A numerical analysis method for static fluid-structure-thermal coupling of an aircraft

Abstract

The application discloses a kind of aircraft static fluid-structure-thermal coupling numerical analysis method, first solve the pressure distribution and heat flow distribution of the material surface CFD grid of geometric model, then it is interpolated to CSD grid using the local interpolation method of RBF, and solve the temperature distribution on the material surface CSD grid;Based on boundary condition, pressure distribution and heat flow distribution, the solution of structure statics is carried out to obtain the displacement distribution on the material surface part CSD grid;Temperature distribution and displacement distribution on CSD grid are interpolated to the material surface part CFD grid using the global interpolation method based on RBF;According to the displacement distribution obtained by interpolation, the original CFD grid of the material surface part is deformed using the grid deformation method based on RBF, to obtain the deformed CFD grid;For the deformed CFD grid, repeat the solution until the displacement distribution and temperature distribution on the material surface part CFD grid converge.This method can more accurately analyze the static fluid-structure-thermal coupling problem of complex configuration of aircraft.

Description

Technical Field

[0001] The present invention relates to the field of aerospace, and in particular to a numerical analysis method for static fluid-solid thermal coupling of an aircraft. Background Art

[0002] Hypersonic vehicles are a technological challenge for the future of aerospace. Structural weight constraints and intense aerodynamic heating reduce structural stiffness, leading to increasingly prominent static flow-solid thermal issues that seriously impact vehicle performance and safety. This complex, multidisciplinary problem involves coupling aerodynamic thermodynamics, unsteady aerodynamics, structural heat transfer, and structural dynamics. Therefore, this issue has become both a key and challenging area in current hypersonic research.

[0003] In the existing literature on static fluid-structure-thermal coupling, most studies and practical engineering applications still widely use engineering methods to predict aerodynamic forces and aeroheat. Unsteady aerodynamic forces are mostly calculated using piston theory, aeroheat is predicted using reference enthalpy or reference temperature methods, and structural dynamics or statics are mostly solved based on modal superposition. These analytical methods can efficiently obtain static fluid-structure-thermal coupling results in the early stages of engineering design, but they cannot accurately predict aeroheat, unsteady aerodynamic forces, and aeroheating processes in complex flow fields. They also ignore the impact of structural geometric nonlinearity on structural static solutions when deformation is large. Therefore, existing static fluid-structure-thermal coupling research methods have low computational accuracy and cannot meet the computational accuracy requirements for the development of new-generation high-speed aircraft. Summary of the Invention

[0004] The purpose of the present invention is to provide a numerical analysis method for static fluid-solid thermal coupling of an aircraft to overcome the problem of low calculation accuracy in existing methods.

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

[0006] A numerical analysis method for static fluid-structure thermal coupling of an aircraft, comprising:

[0007] Step 100: Construct a geometric model of the aircraft; generate a mesh for the geometric model based on the structural characteristics and material properties of the aircraft; configure simulation conditions based on the incoming flow conditions of the aircraft, solve the steady flow field, and obtain the pressure distribution and heat flux distribution of the CFD mesh on the surface of the geometric model;

[0008] Step 200 , using a local interpolation method based on radial basis functions, the pressure distribution and heat flux distribution of the surface CFD grid are interpolated point by point onto the finite element CSD grid of the aircraft geometric model. After the interpolation is completed, the surface heat flux distribution obtained by interpolation on the CSD grid and the material properties of the aircraft are combined to perform heat conduction analysis within the geometric model. The temperature distribution on the surface CSD grid is calculated by solving the heat conduction equation.

[0009] Step 300 , performing a structural statics solution based on the interpolation mapping results of the pressure distribution and the heat flux distribution on the CSD grid and the boundary conditions to obtain the displacement distribution on the CSD grid of the object surface;

[0010] Step 400, interpolating the temperature distribution and displacement distribution on the CSD grid to the CFD grid of the object surface using a global interpolation method based on RBF;

[0011] In step 500, based on the displacement distribution on the CSD mesh of the object surface portion obtained in step 300, the CFD mesh of the object surface portion in step 100 is deformed using an RBF-based mesh deformation method to obtain a deformed CFD mesh; steps 100 to 400 are repeatedly performed on the deformed CFD mesh until the displacement distribution and the temperature distribution on the CFD mesh of the object surface portion converge.

[0012] Furthermore, the mesh generation of the geometric model of the aircraft based on the structural characteristics and material properties of the aircraft includes:

[0013] Using simulation software, a CFD mesh suitable for fluid-structure thermal coupling analysis is generated for the aircraft's geometric model. Taking into account the aircraft's structural characteristics, a structured mesh is used for parts of the geometric model with regular shapes and simple topology, segmented based on the model's characteristic lines and surfaces. For parts of the geometric model with complex shapes, an unstructured mesh is used, generated using a combination of automatic segmentation in the software and manual adjustments.

[0014] During the mesh generation process, the mesh density in different areas is determined based on the material properties and flow field characteristics of the aircraft; the boundary layer area of ​​the geometric model, the sharp corners in the geometric model, and the areas where the flow field changes dramatically need to be meshed and manually adjusted.

[0015] Furthermore, the simulation condition configuration is performed in combination with the incoming flow conditions of the aircraft, and the steady flow field is solved to obtain the pressure distribution and heat flux distribution of the CFD grid on the surface of the geometric model, including:

[0016] After the mesh is generated, the inlet, outlet, and wall boundary conditions of the computational domain are set in combination with the incoming flow conditions of the aircraft. The steady flow field is solved, including numerical simulation of the flow field using the finite volume method based on the Reynolds average equation, to obtain the pressure distribution and heat flux distribution of the CFD mesh on the surface. The surface refers to the external surface where the fluid and structure meet, including all external surfaces of the geometric model exposed to the flow field.

[0017] Furthermore, the RBF-based local interpolation method selects a set of CFD grids of the object surface portion closest to each CSD grid of the geometric model as a support point set, and uses these support points to perform RBF interpolation.

[0018] Furthermore, the RBF-based local interpolation method includes:

[0019] Step 201 : For each CSD grid, a preset number of CFD grids are selected as the support point set of the CSD grid based on the principle of proximity within a specified distance range on the CFD grid of the object surface;

[0020] Step 202: Establish a local RBF interpolation relationship for the set of support points selected by the CSD grid. The RBF interpolation method represents the pressure and heat flow at the CSD grid as the weighted sum of its support points. The influence of each support point is determined by its distance from the CSD grid. Closer support points are assigned a larger weight, while more distant support points are assigned a smaller weight, thereby constructing the RBF interpolation relationship.

[0021] In step 203, the RBF interpolation relationship is applied to each CSD grid to obtain the pressure and heat flux distribution at each CSD grid. The pressure and heat flux distribution of the CSD grid is input as external loads into the finite element solver for heat conduction analysis. The finite element solver solves structural heat transfer and thermal stress based on these external loads, the structural characteristics of the geometric model, and the material properties of the aircraft, and uses the heat conduction equation to derive the temperature distribution on the CSD grid on the surface of the geometric model.

[0022] Furthermore, the structural statics solution is performed based on the interpolation mapping results of the pressure distribution and the heat flux distribution on the CSD grid and the boundary conditions to obtain the displacement distribution on the CSD grid of the object surface, including:

[0023] First, the pressure distribution and heat flux distribution on the CSD grid obtained by the RBF interpolation method are input into the structural finite element model as external loads, and appropriate boundary conditions are set, including fixed end constraints or displacement restrictions in specific directions. Then, the finite element method is used to solve the static response of the model under these external loads and boundary conditions, and the displacement distribution on the CSD grid of the object surface is obtained.

[0024] Furthermore, based on the displacement distribution on the CSD grid of the object surface, the RBF grid deformation method is used to perform displacement interpolation on the CFD grid of the object surface established in step 100, thereby updating the position of the CFD grid and obtaining a new CFD grid;

[0025] Next, the temperature distribution on the CFD mesh obtained in step 400 is re-input as a boundary condition into step 100 to solve the steady flow field; the flow field solution will be performed on the new CFD surface mesh; finally, the process from step 100 to step 400 is repeated until the displacement distribution and temperature distribution on the CFD surface mesh converge.

[0026] A terminal device comprises a processor, a memory and a computer program stored in the memory; the device is characterized in that when the processor executes the computer program, the static fluid-solid thermal coupling numerical analysis method of the aircraft is implemented.

[0027] A computer-readable storage medium stores a computer program; the computer program is characterized in that when executed by a processor, the numerical analysis method of static fluid-solid thermal coupling of an aircraft is implemented.

[0028] Compared with the prior art, the present invention has the following technical features:

[0029] This method significantly improves accuracy compared to traditional engineering methods and is more adaptable to complex mesh deformations than other existing CFD-based fluid-structure thermal coupling methods. This method enables relatively accurate analysis of static fluid-structure thermal coupling problems in complex aircraft configurations, providing a means for studying multi-field coupling problems in static fluid-structure thermal coupling, and ultimately, guiding the development of advanced aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 A schematic flow chart of a method according to an embodiment of the present invention;

[0031] Figure 2 A hypersonic wing model and computational grid according to an embodiment of the present invention;

[0032] Figure 3 is the surface temperature distribution calculated during the aerodynamic heating process in one embodiment of the present invention;

[0033] Figure 4 This is a deformation cloud diagram obtained by static fluid-solid thermal coupling of a wing in one embodiment of the present invention. DETAILED DESCRIPTION

[0034] like Figure 1As shown, one embodiment of the present invention provides a numerical analysis method for static fluid-structure thermal coupling of an aircraft, comprising the following steps:

[0035] Step 100: Construct a geometric model of the aircraft; generate a mesh for the geometric model of the aircraft based on the structural characteristics and material properties of the aircraft; configure simulation conditions based on the incoming flow conditions of the aircraft, and solve the steady flow field to obtain the pressure distribution and heat flux distribution of the CFD mesh on the surface of the geometric model.

[0036] Specifically, commercial simulation software (such as ANSYS ICEM or Pointwise) is used to generate a CFD mesh suitable for fluid-solid-thermal coupling analysis for the geometric model of the aircraft. In combination with the structural characteristics of the aircraft, structured meshes are preferably used for parts of the geometric model with regular shapes and simple topological structures, such as the fuselage and wings of the aircraft. The generation process is based on the characteristic lines and surfaces of the geometric model, which can more accurately capture the flow field information and has higher computational efficiency. For parts of the geometric model with complex shapes, such as local special-shaped structures and connection parts of the aircraft, unstructured meshes are used. They are generated through the automatic division function in the software combined with manual adjustment to meet the fitting requirements of complex geometric shapes.

[0037] During the mesh generation process, the mesh density in different areas is determined based on the material properties and flow field characteristics of the aircraft. For example, the mesh is appropriately encrypted in areas where high-strength and high-thermal conductivity materials are located to more accurately simulate the heat conduction process. At the same time, the built-in mesh encryption strategy in the software is adopted, and additional manual adjustments are made as needed, especially in the boundary layer area of ​​the geometric model. Due to the large velocity gradient and heat exchange in this area, the encrypted mesh can improve the calculation accuracy. In addition, sharp corners in the aircraft geometric model (such as air inlets, trailing edges, etc.) and areas where the flow field may change drastically (such as shock wave areas) also need to be meshed to ensure accurate simulation of the flow field characteristics in these areas.

[0038] After the mesh is generated, the inlet, outlet, and wall boundary conditions of the computational domain are set in combination with the incoming flow conditions of the aircraft, including parameters such as Mach number, Reynolds number, temperature, and pressure. The steady flow field is solved, including numerical simulation of the flow field using the finite volume method or other methods based on the Reynolds-averaged Navier-Stokes (RANS) equations, to obtain the pressure distribution and heat flux distribution of the CFD mesh on the surface. The surface refers to the external surface where the fluid and structure meet, including all external surfaces of the model exposed to the flow field, such as the fuselage, air inlets, and wings.

[0039] In step 200, a local interpolation method based on radial basis functions (RBFs) is used to interpolate the pressure distribution and heat flux distribution of the surface CFD grid onto the finite element (CSD) grid of the aircraft geometric model point by point. After the interpolation is completed, a heat conduction analysis is performed within the geometric model based on the interpolated surface heat flux distribution on the CSD grid and the material properties of the aircraft (such as thermal conductivity and specific heat capacity). The temperature distribution on the surface CSD grid is calculated by solving the heat conduction equation.

[0040] The CSD mesh of the geometric model can be generated on the object surface using a variety of finite element analysis (FEA) software, such as ANSYS Workbench or Abaqus.

[0041] In step 200, the RBF-based local interpolation method selects a set of CFD meshes of the object surface closest to each CSD mesh of the geometric model as a set of support points, and uses these support points to perform RBF interpolation. This method reduces the sensitivity to interpolation parameters such as the support radius. The interpolation steps are as follows:

[0042] In step 201, for each CSD grid, a preset number of CFD grids are selected from the CFD grid on the object surface within a specified distance range based on the principle of proximity as the support point set of the CSD grid. Specifically, for each CSD grid, a suitable distance range is first determined (this distance range is usually set based on the grid size or computational accuracy requirements, and the specific value can be adjusted according to the problem scale). Then, at least three (or more, depending on the specific problem requirements) CFD grids are selected within this range as support points. These CFD grids will be used for local RBF interpolation to reduce sensitivity to interpolation parameters such as support radius, ensuring the stability and accuracy of the interpolation results.

[0043] In step 202, a local RBF interpolation relationship is established for the set of support points selected for the CSD grid. Specifically, the RBF interpolation method represents the pressure and heat flow at the CSD grid as the weighted sum of its support points. The influence of each support point is determined by its distance from the CSD grid. Support points that are closer are assigned a larger weight, while support points that are farther away are assigned a smaller weight, thereby constructing the RBF interpolation relationship. In this way, the pressure distribution and heat flow distribution of the CFD grid obtained in step 100 can be mapped to the CSD grid. In order to solve the weight coefficient corresponding to each support point, the least squares method or other numerical optimization methods are usually used.

[0044] In step 203, the RBF interpolation relationship is applied to each CSD grid to obtain the pressure and heat flux distribution at each CSD grid. The pressure and heat flux distribution of the CSD grid is input as external loads into the finite element solver for heat conduction analysis. The finite element solver solves structural heat transfer and thermal stress based on these external loads, the structural characteristics of the geometric model, and the material properties of the aircraft, and uses the heat conduction equation to derive the temperature distribution on the CSD grid on the surface of the geometric model.

[0045] Step 300 : Based on the interpolation mapping results of the pressure distribution and the heat flux distribution on the CSD grid and the boundary conditions, a structural statics solution is performed to obtain the displacement distribution on the CSD grid of the object surface.

[0046] First, the pressure distribution and heat flux distribution on the CSD mesh obtained by the RBF interpolation method are input as external loads into the structural finite element model, and appropriate boundary conditions are set, such as fixed end constraints or displacement restrictions in specific directions. Then, the finite element method (FEM) is used to solve the static response of the model under these external loads and boundary conditions, and the displacement distribution on the CSD mesh of the object surface is obtained.

[0047] Step 400: interpolate the temperature distribution and displacement distribution on the CSD grid to the CFD grid of the object surface using a global interpolation method based on RBF.

[0048] Among them, the RBF-based global interpolation method is to select all CSD grids as support points for each CFD grid to construct a support point set, and establish a global RBF interpolation relationship based on the relationship between all support points for interpolation.

[0049] In step 500, based on the displacement distribution on the CSD mesh of the object surface portion obtained in step 300, the CFD mesh of the object surface portion in step 100 is deformed using an RBF-based mesh deformation method to obtain a deformed CFD mesh; steps 100 to 400 are repeatedly performed on the deformed CFD mesh until the displacement distribution and the temperature distribution on the CFD mesh of the object surface portion converge.

[0050] Specifically, based on the displacement distribution on the CSD grid of the object surface, the RBF mesh deformation method is used to perform displacement interpolation on the original object surface CFD grid established in step 100, thereby updating the position of the CFD grid and obtaining a new CFD grid. This step can reflect the change in the object surface position caused by structural deformation, thereby ensuring the coupling between fluid analysis and structural deformation.

[0051] Next, based on the temperature distribution on the CFD mesh obtained in step 400, it is re-input as a boundary condition into step 100 to solve the steady flow field; the flow field solution will be performed on the new CFD surface mesh; finally, the process from step 100 to step 400 is repeated until the displacement distribution and temperature distribution on the surface CFD mesh converge, that is, the displacement and temperature changes tend to be stable, ensuring that the results of the fluid-structure thermal coupling analysis are numerically converged and physically consistent.

[0052] Finally, through the above steps, the static deformation results of the model were obtained. Specifically, after iterative calculations, the surface displacement and temperature distribution in the fluid-solid thermal coupling analysis process have reached convergence, and the static deformation results of the model have been determined. These deformation results include the displacement distribution of the model surface under the interaction of pressure, heat flow and the structure itself, as well as the corresponding temperature field. These static deformation results provide important data support for further design optimization, structural strength assessment and fatigue analysis, and can accurately reflect the deformation of the aircraft surface under the influence of fluid mechanics and thermal effects under actual working conditions. This process ensures the accuracy and stability of fluid-solid thermal coupling, and helps to improve the reliability and safety of the model in practical applications.

[0053] The data exchange method between the physical fields in the above embodiment adopts two methods, namely, the local interpolation method based on RBF and the global interpolation method. Multivariate data interpolation based on radial basis function (RBF) is a major tool for interpolating high-dimensional spatial grid data. Its advantages are simple mathematical model, no dependence on grid topology structure, etc., which has great advantages, high flexibility and strong applicability.

[0054] Example:

[0055] Using the above high-precision static fluid-solid thermal coupling analysis method for aircraft, Figure 2 The hypersonic wing model shown is analyzed.

[0056] First, the computational grid is divided according to the flow characteristics and deformation characteristics; Figure 2 The structural finite element computational mesh used in the analysis is shown in FIG.

[0057] Next, the calculation conditions were determined. In this exemplary embodiment, the CFD calculations employed the AUSM spatial discretization format and the SST two-equation turbulence model. The boundary conditions were: an incoming flow Mach number of 6.0, an incoming flow angle of 10°, an incoming flow temperature of 221.5 K, an initial wall temperature of 293 K, a Reynolds number of 1 × 10⁷, and an incoming flow pressure of 300 kPa in the fluid-structure interaction analysis. Under these conditions, the steady flow field was solved.

[0058] After the initial flow field solution is completed, the pressure and heat flux distribution on the CFD surface is interpolated to the CSD grid based on the RBF local interpolation method. The heat conduction analysis of the structure is performed according to the heat flux on the surface and the structural material parameters to obtain the temperature distribution on the model surface. Figure 3 The heat flux distribution obtained from the initial flow field calculation is shown. This heat flux distribution and other related parameters will be interpolated onto the CSD grid for the next step of structural statics calculation.

[0059] After obtaining the pressure and temperature conditions for each grid, the structural finite element solver solves for heat transfer and thermal stresses based on boundary constraints. The structural statics are then solved to determine the structural displacement distribution. These structural displacements are then transferred to the CFD surface grid using the RBF interpolation method, which calculates the deformation of the flow field grid and updates the CFD computational grid. The structural heat transfer results are then interpolated to the CFD grid using the RBF method to update the CFD computational boundary conditions.

[0060] Finally, the CFD steady flow field calculation and the structural finite element static deformation calculation are repeated iteratively. When the structural displacement and surface temperature converge, the static fluid-structure coupling analysis results of fluid-structure thermal coupling can be obtained.

[0061] Figure 4 The static fluid-solid thermal coupling deformation cloud diagram of the wing of this embodiment is displayed, and the deformation of the fluid-solid thermal coupling analysis results is relatively large.

[0062] The above embodiment demonstrates the entire process of analyzing the static fluid-structure coupling characteristics of a typical hypersonic wing considering aerodynamic heating through the high-precision aircraft static fluid-structure thermal coupling numerical analysis method proposed by the present invention.

[0063] 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 numerical analysis method for static fluid-solid thermal coupling of an aircraft, characterized in that: include: Step 100, constructing a geometric model of the aircraft; Generate mesh for the aircraft's geometric model based on the aircraft's structural characteristics and material properties; The simulation conditions are configured based on the incoming flow conditions of the aircraft, and the steady flow field is solved to obtain the pressure distribution and heat flux distribution of the CFD grid on the surface of the geometric model; Step 200 , using a local interpolation method based on radial basis functions, the pressure distribution and heat flux distribution of the surface CFD grid are interpolated point by point onto the finite element CSD grid of the aircraft geometric model. After the interpolation is completed, the surface heat flux distribution obtained by interpolation on the CSD grid and the material properties of the aircraft are combined to perform heat conduction analysis within the geometric model. By solving the heat conduction equation, the temperature distribution on the surface CSD grid is calculated. Step 300 , performing a structural statics solution based on the interpolation mapping results of the pressure distribution and the heat flux distribution on the CSD grid and the boundary conditions to obtain the displacement distribution on the CSD grid of the object surface; Step 400, interpolating the temperature distribution and displacement distribution on the CSD grid to the CFD grid of the object surface using a global interpolation method based on RBF; In step 500, based on the displacement distribution on the CSD mesh of the object surface portion obtained in step 300, the CFD mesh of the object surface portion in step 100 is deformed using an RBF-based mesh deformation method to obtain a deformed CFD mesh; steps 100 to 400 are repeatedly performed on the deformed CFD mesh until the displacement distribution and the temperature distribution on the CFD mesh of the object surface portion converge.

2. The static fluid-solid thermal coupling numerical analysis method for aircraft according to claim 1, characterized in that: The grid generation of the geometric model of the aircraft based on the structural characteristics and material properties of the aircraft includes: Using simulation software, a CFD mesh suitable for fluid-structure thermal coupling analysis is generated for the aircraft's geometric model. Taking into account the aircraft's structural characteristics, a structured mesh is used for parts of the geometric model with regular shapes and simple topology, segmented based on the model's characteristic lines and surfaces. For parts of the geometric model with complex shapes, an unstructured mesh is used, generated using a combination of automatic segmentation in the software and manual adjustments. During the mesh generation process, the mesh density in different areas is determined based on the material properties and flow field characteristics of the aircraft; the mesh is encrypted and manually adjusted for the boundary layer area of ​​the geometric model, sharp corners in the geometric model, and areas where the flow field changes dramatically.

3. The static fluid-solid thermal coupling numerical analysis method for aircraft according to claim 1, characterized in that: The simulation conditions are configured in combination with the incoming flow conditions of the aircraft, and the steady flow field is solved to obtain the pressure distribution and heat flux distribution of the CFD grid on the surface of the geometric model, including: After the mesh is generated, the inlet, outlet, and wall boundary conditions of the computational domain are set in combination with the incoming flow conditions of the aircraft. The steady flow field is solved, including numerical simulation of the flow field using the finite volume method based on the Reynolds average equation, to obtain the pressure distribution and heat flux distribution of the CFD mesh on the surface. The surface refers to the external surface where the fluid and structure meet, including all external surfaces of the geometric model exposed to the flow field.

4. The static fluid-solid thermal coupling numerical analysis method for aircraft according to claim 1, characterized in that: The RBF-based local interpolation method selects a set of CFD grids of the object surface part closest to each CSD grid of the geometric model as a support point set, and uses these support points to perform RBF interpolation.

5. The aircraft static fluid-solid thermal coupling numerical analysis method according to claim 1, characterized in that: The RBF-based local interpolation method includes: Step 201 : For each CSD grid, a preset number of CFD grids are selected as the support point set of the CSD grid based on the principle of proximity within a specified distance range on the CFD grid of the object surface; Step 202: Establish a local RBF interpolation relationship for the set of support points selected by the CSD grid. The RBF interpolation method represents the pressure and heat flow at the CSD grid as the weighted sum of its support points. The influence of each support point is determined by its distance from the CSD grid. Closer support points are assigned a larger weight, while more distant support points are assigned a smaller weight, thereby constructing the RBF interpolation relationship. In step 203, the RBF interpolation relationship is applied to each CSD grid to obtain the pressure and heat flux distribution at each CSD grid. The pressure and heat flux distribution of the CSD grid is input as external loads into the finite element solver for heat conduction analysis. The finite element solver solves structural heat transfer and thermal stress based on these external loads, the structural characteristics of the geometric model, and the material properties of the aircraft, and uses the heat conduction equation to derive the temperature distribution on the CSD grid on the surface of the geometric model.

6. The aircraft static fluid-solid thermal coupling numerical analysis method according to claim 1, characterized in that: The method of solving the structural statics based on the interpolation mapping results of the pressure distribution and the heat flux distribution on the CSD grid and the boundary conditions to obtain the displacement distribution on the CSD grid of the object surface includes: First, the pressure distribution and heat flux distribution on the CSD grid obtained by the RBF interpolation method are input into the structural finite element model as external loads, and appropriate boundary conditions are set, including fixed end constraints or displacement restrictions in specific directions. Then, the finite element method is used to solve the static response of the model under these external loads and boundary conditions, and the displacement distribution on the CSD grid of the object surface is obtained.

7. The aircraft static fluid-solid thermal coupling numerical analysis method according to claim 1, characterized in that: Based on the displacement distribution on the CSD grid of the object surface, the displacement interpolation of the CFD grid of the object surface established in step 100 is performed using the RBF grid deformation method, thereby updating the position of the CFD grid and obtaining a new CFD grid; Next, based on the temperature distribution on the CFD grid obtained in step 400, it is re-input as a boundary condition into step 100 to solve the steady flow field; The flow field solution will be performed on the new CFD surface mesh; finally, the process from step 100 to step 400 is repeated until the displacement distribution and temperature distribution on the CFD mesh of the surface converge.

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, it implements the static fluid-solid thermal coupling numerical analysis method for an aircraft according to any one of claims 1 to 7.

9. A computer-readable storage medium storing a computer program; wherein: When the computer program is executed by a processor, the aircraft static fluid-structure thermal coupling numerical analysis method according to any one of claims 1 to 7 is implemented.

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