A dynamic aeroelastic calculation method based on structural reduced-order model

Abstract

The present invention discloses a method for dynamic aeroelastic calculation based on a structural order reduction model. The method comprises: constructing a three-dimensional model of the component to be analyzed and performing modal analysis to obtain the various modes and structural vibration shapes of the component structure; simplifying the three-dimensional model of the component to obtain the component's aerodynamic shape; generating a flow field grid for aerodynamic calculation based on the component's aerodynamic shape; using a radial basis function neural network to interpolate the flow field grid based on the various modes and structural vibration shapes of the component structure to obtain interpolated results of the structural vibration shapes; based on the interpolated results of the structural vibration shapes, using computational fluid dynamics methods to first calculate unsteady aerodynamic forces, and then using structural model order reduction methods to calculate transient displacements to obtain aeroelastic response results. The method of the present invention can effectively improve the accuracy and efficiency of aeroelastic calculations.

Description

Technical Field

[0001] The present invention belongs to the field of aircraft aerodynamics, and in particular relates to a dynamic aeroelasticity calculation method based on a structural order reduction model. Background Art

[0002] As material technologies and manufacturing processes mature and design methods become more advanced, aircraft slenderness / aspect ratios are becoming increasingly larger. With the continuous increase in slenderness and wingspan, coupled with the urgent need for weight reduction, aircraft stiffness is becoming relatively low, and aeroelastic analysis is becoming increasingly important in aircraft design. Flutter is a typical aeroelastic phenomenon. This self-excited vibration can cause structural vibration and damage in just a few seconds. The consequences of this highly destructive aeroelastic phenomenon in the aerospace field are extremely serious. Due to the extremely destructive nature of flutter, conducting critical and supercritical flutter flight tests is very difficult. Furthermore, due to the high cost and long test cycles of wind tunnel testing, numerical analysis has become a primary method for studying aircraft flutter characteristics.

[0003] Among existing aeroelastic numerical analysis methods, one type involves frequency-domain methods that simplify unsteady aerodynamic forces based on potential flow and linearized equations. These methods use flutter determinants to determine critical points, resulting in high computational efficiency but difficulty accounting for the effects of aerodynamic nonlinearities, such as the complex geometry of the aircraft and variations in shock wave position and intensity. Another type involves time-domain methods that couple computational fluid dynamics (CFD) with structural finite element methods. While these methods offer high accuracy in solving unsteady aerodynamic loads and transient structural displacements, they suffer from poor convergence and computational efficiency. Furthermore, finite element methods make it difficult to analyze the mechanisms of structural dynamic characteristics. Summary of the Invention

[0004] The purpose of the present invention is to provide a dynamic aeroelastic calculation method based on a structural reduced-order model to improve the accuracy and efficiency of aeroelastic calculations.

[0005] In order to achieve the above tasks, the present invention adopts the following technical solutions:

[0006] A dynamic aeroelastic calculation method based on a structural reduced-order model includes:

[0007] Construct a three-dimensional model for the component to be analyzed and perform modal analysis to obtain the various modes and structural vibration shapes of the component structure;

[0008] Simplify the three-dimensional model of the component to obtain the aerodynamic shape of the component; generate the flow field grid for aerodynamic calculation based on the aerodynamic shape of the component;

[0009] Using radial basis function neural network, the flow field grid is interpolated based on the various modes and structural vibration shapes of the component structure to obtain the interpolation results of the structural vibration shape;

[0010] Based on the interpolation results of the structural vibration mode, the computational fluid dynamics method is used to first calculate the unsteady aerodynamic force, and then the transient displacement is calculated using the structural model reduction method to obtain the aeroelastic response results.

[0011] Furthermore, the three-dimensional model is constructed for the component to be analyzed and modal analysis is performed to obtain various modes and structural vibration shapes of the component structure, including:

[0012] Use modeling software to build a three-dimensional model of the component and divide the finite element mesh, set the material properties of the component, define constraints and external loads, build the local stiffness matrix and mass matrix of the component, and assemble the global stiffness matrix and mass matrix; by solving the generalized eigenvalue problem, the eigenvalues ​​and eigenvectors obtained are the various modes and structural vibration shapes of the component structure.

[0013] Furthermore, the simplification of the three-dimensional model of the component to obtain the aerodynamic shape of the component includes:

[0014] First, the internal structure of the component's 3D model is deleted and only the outer surface of the component's 3D model is retained. After removing complex local details that have little impact on aerodynamics, a concise and complete aerodynamic shape of the component is obtained.

[0015] Furthermore, the generation of a flow field grid for aerodynamic calculation of the aerodynamic shape of the component includes:

[0016] The flow field grid includes a surface grid and a volume grid, wherein:

[0017] When generating the surface mesh, regular areas on the aerodynamic shape are divided into quadrilateral structured surface meshes, and irregular areas are filled with triangular unstructured meshes. The surface mesh of the head and leading edge areas of the aerodynamic shape is refined along the direction of flow change. The surface mesh of the far-field boundary is a uniform triangular mesh with a size that matches the component.

[0018] When generating a volume mesh, the volume mesh includes a prismatic mesh of the boundary layer of the aerodynamic shape. The Reynolds number model and the number of prismatic mesh layers are set, and the height of the prismatic mesh increases exponentially starting from the first layer. After all prismatic meshes are generated, tetrahedral meshes are used to fill the remaining space except for the surface mesh and volume mesh to obtain the entire flow field mesh of the aerodynamic shape.

[0019] Furthermore, the height of the first layer of prism grid on the boundary layer is given by the following formula:

[0020] ;

[0021] in:

[0022] ;

[0023] In the above formula, is the height of the first prism grid, is the dimensionless wall distance, are the kinematic viscosity, density, velocity and dynamic viscosity of the incoming flow, is the wall friction velocity, is the wall shear stress, is the coefficient of surface friction, is the characteristic length of the aerodynamic shape, and Re is the Reynolds number.

[0024] Furthermore, the radial basis function neural network is used to interpolate the flow field grid based on the various modes and structural vibration shapes of the component structure to obtain the interpolation result of the structural vibration shape, including:

[0025] The kernel function of the radial basis function neural network uses a Gaussian function; the coordinates of the finite element grid of the three-dimensional model, the modes of each order on the finite element grid and the structural vibration shapes are used as input vectors to train the radial basis function neural network to obtain a fitting model of the spatial distribution of the structural vibration shapes; the coordinates of the flow field grid are input into the fitting model, and the output of the fitting model is the interpolation result of the structural vibration shapes from the finite element grid to the flow field grid.

[0026] Furthermore, the computational fluid dynamics method is used to calculate the unsteady aerodynamic force, including:

[0027] First, the density-based or pressure-based solver of Fluent software is used, and the second-order method is used for spatial discretization. Based on the interpolation results of the structural vibration mode, multiple implicit iterative calculations are performed to converge to obtain the steady flow field, where the governing equation is the NS equation.

[0028] Secondly, after the steady flow field calculation is completed, the unsteady calculation mode is switched to. The physical time step and total calculation time are set based on the period of each mode of the component structure. The externally compiled UDF code is loaded, and the initial value of the generalized velocity of the first-order mode of the component structure is assigned to apply the initial disturbance, and the fluid-structure coupling unsteady calculation begins. The UDF code is responsible for calculating the unsteady aerodynamic force of each mode within each physical time step.

[0029] Furthermore, the calculation of transient displacement using a structural model order reduction method includes:

[0030] Based on the modal superposition method, the displacement of each mode is solved and the structural dynamics reduced-order model is constructed;

[0031] The displacement and velocity of each mode are used to construct state variables, and the structural equation is established based on the state variables;

[0032] A linear multi-step method with second-order explicit / implicit hybridization is used to solve the structural equations and obtain the estimated values ​​of the state variables at the next moment;

[0033] The transient displacement of the structure at the next moment is obtained by superimposing the modes based on the estimated values.

[0034] Furthermore, the calculation of transient displacement using a structural model order reduction method further includes:

[0035] The surface position of the aerodynamic shape is updated, and finally the mesh deformation function is used to update the position of all flow field meshes. After the flow field mesh position is updated, the next physical time step is entered, and the calculation process of unsteady aerodynamic forces and transient displacements is repeated. The unsteady aerodynamic forces are calculated first, and then the transient displacements of the structure are calculated. The calculation stops after the given total calculation time is reached.

[0036] A terminal device includes a processor, a memory, and a computer program stored in the memory; when the processor executes the computer program, the dynamic aeroelasticity calculation method based on the structural reduced-order model is implemented.

[0037] A computer-readable storage medium stores a computer program; when the computer program is executed by a processor, the dynamic aeroelasticity calculation method based on a structural reduced-order model is implemented.

[0038] Compared with the prior art, the present invention has the following technical features:

[0039] 1. High-precision and efficient structural calculation: A structural reduction model is used to solve structural displacements. Compared with the finite element method, this method ensures displacement solution accuracy while greatly reducing the degrees of freedom. The structural displacement solution time within each time step is reduced to seconds, significantly improving computational efficiency.

[0040] 2. The computational fluid dynamics (CFD) method is used to solve the aerodynamic forces, and the structural reduction model is used to solve the structural displacements. The unsteady coupling of the two forms a highly accurate and efficient dynamic aeroelastic calculation method, which is more convenient for the mechanism analysis of aeroelastic problems than the finite element method. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 A schematic flow chart of a method according to an embodiment of the present invention;

[0042] Figure 2 A flow field spatial grid diagram in one embodiment of the present invention;

[0043] Figure 3 The vibration response of the structure near the flutter critical speed in one embodiment of the present invention;

[0044] Figure 4 Comparison between calculation and experiment of critical flutter speed in one embodiment of the present invention;

[0045] Figure 5 Calculation and experimental comparison of the flutter critical frequency in one embodiment of the present invention. DETAILED DESCRIPTION

[0046] The present invention provides a dynamic aeroelastic calculation method based on a structural reduced-order model. The unsteady aerodynamic force is calculated using a high-precision computational fluid dynamics (CFD) method, and the transient displacement of the structure is calculated using a structural reduced-order model, providing a high-precision and efficient numerical calculation method for the analysis of aeroelastic problems of elastic aircraft.

[0047] A dynamic aeroelastic calculation method based on a reduced-order structural model, see Figure 1 , including the following steps:

[0048] Step 1: Build a 3D model for the component to be analyzed and perform modal analysis to obtain the various modes and structural vibration shapes of the component structure.

[0049] Use modeling software to build a three-dimensional model of the component and divide the finite element mesh, set the material properties of the component, define constraints and external loads, build the local stiffness matrix and mass matrix of the component, and assemble the global stiffness matrix and mass matrix; by solving the generalized eigenvalue problem, the eigenvalues ​​and eigenvectors obtained are the various modes and structural vibration shapes of the component structure.

[0050] Step 2: Simplify the three-dimensional model of the component to obtain the aerodynamic shape of the component; generate a flow field grid for aerodynamic calculation based on the aerodynamic shape of the component.

[0051] Among them, when simplifying the three-dimensional model of the component, the internal structure of the three-dimensional model of the component is first deleted and only the outer surface of the three-dimensional model of the component is retained. After removing the complex local details that have little impact on aerodynamics (which can be specified by setting a threshold or based on experience), a concise and complete aerodynamic shape of the component is obtained.

[0052] Perform flow field meshing on the aerodynamic shape; the flow field mesh includes surface mesh and volume mesh, where:

[0053] When generating surface meshes, regular areas on the aerodynamic shape (for example, when the component is a wing, the wing surface is a regular area) are divided into quadrilateral structured surface meshes, and irregular areas are filled with triangular unstructured meshes; the surface meshes are encrypted along the direction of flow change in areas where the flow changes drastically, such as the head and leading edge of the aerodynamic shape; and the distance between the far-field boundary and the aerodynamic shape is no less than 20 times the length of the component, and the surface mesh of the far-field boundary is a uniform triangular mesh of a size comparable to that of the component.

[0054] When generating the volume mesh, the volume mesh includes the prismatic mesh of the aerodynamic shape boundary layer; the Reynolds number model and the number of prismatic mesh layers are set (about 30 layers of prismatic mesh are generated), and the height of the prismatic mesh increases exponentially from the first layer, with a growth rate of about 1.2 to ensure that there are enough prismatic meshes in the boundary layer and the transition is natural; after all the prismatic meshes are generated, tetrahedral meshes are used to fill the remaining space except for the surface mesh and volume mesh to obtain the entire flow field mesh of the aerodynamic shape.

[0055] The height of the first prism grid on the boundary layer is given by the following formula:

[0056] ;

[0057] in:

[0058] ;

[0059] In the above formula, is the height of the first prism grid, is the dimensionless wall distance, are the kinematic viscosity, density, velocity and dynamic viscosity of the incoming flow, is the wall friction velocity, is the wall shear stress, is the coefficient of surface friction, is the characteristic length of the aerodynamic shape, and Re is the Reynolds number. For high Reynolds number models, such as Model, Reynolds stress model, etc. Take about 30, for low Reynolds number models, such as SA model, Models, etc. Take about 1.

[0060] Step three: Using radial basis function neural network, interpolate the flow field grid based on the various modes and structural vibration shapes of the component structure to obtain the interpolation results of the structural vibration shapes.

[0061] This step uses a radial basis function (RBF) neural network, whose kernel function uses the widely used Gaussian function; the coordinates of the finite element grid of the three-dimensional model in step one, the modes of each order on the finite element grid, and the structural vibration shapes are used as input vectors to train the radial basis function neural network to obtain a fitting model of the spatial distribution of the structural vibration shapes; the coordinates of the flow field grid are input into the fitting model, and the output of the fitting model is the interpolation result of the structural vibration shapes from the finite element grid to the flow field grid.

[0062] Step 4: Based on the interpolation results of the structural vibration mode, the computational fluid dynamics method is used to first calculate the unsteady aerodynamic force, and then the structural model reduction method is used to calculate the transient displacement to obtain the aeroelastic response result.

[0063] The computational fluid dynamics method is used to first calculate the unsteady aerodynamic force, including:

[0064] First, the density-based or pressure-based solver of Fluent software is used, and the second-order method is used for spatial discretization. Multiple implicit iterative calculations are performed based on the interpolation results of the structural vibration mode to converge to obtain the steady flow field, where the governing equation is the NS equation:

[0065] ;

[0066] In the formula 、 and are the conserved variables, convective flux and viscous flux, respectively. 、 are discrete control volumes and volume elements, 、 、 is the component surface, the surface unit normal vector and the area element, is the time parameter.

[0067] Secondly, after the steady flow field calculation is completed, the unsteady calculation mode is switched to. To ensure sufficient unsteady time simulation accuracy, the physical time step is no less than 1 / 50 of the minimum period in each mode of the component structure. To clearly and accurately judge the response trend of the structural vibration, the total calculation time exceeds 10 times the longest period in each mode of the component structure. The externally compiled UDF code is loaded, and the initial value of the generalized velocity of the first-order mode of the component structure is assigned to the initial perturbation in the range of 0.001 to 0.01, and the fluid-structure coupling unsteady calculation is started. The UDF code is responsible for calculating the unsteady aerodynamic force of each mode in each physical time step.

[0068] The method of calculating transient displacement by using a structural model order reduction method includes:

[0069] Based on the modal superposition method, the displacement of each mode is solved, and the corresponding structural dynamics reduced-order model is:

[0070] ;

[0071] In the formula are the generalized displacement, generalized mass, generalized damping, generalized stiffness and generalized aerodynamic force matrices of the structural mode respectively; 、 represents generalized velocity and generalized acceleration.

[0072] Introducing state variables ,in 、 Indicates the The displacement and velocity of the modal order, n represents the total modal order, and the superscript T represents the transpose.

[0073] Constructing the structural equation:

[0074] ;

[0075] Where, Represents state variables The first derivative of , , is a zero matrix, is the identity matrix; Representation and structural transient displacement, time Related functions.

[0076] The second-order explicit / implicit hybrid linear multi-step method is used to solve the structural equation and obtain the displacement at the next moment:

[0077] ;

[0078] ;

[0079] In the formula is the time increment, are the state variables of the previous moment, current moment and next moment respectively, are the generalized aerodynamic forces at the previous moment, the current moment, and the next moment, respectively. is the estimated value of the state variable at the next moment;

[0080] Based on the estimated The displacement of the first mode is obtained by modal superposition, and the transient displacement of the structure at the next moment is obtained:

[0081] ;

[0082] In the formula is the transient displacement of the structure, 、 Respectively The displacement and structural vibration shape of the first mode, is the total modal order.

[0083] Finally, the GRID_MOTION function provided by Fluent is used to update the surface position of the aerodynamic shape. Finally, the grid deformation functions such as the spring method and the diffusion method are used to update the positions of all flow field grids. After the flow field grid positions are updated, the next physical time step is entered and the above steps are repeated. The unsteady aerodynamic force is calculated first and then the transient displacement of the structure is calculated. The calculation is stopped after the given total calculation time is reached.

[0084] Leveraging the high-precision and efficient numerical simulation capabilities of Fluent software, compared to self-developed CFD programs, it possesses a wealth of physical models and advanced algorithms, capable of simulating a variety of complex flow phenomena from incompressible to highly compressible, including laminar flow, turbulent flow, chemical reactions, heat transfer, etc.; high-performance parallel algorithms combined with a variety of acceleration algorithms significantly improve computational efficiency.

[0085] In one embodiment of the present invention, a wing is used as the component to be analyzed. After performing modal analysis, the generalized mass, frequency, and mode shape data of the first four wing modes are extracted. Based on the wing shape, a set of flow field grids required for aerodynamic calculations is generated, with the far-field boundary at a distance of no less than 20 times the wing length. Figure 2 As shown. The meshing can be done using ICEM, Pointwise and other software. The mesh type is unstructured mesh. The height of the first layer of prism mesh near the wall satisfies the dimensionless wall distance y. + The prismatic mesh in the boundary layer was generated to 30 layers. In Matlab, the radial basis function newrb was used to fit the spatial distribution of the vibration modes on the finite element mesh of the wing. The mesh node coordinates of the flow field mesh were then input into the fitted model to interpolate the vibration modes from the finite element mesh to the flow field mesh.

[0086] When performing unsteady aerodynamic calculations, the physical time step is 1 / 60 of the minimum period in each mode, and the total calculation time exceeds 20 times the maximum period in each mode. An initial perturbation is applied to the generalized velocity of the first-order structure mode within the range of 0.001, and the fluid-structure interaction unsteady calculation begins.

[0087] After the fluid-structure interaction unsteady calculation is completed, the time history results of the transient displacement stack for each mode are output. This transient displacement stacking yields the actual wing deformation, i.e., the time-dependent vibration response of the wing under aerodynamic loads. At the same Mach number, if the wing vibration amplitude gradually decays over time at a certain incoming flow velocity, then that velocity is below the critical flutter speed. Conversely, if the vibration amplitude increases exponentially with time, then that velocity is above the critical flutter speed. By gradually varying the incoming flow velocity range using this criterion, the critical flutter speed of the wing can be determined. The corresponding vibration frequency at this point is also the critical flutter frequency.

[0088] The critical flutter state of the wing at different Mach numbers was calculated. Figure 3 The figure shows the wing vibration response results under the working condition of Mach number Ma=0.678. When the speed is less than the flutter speed, the displacement of each modal decays to zero with time. Conversely, when the speed is greater than the flutter speed, the first-order and second-order modal displacements increase exponentially with time. Figure 4 and Figure 5The critical flutter speeds and frequencies at different Mach numbers obtained from experiments and calculations were compared. The calculated and experimental results were very consistent in terms of regularity and magnitude, and were able to better capture the typical "pit" phenomenon at transonic speeds. This shows that the dynamic aeroelastic calculation method based on the structural reduced-order model proposed in the present invention is reasonable. The time taken to solve the structural displacement in each step is less than 1% of the aerodynamic force calculation, which is greatly improved in efficiency compared to the finite element method.

[0089] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present application, and should all be included in the scope of protection of the present application.

Claims

1. A dynamic aeroelastic calculation method based on a structural reduced-order model, characterized in that: include: Construct a three-dimensional model for the component to be analyzed and perform modal analysis to obtain the various modes and structural vibration shapes of the component structure; Simplify the three-dimensional model of the component to obtain the aerodynamic shape of the component; generate the flow field grid for aerodynamic calculation based on the aerodynamic shape of the component, including: The flow field grid includes a surface grid and a volume grid, wherein: When generating the surface mesh, regular areas on the aerodynamic shape are divided into quadrilateral structured surface meshes, and irregular areas are filled with triangular unstructured meshes. The surface mesh of the head and leading edge areas of the aerodynamic shape is refined along the direction of flow change. The surface mesh of the far-field boundary is a uniform triangular mesh with a size that matches the component. When generating a volume mesh, the volume mesh includes prismatic meshes for the boundary layer of the aerodynamic shape. The Reynolds number model and the number of prismatic mesh layers are set, and the height of the prismatic mesh increases exponentially starting from the first layer. After all prismatic meshes are generated, tetrahedral meshes are used to fill the remaining space except for the surface meshes and volume meshes to obtain the entire flow field mesh of the aerodynamic shape. Using radial basis function neural network, the flow field grid is interpolated based on the various modes and structural vibration shapes of the component structure to obtain the interpolation results of the structural vibration shape; Based on the interpolation results of the structural vibration mode, the computational fluid dynamics method is used to first calculate the unsteady aerodynamic force, and then the transient displacement is calculated using the structural model reduction method to obtain the aeroelastic response results; The height of the first layer of prism grid on the boundary layer is given by the following formula: ； in: ； In the above formula, is the height of the first prism grid, is the dimensionless wall distance, are the kinematic viscosity, density, velocity and dynamic viscosity of the incoming flow, is the wall friction velocity, is the wall shear stress, is the surface friction coefficient, is the characteristic length of the aerodynamic shape, and Re is the Reynolds number.

2. The dynamic aeroelastic calculation method based on the structural reduced-order model according to claim 1 is characterized in that: The method of constructing a three-dimensional model of the component to be analyzed and performing modal analysis to obtain various modes and structural vibration shapes of the component structure includes: Use modeling software to build a three-dimensional model of the component and divide the finite element mesh, set the material properties of the component, define constraints and external loads, build the local stiffness matrix and mass matrix of the component, and assemble the global stiffness matrix and mass matrix; by solving the generalized eigenvalue problem, the eigenvalues ​​and eigenvectors obtained are the various modes and structural vibration shapes of the component structure.

3. The dynamic aeroelastic calculation method based on a structural reduced-order model according to claim 1, characterized in that: The simplification of the three-dimensional model of the component to obtain the aerodynamic shape of the component includes: First, the internal structure of the component's 3D model is deleted and only the outer surface of the component's 3D model is retained. After removing complex local details that have little impact on aerodynamics, a concise and complete aerodynamic shape of the component is obtained.

4. The dynamic aeroelastic calculation method based on a structural reduced-order model according to claim 1, characterized in that: The radial basis function neural network is used to interpolate the flow field grid based on the various modes and structural vibration shapes of the component structure to obtain the interpolation results of the structural vibration shape, including: The kernel function of the radial basis function neural network uses a Gaussian function; the coordinates of the finite element grid of the three-dimensional model, the modes of each order on the finite element grid and the structural vibration shapes are used as input vectors to train the radial basis function neural network to obtain a fitting model of the spatial distribution of the structural vibration shapes; the coordinates of the flow field grid are input into the fitting model, and the output of the fitting model is the interpolation result of the structural vibration shapes from the finite element grid to the flow field grid.

5. The dynamic aeroelastic calculation method based on a structural order reduction model according to claim 1, characterized in that: The computational fluid dynamics method is used to first calculate the unsteady aerodynamic force, including: First, the density-based or pressure-based solver of Fluent software is used, and the second-order method is used for spatial discretization. Based on the interpolation results of the structural vibration mode, multiple implicit iterative calculations are performed to converge to obtain the steady flow field, where the governing equation is the NS equation. Secondly, after the steady flow field calculation is completed, the unsteady calculation mode is switched to. The physical time step and total calculation time are set based on the period of each mode of the component structure. The externally compiled UDF code is loaded, and the initial value of the generalized velocity of the first-order mode of the component structure is assigned to apply the initial disturbance, and the fluid-structure coupling unsteady calculation begins. The UDF code is responsible for calculating the unsteady aerodynamic force of each mode within each physical time step.

6. The dynamic aeroelastic calculation method based on a structural order reduction model according to claim 1, characterized in that: The method of calculating transient displacement by using a structural model order reduction method includes: Based on the modal superposition method, the displacement of each mode is solved and a structural dynamics reduced-order model is constructed; The displacement and velocity of each mode are used to construct state variables, and the structural equation is established based on the state variables; A linear multi-step method with second-order explicit / implicit hybridization is used to solve the structural equations and obtain the estimated value of the state variables at the next moment; The transient displacement of the structure at the next moment is obtained by superimposing the modes based on the estimated values.

7. The dynamic aeroelastic calculation method based on a structural order reduction model according to claim 6, characterized in that: The method of calculating the transient displacement by using the structural model order reduction method further includes: The surface position of the aerodynamic shape is updated, and finally the mesh deformation function is used to update the position of all flow field meshes. After the flow field mesh position is updated, the next physical time step is entered, and the calculation process of unsteady aerodynamic forces and transient displacements is repeated. The unsteady aerodynamic forces are calculated first, and then the transient displacements of the structure are calculated. The calculation stops after the given total calculation time is reached.

8. A terminal device comprising a processor, a memory, and a computer program stored in the memory; characterized in that: When the processor executes the computer program, the dynamic aeroelasticity calculation method based on the structural reduced-order model according to any one of claims 1 to 7 is implemented.

9. A computer-readable storage medium storing a computer program; wherein: When the computer program is executed by a processor, the dynamic aeroelasticity calculation method based on a structural reduced-order model according to any one of claims 1 to 7 is implemented.

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