps: generating a structural finite element computation mesh based on the discrete element type, the discrete element size and the discrete element distribution corresponding to the target component in the target aircraft to create a structural finite element model of the target component; screening surface grid points from the structural finite element model, and screening a plurality of target surface grid points from the surface grid points to obtain a target grid point set; respectively obtaining 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 sequence to obtain a structural flexibility matrix of the target component; and performing static-pneumatic elastic coupling simulation on the target component based on the structural flexibility matrix. The flexibility and the ease of obtaining the structural compliance matrix are improved.

Description

Generating method of structural compliance matrix and related components based on structural finite element model

technical field

The invention relates to the technical field of aeroelastic numerical simulation of aerospace vehicles, in particular to a method, device, equipment and medium for generating a structural compliance matrix based on a structural finite element model.

Background technique

The structural deformation calculation in the static aeroelastic coupling simulation of aerospace vehicle mainly includes three methods: structural finite element solution, modal superposition and compliance matrix solution. Among them, the structural finite element solution has the advantages of high analysis accuracy and wide application range, but the finite element solution has a large amount of computation and complex interfaces, and is generally used in the case of complex structures; the modal superposition method decomposes the structural displacement into the modal space , the deformation of the structure is obtained by linear weighting between different modes, which has the advantages of small calculation amount and simple algorithm, but the prediction accuracy of the structural deformation depends on the selection of the structural mode order, which has a certain degree of experience; the flexibility matrix The method constructs the flexibility matrix of the structural model, and directly obtains the structural deformation by using the matrix operation according to the applied load vector. It has the characteristics of small calculation amount and easy realization. method.

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 the output interface of the stiffness matrix, such as Nastran, by extracting the stiffness matrix and performing the inversion operation to obtain the structure. the flexibility matrix. There are two problems in this structural flexibility matrix generation method. One is that 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 the inversion calculation is huge, but also due to the stiffness matrix condition The number deviation 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 stiffness matrix due to technical confidentiality considerations. The structural compliance matrix cannot be obtained directly based on the finite element model of such commercial software.

In conclusion, it can be seen that how to improve the flexibility and ease of obtaining the structural compliance matrix is a problem to be solved in the art.

SUMMARY OF THE INVENTION

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

In a first aspect, the present application discloses a method for generating a structural compliance matrix based on a structural finite element model, including:

Based on the discrete element type, discrete element size, and discrete element distribution corresponding to the target component in the target aircraft, a structural finite element calculation grid is generated, and based on the structural finite element calculation grid, the corresponding solution type, and the solution parameters, all Describe the structural finite element model of the target component;

Screen out surface mesh points from the structural finite element model, and screen out several target surface mesh points from the surface mesh points based on the preset compliance matrix scale and preset load transfer loading requirements to obtain the target grid point set;

Obtain the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom respectively, and assemble each of the displacement responses based on the preset degree of freedom sequence to obtain the target A structural compliance matrix of the component, so as to perform a static aeroelastic coupling simulation of the target component based on the structural compliance matrix.

Optionally, before generating the structural finite element calculation grid based on the discrete element type, discrete element size and discrete element 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.

Optionally, 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, including:

Determine the constitutive relationship of the structural finite element model by using the material parameters of the target component, and add corresponding constraint boundary conditions on the nodes of the structural finite element calculation grid;

A corresponding solution type and solution parameter are selected, and based on the constitutive relation, the constrained boundary condition, the solution type and the solution parameter, a structural finite element model of the target component is created.

Optionally, the filtering of surface mesh points from the structural finite element model includes:

The surface mesh points are screened out from the structural finite element model using the surface element connection relationship analysis method;

Or, the surface mesh points are screened out from the structural finite element model by using the surface element normal feature analysis method.

Optionally, the separately acquiring the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom, including:

Acquire the displacement responses of all the target surface grid points in the target grid point set when each of the target surface grid points in the target grid point set is in the x direction, the y direction and the z direction respectively.

Optionally, when each of the target surface grid points in the acquired target grid point set is in the x direction, the y direction and the z direction respectively, all the target surface grid points in the target grid point set are obtained. displacement response, including:

The current target surface grid point is arbitrarily selected 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 responses of all the target surface grid points in the target grid point set based on a preset statics solution algorithm, and then clear the current the unit load of the target surface grid point in the x direction;

Apply a unit load in the y direction to the current target surface grid point, and obtain the second displacement responses of all the target surface grid points in the target grid point set based on a preset statics solution algorithm, and then clear the current the unit load of the target surface grid point in the y direction;

Apply a unit load in the z-direction to the current target surface grid point, and obtain the 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 clear the current the unit load of the target surface grid point in the z direction.

Optionally, after assembling each of the displacement responses based on a preset order of degrees of freedom to obtain a structural compliance matrix of the target component, the method further includes:

Under different preset load loading conditions, several first structural displacements and corresponding several second structural displacements calculated by the structural finite element model and the flexibility matrix method are respectively used, and several first structural displacements are calculated respectively. several displacement differences between the structural displacement and the corresponding several second structural displacements, and then screen out the target displacement differences that meet the preset conditions from the several displacement differences;

Determine whether the target displacement difference is greater than a preset difference threshold, if not, determine that the structural compliance matrix meets the preset requirements; if so, determine that the structural compliance matrix does not meet the preset requirements, and re-jump to the Describe the steps of generating 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 a second aspect, the present application discloses a device for generating a structural compliance matrix based on a structural finite element model, including:

A model creation module for generating 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 based on the structural finite element calculation grid and the corresponding solution type and solving parameters to create a structural finite element model of the target component;

The grid point set acquisition module is used to filter out the surface grid points from the finite element model of the structure, and select several surface grid points from the surface grid points based on the preset compliance matrix scale and the preset load transfer loading requirements target surface grid points to get the target grid point set;

A matrix acquisition module is used to separately acquire the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom, and based on the preset degree of freedom sequence, each of the displacement responses is performed. Assembling to obtain a structural compliance matrix of the target component, so as to perform a static aeroelastic coupling simulation on the target component based on the structural compliance matrix.

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

memory for storing computer programs;

The processor is configured to execute the computer program to implement the steps of the aforementioned method for generating a structural compliance matrix based on a structural finite element model.

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 aforementioned method for generating a structural compliance matrix based on a structural finite element model is implemented. step.

It can be seen that the present application generates 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 based on the structural finite element calculation grid, the corresponding solution type and solution parameters, create a structural finite element model of the target component; screen out surface mesh points from the structural finite element model, and select the surface mesh points from the surface mesh points based on a preset compliance matrix scale and preset load transfer loading requirements Screen out a number of target surface grid points to obtain a target grid point set; respectively obtain the displacement responses of each target surface grid point in the target grid point set under different preset degrees of freedom, and based on the preset Assuming the order of degrees of freedom, the displacement responses of each of the target surface grid points are assembled to obtain a structural compliance matrix of the target component, so that the target component can be statically aerodynamic based on the structural compliance matrix. Elastic coupling simulation. It can be seen that the present application generates a structural finite element calculation grid based on the relevant information of the discrete elements 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 The displacement response of the target grid point set in the structural finite element model is assembled to obtain the structural compliance matrix of the target component, and there is no need to calculate the inverse matrix of the stiffness matrix to obtain the structural compliance matrix of the target component, which improves the acquisition of the structure of the target component. Flexibility and ease of compliance matrix.

Description of drawings

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the accompanying drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only It is an embodiment of the present invention. For those of ordinary skill in the art, other drawings can also be obtained according to the provided drawings without creative work.

1 is a flowchart of a method for generating a structural compliance matrix based on a structural finite element model disclosed in the present application;

2 is a flowchart of a specific method for generating a structural compliance matrix based on a structural finite element model disclosed in the present application;

3 is a schematic diagram of a specific target component disclosed in the application;

4 is a schematic diagram of a specific structural finite element calculation grid disclosed in the application;

5 is a schematic diagram of a specific structural finite element model disclosed in the application;

6 is a schematic diagram of a specific target surface node selection disclosed in the application;

7 is a schematic diagram of a specific structural compliance matrix verification disclosed in the application;

8 is a schematic structural diagram of a device for generating a structural compliance matrix based on a structural finite element model disclosed in the present application;

FIG. 9 is a structural diagram of an electronic device disclosed in this application.

Detailed ways

The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present invention, but not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

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 the output interface of the stiffness matrix, such as Nastran, by extracting the stiffness matrix and performing the inversion operation to obtain the structure. the flexibility matrix. There are two problems in this structural flexibility matrix generation method. One is that 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 the inversion calculation is huge, but also due to the stiffness matrix condition The number deviation 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 stiffness matrix due to technical confidentiality considerations. The structural compliance matrix cannot be obtained directly based on the finite element model of such commercial software.

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

Referring to FIG. 1 , an embodiment of the present application discloses a device for generating a structural compliance matrix based on a structural finite element model, including:

Step S11 : generating 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 based on the structural finite element calculation grid, corresponding solution types and solution parameters , to create a structural finite element model of the target component.

In this embodiment, before generating the 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, it is necessary to combine the analysis accuracy according to the geometric characteristics of the target component in the target aircraft. Requirements, determine the discrete element type, discrete element size and discrete element distribution of the target part. When generating the structural finite element calculation grid, the subdivision algorithm can be used to generate the structural finite element calculation grid. Select accurate material parameters based on the structural material used by the target component to determine the constitutive relationship of the structural finite element model, and add correct constraint boundaries on the corresponding structural finite element mesh nodes based on the constraint relationship between the target component and the environment According to the conditions, the statics solution can be selected as the solution type of the structural finite element model, and the selection of the solution parameters is completed based on the analysis requirements, and then the creation of the structural finite element model is completed.

Step S12: screen out the surface grid points from the structural finite element model, and screen out several target surface grid points from the surface grid points based on the preset compliance matrix scale and the preset load transfer loading requirements, to get the target grid point set.

In this embodiment, the filtering of the surface grid points from the structural finite element model specifically includes: selecting the surface grid points from the structural finite element model by using the surface element connection relationship analysis method; or, using the surface element normal direction The feature analysis method selects the surface mesh points from the structural finite element model. Based on the preset compliance matrix scale and the preset load transfer loading requirements, a number of target surface grid points P _i are selected from the surface grid points by manual selection or algorithm screening to obtain the target grid point set P, The target surface grid point P _i is the grid point used for load transfer.

Step S13 : respectively acquiring 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 the sequence of the preset degrees of freedom to obtain a structural compliance matrix of the target component, so as to perform a static aeroelastic coupling simulation of the target component based on the structural compliance matrix.

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 , a unit load in the x direction is applied to P _i , a preset statics solution is performed, and the obtained and stored Displacement response dXYZ ₁ of all grid points of the target grid point set P, and then clear all loads;

Apply a unit load in the y direction to Pi, perform a preset statics solution, obtain and store the displacement responses _{dXYZ 2} of all grid points in the target grid point set P, and then clear all loads; apply a unit load in the z direction to _Pi , perform a preset statics solution, obtain and store the displacement responses dXYZ ₃ of all grid points in the target grid point set P, and then remove all loads. It can be understood that all grid points in the target grid point set P are traversed, and unit loads are sequentially applied in the x, y, and z degrees of freedom directions on each grid point in the target grid point set P, and Carry out a preset static analysis to obtain the displacement responses of all grid points of the target grid point set P under the corresponding load.

In this embodiment, based on the preset order of degrees of freedom, the displacement responses dXYZ ₁ , dXYZ ₂ , and dXYZ ₃ of each target surface grid point are assembled to obtain the structural compliance matrix C of the target component, wherein the assembly relationship is as follows :

C=[dXYZ ¹ ... dXYZ ^w ... dXYZ ^N ];

dXYZ ^w =[dXYZ ₁ dXYZ ₂ dXYZ ₃ ] ^w ;

In the formula, 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, and w represents the wth in the target grid point set P. A unit load is applied to each grid point, i represents the displacement response at the ith grid point in the target grid point set P, and xForce, yForce, and zForce represent the result obtained by applying a unit load in the x, y, and z degrees of freedom directions, respectively. Displacement response of grid points.

In this embodiment, the generated structural compliance matrix can be output as a structural compliance matrix file according to a specific data format, which can be used as an input data file for other software modules, so that other software modules can perform related calculations based on the structural compliance matrix file, For example, it can be used as an input data file when performing a coupled static and aeroelastic simulation to perform a coupled static and aeroelastic simulation of a target component in a target aircraft.

It can be seen that the present application generates 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 based on the structural finite element calculation grid, the corresponding solution type and solution parameters, create a structural finite element model of the target component; screen out surface mesh points from the structural finite element model, and select the surface mesh points from the surface mesh points based on a preset compliance matrix scale and preset load transfer loading requirements Screen out a number of target surface grid points to obtain a target grid point set; respectively obtain the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom, and based on the preset In order of degrees of freedom, each of the displacement responses is assembled to obtain a structural compliance matrix of the target component, so as to perform a static aeroelastic coupling simulation of the target component based on the structural compliance matrix. It can be seen that the present application generates a structural finite element calculation grid based on the relevant information of the discrete elements 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 The displacement response of the target grid point set in the structural finite element model is assembled to obtain the structural compliance matrix of the target component, and there is no need to calculate the inverse matrix of the stiffness matrix to obtain the structural compliance matrix of the target component, which improves the acquisition of the structure of the target component. Flexibility and ease of compliance matrix.

Referring to FIG. 2 , an embodiment of the present application discloses a specific method for generating a structural compliance matrix based on a structural finite element model, including:

Step S21 : Determine the discrete unit type, discrete unit size and discrete unit distribution corresponding to the target component based on the geometric characteristics and analysis accuracy requirements of the target component in the target aircraft.

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

Step S22: Generate a structural finite element calculation grid based on the discrete element type, the discrete element size, and the discrete element distribution, and create a finite element calculation grid based on the structural finite element calculation grid, the corresponding solution type, and the solution parameters. Describe the structural finite element model of the target component.

In this embodiment, for example, a schematic diagram of a specific structural finite element calculation grid shown in FIG. 4 , a structural finite element calculation grid is generated based on the type, size and distribution of the discrete elements 2 , and 17 plates are set in the length direction of the flat plate member 1 . The grid points, 5 grid points in the width direction, and 2 grid points in the thickness direction are set. The grid points 3 in the three directions are uniformly distributed. The structural finite element calculation mesh.

In this embodiment, creating 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 structural finite element using material parameters of the target component The constitutive relationship of the model, and the corresponding constraint boundary conditions are added to the nodes of the structural finite element calculation grid; the corresponding solution type and solution parameters are selected, and based on the constitutive relationship, the constraint boundary conditions, the According to the solution type and the solution parameters, a structural finite element model of the target component is created. For example, using steel material to define material parameters such as elastic modulus, Poisson's ratio, and density based on plate component 1 to determine the constitutive relationship of the material of the structural finite element model, such as the schematic diagram of a specific structural finite element model shown in Figure 5, based on The right end of the plate component 1 is clamped, and the clamp constraint 4 is added to the corresponding right end face 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 iterative method can be completed according to the analysis requirements, etc. The selection of solving parameters is completed to complete the creation of the finite element model of the structure.

Step S23: screen out surface mesh points from the structural finite element model, and screen out a number of target surface mesh points from the surface mesh points based on a preset compliance matrix scale and a preset load transfer loading requirement, to get the target grid point set.

In this embodiment, all 170 surface mesh points of the plate part 1 are selected from all the mesh points of the structural finite element model of the plate part 1 by the surface element connection relationship analysis method or the surface element normal feature analysis method. For example, a schematic diagram of a specific target surface node selection shown in Figure 6, based on the preset flexibility matrix scale and preset load transfer loading requirements, through manual selection or algorithm screening, from 170 surface grid points. 70 target surface nodes are selected to form the target grid point set P for solving the structural compliance matrix of the plate component 1.

Step S24: respectively acquiring 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 the sequence of the preset degrees of freedom to obtain a structural compliance matrix of the target component, so as to perform a static aeroelastic coupling simulation of the target component based on the structural compliance matrix.

In this embodiment, the separately acquiring the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom specifically includes: acquiring each of the target grid points in the target grid point set. The displacement responses of all the target surface grid points in the target grid point set when the target surface grid points are in the x direction, the y direction and the z direction respectively.

In this embodiment, when each of the target surface mesh points in the acquired target mesh point set is in the x direction, the y direction and the z direction respectively, all the target surface meshes in the target mesh point set are The displacement response of the point, 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 solving based on preset statics The algorithm obtains the first displacement response of all the target surface grid points in the target grid point set, and then clears the current unit load of the target surface grid points in the x direction; for the current target surface A unit load in the y direction is applied to the grid points, and the 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 current target surface grid points are cleared. The unit load in the y direction; apply a unit load in the z direction to the current target surface mesh point, and obtain all the target surface meshes in the target mesh point set based on a preset statics solution algorithm The third displacement response of the point, then clears the unit load in the z direction for the current target surface mesh point.

In this embodiment, after assembling each of the displacement responses to obtain the structural compliance matrix of the target component based on a preset order of degrees of freedom, the method further includes: under different preset load loading conditions, using Several first structural displacements and corresponding several second structural displacements calculated by the structural finite element model and the compliance matrix method, and several first structural displacements and corresponding several second structural displacements are calculated respectively. Several displacement differences between the structural displacements, and then screen out the target displacement differences that meet the preset conditions from the several displacement differences; determine whether the target displacement differences are greater than the preset difference threshold, if not, determine that the structural flexibility The degree matrix meets the preset requirements; if it is, it is determined that the structural compliance matrix does not meet the preset requirements, and jumps to the generated structure based on the discrete element type, discrete element size and discrete element distribution corresponding to the target component. Steps for finite element calculation of meshes. As shown in Figure 7, a specific schematic diagram of structural compliance matrix verification, under the preset load loading condition 1, the first structural displacement 1 and the second structural displacement are calculated by using the structural finite element model and the flexibility matrix method respectively. 1. Under the preset load loading condition 2, the first structural displacement 2 and the second structural displacement 2 are calculated by using the structural finite element model and the flexibility matrix method respectively. Under the preset load loading condition N, the structural finite element model and the Metamodel and compliance matrix method to calculate the displacement N of the first structure and the displacement N of the second structure; calculate the displacement difference between the displacement 1 of the first structure and the displacement 1 of the second structure 1, calculate the displacement of the first structure 2 and the displacement of the second structure Displacement difference 2 between displacement 2, ... Calculate the displacement difference N between the first structure displacement N and the second structure displacement N; determine the maximum displacement difference from the displacement difference 1, displacement difference 2, ... displacement difference N as the target Displacement difference, and determine whether the target displacement difference is greater than the preset difference threshold; if otherwise, it is determined that the structural compliance matrix meets the preset requirements, that is, a correct structural compliance matrix is generated; if so, it is determined that the structural compliance matrix does not meet the preset requirements. request, that is, an incorrect structural compliance matrix is generated, and jump to the step of generating a structural finite element calculation grid based on the discrete element type, discrete element size and discrete element 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 compliance matrix meets the preset requirements, thereby ensuring the reliability of the subsequent static aeroelastic coupling simulation using the structural compliance matrix.

It can be seen that the structural flexibility matrix generation method in this application is not only applicable to all the degrees of freedom of grid nodes, 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 The ease of generating the structural flexibility matrix of the structural finite element model, and the application can also check the correctness of the structural flexibility matrix, so that when the structural flexibility matrix is used for the subsequent static aeroelastic coupling simulation, it is possible to avoid problems caused by structural flexibility. A situation where the matrix is incorrect and the simulation results are wrong.

Referring to FIG. 8 , an embodiment of the present application discloses a device for generating a structural compliance matrix based on a structural finite element model, including:

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 based on the structural finite element calculation grid, the corresponding solution type and solution parameters to create a structural finite element model of the target component;

The grid point set acquisition module 12 is used to filter out the surface grid points from the finite element model of the structure, and select a number of surface grid points from the surface grid points based on the preset compliance matrix scale and the preset load transfer loading requirements target surface grid points to obtain the target grid point set;

The matrix acquisition module 13 is used to separately acquire the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom, and based on the preset degree of freedom sequence, each of the displacement responses Assembling is performed to obtain a structural compliance matrix of the target component so as to perform a static aeroelastic coupling simulation of the target component based on the structural compliance matrix.

It can be seen that the present application generates 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 based on the structural finite element calculation grid, the corresponding solution type and solution parameters, create a structural finite element model of the target component; screen out surface mesh points from the structural finite element model, and select the surface mesh points from the surface mesh points based on a preset compliance matrix scale and preset load transfer loading requirements Screen out a number of target surface grid points to obtain a target grid point set; respectively obtain the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom, and based on the preset In order of degrees of freedom, each of the displacement responses is assembled to obtain a structural compliance matrix of the target component, so as to perform a static aeroelastic coupling simulation of the target component based on the structural compliance matrix. It can be seen that the present application generates a structural finite element calculation grid based on the relevant information of the discrete elements 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 The displacement response of the target grid point set in the structural finite element model is assembled to obtain the structural compliance matrix of the target component, and there is no need to calculate the inverse matrix of the stiffness matrix to obtain the structural compliance matrix of the target component, which improves the acquisition of the structure of the target component. Flexibility and ease of compliance matrix.

FIG. 9 is a schematic structural diagram of an electronic device according to 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 and output interface 25 and a communication bus 26 . Wherein, the memory 22 is used to store a computer program, and the computer program is loaded and executed by the processor 21 to realize the structural compliance matrix based on the structural finite element model and executed by the electronic device disclosed in any of the foregoing embodiments. Relevant steps in the generation method.

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 external devices, and the communication protocol it follows is applicable to this Any communication protocol applying for the technical solution 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, which is not carried out here. Specific restrictions.

The processor 21 may include one or more processing cores, such as a 4-core processor, an 8-core processor, and the like. The processor 21 may use at least one hardware form among DSP (Digital Signal Processing, digital signal processing), FPGA (Field-Programmable Gate Array, field programmable gate array), PLA (Programmable Logic Array, programmable logic array) accomplish. The processor 21 may also include a main processor and a coprocessor. The main processor is a processor used to process data in the wake-up state, also called a CPU (Central Processing Unit, central processing unit); A low-power processor for processing data in a standby state. In some embodiments, the processor 21 may be integrated with a GPU (Graphics Processing Unit, image processor), and the GPU is used for rendering and drawing the content that needs to be displayed on the display screen. In some embodiments, the processor 21 may further include an AI (Artificial Intelligence, artificial intelligence) processor, where the AI processor is used to process computing operations related to machine learning.

In addition, the memory 22, as a carrier for resource storage, can be a read-only memory, a random access memory, a magnetic disk or an optical disk, etc. The resources stored on the memory 22 include the operating system 221, the computer program 222 and the data 223, etc., and the storage method can be short-term storage or Permanent storage.

The operating system 221 is used to manage and control various hardware devices and computer programs 222 on the electronic device, so as 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 the computer program 222 that can be used to complete the method for generating a structural compliance matrix based on a structural finite element model disclosed in any of the foregoing embodiments, the computer program 222 can further include a computer program that can be used to complete other specific tasks. computer program. The data 223 may not only include the data received by the electronic device and transmitted from the external device, but also may include the data collected by the own input/output interface 25 and the like.

Further, an embodiment of the present application further discloses a computer-readable storage medium, where a computer program is stored in the storage medium, and when the computer program is loaded and executed by a processor, the computer program disclosed in any of the foregoing embodiments can be implemented based on a computer program. Method steps performed during the generation of a structural compliance matrix for a structural finite element model.

Finally, it should also 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 these entities or that there is any such actual relationship or sequence between operations. Moreover, the terms "comprising", "comprising" or any other variation thereof are intended to encompass a non-exclusive inclusion such that a process, method, article or device that includes a list of elements includes not only those elements, but also includes not explicitly listed or other elements inherent to such a process, method, article or apparatus. Without further limitation, an element qualified by the phrase "comprising a..." does not preclude the presence of additional identical elements in a process, method, article or apparatus that includes the element.

The method, device, equipment and medium for generating a structural compliance matrix based on a structural finite element model provided by the present invention have been described in detail above. The principles and implementations of the present invention are described with specific examples in this paper. The description of the embodiment is only used to help understand the method of the present invention and its core idea; meanwhile, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in specific embodiments and application scope. As mentioned above, the contents of this specification should not be construed as limiting the present invention.

Claims (10)

1. a structural flexibility matrix generation method based on a structural finite element model, is characterized in that, comprising: Based on the discrete element type, discrete element size, and discrete element distribution corresponding to the target component in the target aircraft, a structural finite element calculation grid is generated, and based on the structural finite element calculation grid, the corresponding solution type, and the solution parameters, all Describe the structural finite element model of the target component; Screen out surface mesh points from the structural finite element model, and screen out several target surface mesh points from the surface mesh points based on the preset compliance matrix scale and preset load transfer loading requirements to obtain the target grid point set; Obtain the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom respectively, and assemble each of the displacement responses based on the preset degree of freedom sequence to obtain the target A structural compliance matrix of the component, so as to perform a static aeroelastic coupling simulation of the target component based on the structural compliance matrix. 2 . The method for generating a structural compliance matrix based on a structural finite element model according to claim 1 , wherein the structural finite element calculation is generated based on the discrete element type, discrete element size and discrete element distribution corresponding to the target component. 3 . Before the grid, also include: 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 compliance matrix based on a structural finite element model according to claim 1 , wherein the target is created based on the structural finite element calculation grid, corresponding solution types and solution parameters. 4 . Structural finite element model of the component, including: Determine the constitutive relationship of the structural finite element model by using the material parameters of the target component, and add corresponding constraint boundary conditions on the nodes of the structural finite element calculation grid; A corresponding solution type and solution parameter are selected, and based on the constitutive relation, the constrained boundary condition, the solution type and the solution parameter, a structural finite element model of the target component is created. 4. The method for generating a structural compliance matrix based on a structural finite element model according to claim 1, wherein the filtering of surface mesh points from the structural finite element model comprises: The surface mesh points are screened out from the structural finite element model using the surface element connection relationship analysis method; Or, the surface mesh points are screened out from the structural finite element model by using the surface element normal feature analysis method. 5 . The method for generating a structural compliance matrix based on a structural finite element model according to claim 1 , wherein the acquisition of all the target surface grid points in the target grid point set respectively is in different preset freedoms. 6 . displacement response in degrees, including: Acquire the displacement responses of all the target surface grid points in the target grid point set when each of the target surface grid points in the target grid point set is in the x direction, the y direction and the z direction respectively. 6 . The method for generating a structural compliance matrix based on a structural finite element model according to claim 5 , wherein the acquisition of each of the target surface grid points in the target grid point set is respectively in the x direction, 6 . The displacement responses of all the target surface grid points in the target grid point set in the y direction and the z direction, including: The current target surface grid point is arbitrarily selected 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 responses of all the target surface grid points in the target grid point set based on a preset statics solution algorithm, and then clear the current the unit load of the target surface grid point in the x direction; Apply a unit load in the y direction to the current target surface grid point, and obtain the second displacement responses of all the target surface grid points in the target grid point set based on a preset statics solution algorithm, and then clear the current the unit load of the target surface grid point in the y direction; Apply a unit load in the z-direction to the current target surface grid point, and obtain the 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 clear the current the unit load of the target surface grid point in the z direction. 7. The method for generating a structural compliance matrix based on a structural finite element model according to any one of claims 1 to 6, wherein the displacement response is assembled based on a preset order of degrees of freedom to After the structural compliance matrix of the target component is obtained, it also includes: Under different preset load loading conditions, several first structural displacements and corresponding several second structural displacements calculated by the structural finite element model and the flexibility matrix method are respectively used, and several first structural displacements are calculated respectively. several displacement differences between the structural displacement and the corresponding several second structural displacements, and then screen out the target displacement differences that meet the preset conditions from the several displacement differences; Determine whether the target displacement difference is greater than a preset difference threshold, if not, determine that the structural compliance matrix meets the preset requirements; if so, determine that the structural compliance matrix does not meet the preset requirements, and re-jump to the Describe the steps of generating a structural finite element calculation grid based on the discrete element type, discrete element size and discrete element distribution corresponding to the target component. 8. A device for generating a structural compliance matrix based on a structural finite element model, comprising: The model creation module 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 based on the structural finite element calculation grid, the corresponding solution type and solving parameters to create a structural finite element model of the target component; The grid point set acquisition module is used to filter out the surface grid points from the finite element model of the structure, and select several surface grid points from the surface grid points based on the preset compliance matrix scale and the preset load transfer loading requirements target surface grid points to get the target grid point set; A matrix acquisition module is used to separately acquire the displacement responses of all the target surface grid points in the target grid point set under different preset degrees of freedom, and based on the preset degree of freedom sequence, each of the displacement responses is performed. Assembling to obtain a structural compliance matrix of the target component, so as to perform a static aeroelastic coupling simulation on the target component based on the structural compliance matrix. 9. An electronic device, characterized in that, comprising: memory for storing computer programs; The processor is configured to execute the computer program to implement the steps of the method for generating a structural compliance matrix based on a structural finite element model according to any one of claims 1 to 7. 10. A computer-readable storage medium, characterized in that it is used for storing a computer program; wherein, when the computer program is executed by a processor, the method according to any one of claims 1 to 7 based on a structural finite element model is implemented. Steps of the structural compliance matrix generation method.

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