Aircraft static fluid-solid-thermal coupling numerical analysis method

Abstract

The invention discloses an aircraft static fluid-solid-thermal coupling numerical analysis method, which comprises the following steps of: firstly, solving pressure distribution and heat flow distribution of a geometric model object plane CFD (Computational Fluid Dynamics) grid, then interpolating the pressure distribution and the heat flow distribution to a CSD (Computational State Detector) grid by adopting an RBF (Radial Basis Function) local interpolation method, and solving temperature distribution on the object plane CSD grid; performing structural statics solution based on the boundary condition, the pressure distribution and the heat flow distribution to obtain displacement distribution on the CSD grid of the object plane part; interpolating the temperature distribution and the displacement distribution on the CSD grid to the CFD grid of the object plane part by adopting a global interpolation method based on RBF (Radial Basis Function); displacement distribution is obtained according to the interpolation, an original CFD grid of the object plane part is deformed by adopting a grid deformation method based on RBF, and a deformed CFD grid is obtained; and repeatedly solving the deformed CFD grid until the displacement distribution and the temperature distribution on the CFD grid of the object plane part are converged. According to the method, the static fluid-solid-thermal coupling problem of the complex configuration of the aircraft can be accurately analyzed.

Description

Technical Field

[0001] The 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 the technological high ground in the future aerospace field. The limitation of structural weight and the drastic aerodynamic heating effect reduce the structural stiffness, resulting in increasingly prominent static fluid-solid thermal problems, which seriously affect the performance and safety of the aircraft. At the same time, the static fluid-solid thermal problem is a complex multidisciplinary coupling problem involving aerodynamic thermodynamics, unsteady aerodynamics, structural heat transfer and structural dynamics. Therefore, the static fluid-solid thermal problem has become the focus and difficulty in current hypersonic research.

[0003] In the existing research literature on static fluid-solid-thermal coupling problems, most studies and actual engineering applications still widely use engineering methods to predict aerodynamic forces and aerodynamic heat. Among them, unsteady aerodynamic forces are mostly calculated using piston theory, aerodynamic heat is predicted using reference enthalpy or reference temperature methods, and structural dynamics or statics are mostly solved based on the modal superposition method. These analysis methods can efficiently obtain static fluid-solid-thermal coupling results in the early stages of engineering design, but they cannot accurately predict aerodynamic heat, unsteady aerodynamic forces, and aerodynamic heating processes under complex flow fields, and ignore the influence of structural geometric nonlinearity on structural static solutions when deformation is large. Therefore, the existing static fluid-solid-thermal coupling research methods have low calculation accuracy and cannot meet the requirements for calculation accuracy in the development of a new generation of 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-solid thermal coupling of an aircraft, comprising:

[0007] Step 100, constructing a geometric model of the aircraft; generating a mesh for the geometric model of the aircraft based on the structural characteristics and material properties of the aircraft; configuring simulation conditions in combination with the incoming flow conditions of the aircraft, solving the steady flow field to 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 CFD grid of the object surface are interpolated point by point onto the finite element CSD grid of the aircraft geometric model; after the interpolation is completed, the heat flux distribution of the object surface obtained by interpolation on the CSD grid and the material properties of the aircraft are combined to perform heat conduction analysis in the geometric model; by solving the heat conduction equation, the temperature distribution on the CSD grid of the object surface is calculated;

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

[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] Step 500, based on the displacement distribution on the CSD grid of the object surface part obtained in step 300, the CFD grid of the object surface part in step 100 is deformed by using the RBF-based grid deformation method to obtain a deformed CFD grid; steps 100 to 400 are repeatedly executed for the deformed CFD grid until the displacement distribution and temperature distribution on the CFD grid of the object surface part 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] Generate CFD mesh suitable for fluid-solid thermal coupling analysis for the geometric model of the aircraft through simulation software; in combination with the structural characteristics of the aircraft, structured mesh is used for parts of the geometric model with regular shapes and simple topological structures, and is divided based on the characteristic lines and surfaces of the geometric model; for parts of the geometric model with complex shapes, unstructured mesh is used, which is generated through the automatic division function in the software combined with manual adjustment;

[0014] During the mesh generation process, the mesh density in different areas is determined according to the material properties of the aircraft and the flow field characteristics; 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 encrypted and manually adjusted.

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

[0016] After the mesh is generated, the inlet, outlet and wall boundary conditions of the calculation 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 of the object; the surface refers to the external surface where the fluid and the structure meet, including all external surfaces of the geometric model exposed to the flow field.

[0017] Furthermore, the RBF-based local interpolation method is to select a group of CFD grids of the object surface part closest to each CSD grid of the geometric model as a support point set, and use 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 a support point set of the CSD grid according to the principle of proximity within a specified distance range on the CFD grid of the object surface;

[0020] Step 202, establishing a local RBF interpolation relational expression for the set of support points selected by the CSD grid; wherein 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, and support points with a closer distance will be given a larger weight, and support points with a farther distance will be given a smaller weight, thereby constructing the RBF interpolation relational expression;

[0021] Step 203, applying the RBF interpolation relationship 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 into the finite element solver as an external load for heat conduction analysis; the finite element solver will solve the structural heat transfer and thermal stress according to these external loads and the structural characteristics of the geometric model and the material properties of the aircraft, and use the heat conduction equation to obtain the temperature distribution on the CSD grid of the surface part of the geometric model.

[0022] Furthermore, the method of solving the structural statics according to the interpolation mapping results of the pressure distribution and the heat flow distribution on the CSD grid and the boundary conditions to obtain the displacement distribution on the CSD grid of the object surface includes:

[0023] Firstly, 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] Further, 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, 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 object surface grid; finally, the process from step 100 to step 400 is repeated until the displacement distribution and temperature distribution on the CFD grid of the object surface converge.

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

[0027] A computer-readable storage medium having a computer program stored therein; wherein when the computer program is executed by a processor, the aircraft static fluid-solid thermal coupling numerical analysis method is implemented.

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

[0029] Compared with traditional engineering methods, the present invention has significantly improved accuracy. Compared with other existing CFD-based fluid-solid thermal coupling methods, it has higher adaptability to complex configuration mesh deformation. This method can accurately analyze the static fluid-solid thermal coupling problem of complex aircraft configurations, provide a means for the study of static fluid-solid thermal multi-field coupling problems of aircraft, and provide guidance for the development of advanced aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 A schematic diagram of a method in one embodiment of the present invention;

[0031] Figure 2 A hypersonic wing model and a computational grid in one 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 It 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-solid 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 in combination with the incoming flow conditions of the aircraft, solve the steady flow field to obtain the pressure distribution and heat flux distribution of the CFD mesh of the surface part of the geometric model.

[0036] Specifically, a CFD mesh suitable for fluid-solid-thermal coupling analysis is generated for the geometric model of the aircraft through commercial simulation software (such as ANSYS ICEM or Pointwise); among them, combined with the structural characteristics of the aircraft, for parts of the geometric model with regular shapes and simple topological structures, such as the fuselage and wings of the aircraft, structured meshes are preferably used. The generation process is based on the division of the characteristic lines and surfaces of the geometric model, which can more accurately capture the flow field information and has higher calculation 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, which 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 density of the mesh in different areas is determined according to 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 dramatically (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 grid is generated, the inlet, outlet and wall boundary conditions of the calculation domain are set in combination with the incoming flow conditions of the aircraft, including Mach number, Reynolds number, temperature, pressure and other parameters; the steady flow field is solved, including numerical simulation of the flow field based on the Reynolds-averaged Navier-Stokes (RANS) equations using the finite volume method or other methods to obtain the pressure distribution and heat flux distribution of the CFD grid on the surface; the surface refers to the external surface where the fluid and the structure meet, including all external surfaces of the model exposed to the flow field, such as the fuselage, air inlet and wings.

[0039] Step 200, using a local interpolation method based on radial basis function (RBF), the pressure distribution and heat flux distribution of the CFD grid of the object surface are interpolated point by point and mapped to the finite element (CSD) grid of the aircraft geometric model; after the interpolation is completed, the heat flux distribution of the object surface obtained by interpolation on the CSD grid and the material properties of the aircraft (such as thermal conductivity, specific heat capacity, etc.) are combined to perform heat conduction analysis in the geometric model; by solving the heat conduction equation, the temperature distribution on the CSD grid of the object surface is calculated.

[0040] Among them, 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 is to select 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 use these support points to perform RBF interpolation; this method reduces the sensitivity to interpolation parameters such as support radius, and the interpolation steps are as follows:

[0042] Step 201, for each CSD grid, a preset number of CFD grids are selected as the support point set of the CSD grid according to the principle of proximity within a specified distance range on the CFD grid of the object surface; specifically, for each CSD grid, first determine a suitable distance range (the distance range is usually set according to the grid size or calculation accuracy requirements, and the specific value can be adjusted according to the problem scale), and then select at least 3 (or more, determined according to the specific problem requirements) CFD grids within the range as support points; these CFD grids will be used for local RBF interpolation to reduce the sensitivity to interpolation parameters such as support radius, and ensure the stability and accuracy of the interpolation results.

[0043] Step 202, establish a local RBF interpolation relationship for the set of support points selected by 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, and support points with closer distances will be given greater weights, while support points with farther distances will be given smaller weights, thereby constructing an 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] Step 203, applying the RBF interpolation relationship 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 into the finite element solver as an external load for heat conduction analysis; the finite element solver will solve the structural heat transfer and thermal stress according to these external loads and the structural characteristics of the geometric model and the material properties of the aircraft, and use the heat conduction equation to obtain the temperature distribution on the CSD grid of the surface part of the geometric model.

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

[0046] Firstly, 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, 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 grid 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] Step 500, based on the displacement distribution on the CSD grid of the object surface part obtained in step 300, the CFD grid of the object surface part in step 100 is deformed by using the RBF-based grid deformation method to obtain a deformed CFD grid; steps 100 to 400 are repeatedly executed for the deformed CFD grid until the displacement distribution and temperature distribution on the CFD grid of the object surface part converge.

[0050] Specifically, 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 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 position of the object surface caused by structural deformation, thereby ensuring the coupling between fluid analysis and structural deformation.

[0051] 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 grid; finally, the process from step 100 to step 400 is repeated until the displacement distribution and temperature distribution on the CFD grid of the surface converge, that is, the displacement and temperature changes tend to be stable, ensuring that the results of the fluid-solid 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 main tool for high-dimensional space grid data interpolation. Its mathematical model is simple and does not need to rely on the grid topology structure. It 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 Figure .

[0057] Then, the calculation conditions are determined. In this exemplary embodiment, the AUSM spatial discretization format is used in the CFD calculation, and the SST two-equation turbulence model is used. The calculation boundary conditions are: the incoming flow Mach number is 6.0, the incoming flow angle of attack is 10°, the incoming flow temperature is 221.5K, the wall initial temperature is 293K, the Reynolds number is 1×107, and the incoming flow pressure in the fluid-solid coupling analysis is 300kPa. Under these conditions, the steady flow field is 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. The heat flux distribution and other related parameters will be interpolated to the CSD grid for the next step of structural statics calculation.

[0059] After the structural finite element solver obtains the pressure and temperature conditions of each grid, it solves the structural heat transfer and thermal stress according to the boundary constraints. Then the structural statics are solved to obtain the displacement distribution of the structure. The structural displacement will be transferred to the CFD surface grid through the RBF interpolation method, and the deformation of the flow field grid will be calculated to update the CFD calculation grid. The results of structural heat transfer will be interpolated to the CFD grid through the RBF method to update the CFD calculation boundary conditions.

[0060] Finally, the CFD steady flow field calculation and the structural finite element static deformation calculation are repeated and when the structural displacement and the surface temperature converge, the static fluid-solid coupling analysis results of fluid-solid 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 amount of the fluid-solid thermal coupling analysis result is relatively large.

[0062] The above-mentioned embodiment demonstrates the whole process of analyzing the static fluid-solid coupling characteristics of a typical hypersonic wing considering aerodynamic heating through the high-precision aircraft static fluid-solid 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 embodiments of the present application, and should all be included in the protection scope 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 geometric model of the aircraft based on the structural characteristics and material properties of the aircraft; Combine the incoming flow conditions of the aircraft to configure the simulation conditions, solve the steady flow field 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 CFD grid of the object surface are interpolated point by point onto the finite element CSD grid of the aircraft geometric model; after the interpolation is completed, the heat flux distribution of the object surface obtained by interpolation on the CSD grid and the material properties of the aircraft are combined to perform heat conduction analysis in the geometric model; by solving the heat conduction equation, the temperature distribution on the CSD grid of the object surface is calculated; Step 300, solving the structural statics to obtain the displacement distribution on the CSD grid of the object surface according to the interpolation mapping results of the pressure distribution and the heat flux distribution on the CSD grid and the boundary conditions; 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; Step 500, based on the displacement distribution on the CSD grid of the object surface part obtained in step 300, the CFD grid of the object surface part in step 100 is deformed by using the RBF-based grid deformation method to obtain a deformed CFD grid; steps 100 to 400 are repeatedly executed for the deformed CFD grid until the displacement distribution and temperature distribution on the CFD grid of the object surface part 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: Generate CFD mesh suitable for fluid-solid thermal coupling analysis for the geometric model of the aircraft through simulation software; in combination with the structural characteristics of the aircraft, structured mesh is used for parts of the geometric model with regular shapes and simple topological structures, and is divided based on the characteristic lines and surfaces of the geometric model; for parts of the geometric model with complex shapes, unstructured mesh is used, which is generated through the automatic division function in the software combined with manual adjustment; During the mesh generation process, the mesh density in different areas is determined according to the material properties of the aircraft and the flow field characteristics; the mesh is encrypted and manually adjusted for the boundary layer area of ​​the geometric model, the sharp corners in the geometric model, and the parts 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 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 flow distribution of the CFD grid of the surface part of the geometric model, including: After the mesh is generated, the inlet, outlet and wall boundary conditions of the calculation 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 of the object; the surface refers to the external surface where the fluid and the 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 is to select a group of CFD grids of the object surface part closest to each CSD grid of the geometric model as a support point set, and use 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 a support point set of the CSD grid according to the principle of proximity within a specified distance range on the CFD grid of the object surface; Step 202, establishing a local RBF interpolation relational expression for the set of support points selected by the CSD grid; wherein 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, and support points with a closer distance will be given a larger weight, and support points with a farther distance will be given a smaller weight, thereby constructing the RBF interpolation relational expression; Step 203, applying the RBF interpolation relationship 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 into the finite element solver as an external load for heat conduction analysis; the finite element solver will solve the structural heat transfer and thermal stress according to these external loads and the structural characteristics of the geometric model and the material properties of the aircraft, and use the heat conduction equation to obtain the temperature distribution on the CSD grid of the surface part 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 structural statics according to the interpolation mapping results of pressure distribution and heat flow distribution on the CSD grid and boundary conditions to obtain the displacement distribution on the CSD grid of the object surface includes: Firstly, 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, so as to update the position of the CFD grid and obtain 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 object 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 object 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, wherein a computer program is stored in the medium; characterized in that: When the computer program is executed by a processor, the aircraft static fluid-solid thermal coupling numerical analysis method according to any one of claims 1 to 7 is implemented.

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