A method, device and medium for analyzing a gas-thermal structure three-field coupling

Abstract

The application provides a gas-heat structure three-field coupling analysis method, equipment and medium, wherein the method comprises: obtaining relevant parameters of a high-speed hypersonic aircraft to be analyzed, the relevant parameters at least comprising: initial geometric shape of a wing surface of the high-speed hypersonic aircraft to be analyzed, initial aerodynamic force parameters; performing analysis based on the initial geometric shape and the initial aerodynamic force parameters to obtain local airflow parameters; performing aerodynamic heat analysis based on the local airflow parameters and the obtained wall surface temperature to obtain surface heat flow of the wing surface; performing heat conduction analysis based on the surface heat flow of the wing surface to obtain new temperature distribution and temperature change of the structure of the wing surface; obtaining cycle conditions based on the temperature change; and outputting coupling results if the cycle conditions are met. In the method, a coupling analysis method is adopted, the influence of temperature change on material properties and structure is considered, and therefore more accurate results are obtained. Meanwhile, the method sets cycle conditions to control the number of iteration calculations, and therefore the calculation process is more efficient.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft, and specifically provides a gas-thermal-structure three-field coupling analysis method, device and medium. BACKGROUND

[0002] The wing surface structure of a hypersonic aircraft is simultaneously affected by the interaction of aerodynamic force, heat conduction and structural force during flight, which means that the aerodynamic force will affect the wing surface structure, heat conduction will cause the temperature of the structure to change, and the deformation of the structure will affect the aerodynamic force and heat conduction. Therefore, for the design and analysis of the wing surface structure of a hypersonic aircraft, the coupling effects of the three fields need to be considered comprehensively to ensure the reliability and performance of the aircraft. For the aerodynamic / thermal / structural three-field coupling problem of the wing surface structure of a hypersonic aircraft, the full-order analysis method is generally used at present. At present, the full-order analysis method is mainly based on the finite element method, but in the hypersonic flow, simultaneously solving the aerodynamic, structural and heat conduction problems will face the challenge of mutual correlation and coupling of boundary conditions, and there is also the problem of long analysis time and slow analysis speed. SUMMARY

[0003] In order to overcome the above-mentioned defects, the present application is proposed to provide a solution or at least partially solve the problem of long analysis time and slow analysis speed.

[0004] In a first aspect, the present application provides a gas-thermal-structure three-field coupling analysis method, comprising:

[0005] Obtaining relevant parameters of a hypersonic aircraft to be analyzed, the relevant parameters at least including: initial geometric shape of a wing surface of the hypersonic aircraft to be analyzed, initial aerodynamic force parameters;

[0006] Performing analysis based on the initial geometric shape and initial aerodynamic force parameters to obtain local airflow parameters;

[0007] Performing aerodynamic thermal analysis based on the local airflow parameters and the obtained wall temperature to obtain surface heat flow of the wing surface;

[0008] Performing heat conduction analysis based on the surface heat flow of the wing surface to obtain new temperature distribution and temperature change of the structure of the wing surface;

[0009] Obtaining a cycle condition based on the temperature change; if the cycle condition is met, outputting a coupling result, the coupling result at least including surface heat flow, new temperature distribution and temperature change of the structure of the wing surface.

[0010] In one technical solution of the above-mentioned gas-thermal-structure three-field coupling analysis method, performing analysis based on the initial geometric shape and initial aerodynamic force parameters to obtain local airflow parameters at least includes:

[0011] performing aerodynamic force analysis on the airfoil to obtain aerodynamic load and inertial load of the airfoil;

[0012] performing static force analysis based on initial geometric shape and aerodynamic force parameters of the hypersonic vehicle to be analyzed to obtain local airflow parameters.

[0013] In one of the technical solutions of the above-mentioned three-field coupling analysis method of aero-thermal structure, the aerodynamic force analysis on the airfoil to obtain the aerodynamic load and the inertial load of the airfoil comprises:

[0014] discretizing the airfoil surface of the hypersonic vehicle to be analyzed into a plurality of nodes, measuring or calculating the pressure distribution on the surface of each node based on the pressure distribution, converting the pressure distribution into force, and distributing the obtained force to the nodes to determine the size and direction of the force on each node according to the geometric structure of the airfoil, i.e. the aerodynamic load on each node is obtained.

[0015] obtaining the total mass of the hypersonic vehicle to be analyzed and the overloads of the hypersonic vehicle to be analyzed in x, y and z directions, and calculating the inertial load of the hypersonic vehicle to be analyzed based on the total mass of the hypersonic vehicle to be analyzed and the overloads of the hypersonic vehicle to be analyzed in x, y and z directions.

[0016] In one of the technical solutions of the above-mentioned three-field coupling analysis method of aero-thermal structure, the static force analysis based on the initial geometric shape and aerodynamic force parameters of the hypersonic vehicle to be analyzed to obtain the local airflow parameters comprises:

[0017] applying secondary dynamic load to the airfoil;

[0018] obtaining the initial displacement of the nodes of the airfoil under the secondary dynamic load;

[0019] recomputing the aerodynamic force of the airfoil after the displacement of the nodes by an iterative method, combining the aerodynamic force of the airfoil after the displacement of the nodes with the initial displacement of the nodes, and then re-computing the displacement of the nodes, and then using the updated displacement of the nodes to re-compute the aerodynamic force, and repeating the step until the displacement of the nodes and the aerodynamic force converge;

[0020] obtaining the local airflow parameters based on the aerodynamic force at the time of convergence.

[0021] In one of the technical solutions of the above-mentioned three-field coupling analysis method of aero-thermal structure, obtaining the initial displacement of the nodes of the airfoil under the secondary dynamic load comprises:

[0022] calculating the initial load acting on each node according to the given secondary dynamic load;

[0023] obtaining the structural stiffness matrix of the airfoil;

[0024] Based on the initial load on each node, the structure stiffness matrix obtains the initial displacement of the node.

[0025] In one of the technical solutions of the above-mentioned three-field coupling analysis method of the aero-thermal structure, the wall surface temperature is obtained based on the local airflow parameter and the aerodynamic heat analysis is performed based on the wall surface temperature to obtain the surface heat flux of the airfoil.

[0026] The temperature of each node is obtained, and the wall surface temperature is obtained based on the average value of all the node temperatures.

[0027] The local airflow parameter and the wall surface temperature are taken as inputs to perform aerodynamic heat analysis simulation.

[0028] Based on the process of aerodynamic heat analysis simulation, the heat transfer process of the airfoil surface is calculated to obtain the surface heat flux of the airfoil.

[0029] In one of the technical solutions of the above-mentioned three-field coupling analysis method of the aero-thermal structure, the structure new temperature distribution and temperature change of the airfoil are obtained based on the surface heat flux of the airfoil.

[0030] The node temperature before heat conduction is obtained.

[0031] The current temperature of the node is calculated based on the surface heat flux, and the node temperature before heat conduction is updated based on the current temperature of the node.

[0032] The current structure temperature of the airfoil is obtained based on the current temperature of the node, and the new temperature distribution and temperature change of the airfoil are obtained based on all the current structure temperatures of the airfoil.

[0033] In one of the technical solutions of the above-mentioned three-field coupling analysis method of the aero-thermal structure, the cycle condition is obtained based on the temperature change.

[0034] The thermal strain matrix of the airfoil is obtained based on the temperature change.

[0035] The thermal load is obtained based on the structure stiffness matrix and the thermal strain matrix.

[0036] The cycle condition is obtained based on the change amount of the thermal load and the maximum number of iterations, and the cycle condition is whether the change amount of the thermal load is less than a threshold value or whether the maximum number of iterations is reached.

[0037] In a second aspect, the present application provides an electronic device comprising a processor and a storage device, the storage device being adapted to store a plurality of program codes, the program codes being adapted to be loaded and run by the processor to perform any one of the technical solutions of the above-mentioned three-field coupling analysis method of the aero-thermal structure.

[0038] In a third aspect, the present application provides a computer readable storage medium, wherein a plurality of program codes are stored, the program codes being adapted to be loaded and run by a processor to execute the aerothermal structure three-field coupling analysis method according to any one of the technical solutions of the aerothermal structure three-field coupling analysis method.

[0039] The one or more technical solutions of the present application have at least one or more of the following beneficial effects:

[0040] In the implementation of the technical solutions of the present application, the present application provides an aerothermal structure three-field coupling analysis method, which comprises: obtaining relevant parameters of a hypersonic vehicle to be analyzed, the relevant parameters at least comprising: an initial geometric shape of a wing surface of the hypersonic vehicle to be analyzed, and initial aerodynamic force parameters; performing analysis based on the initial geometric shape and the initial aerodynamic force parameters to obtain local airflow parameters; performing aerodynamic heat analysis based on the local airflow parameters and the obtained wall surface temperature to obtain surface heat flux of the wing surface; performing heat conduction analysis based on the surface heat flux of the wing surface to obtain new temperature distribution and temperature change of the wing surface; obtaining a cycle condition based on the temperature change; and outputting a coupling result if the cycle condition is met. Compared with the prior art, the aerothermal structure three-field coupling analysis method provided by the present application has the beneficial effect that: in the method, a coupling analysis method is adopted, the influence of temperature change on material properties and structure is considered, and therefore more accurate results are obtained. At the same time, the method sets a cycle condition to control the number of iterations, so that the calculation process is more efficient.

[0041] Further, due to the change of the material properties of the structure caused by the temperature change, the thermal strain is obtained according to the temperature change, and only the temperature distribution and the thermal strain need to be updated in each step; since the structure stiffness matrix is not affected by the temperature, the entire structure stiffness matrix does not need to be recalculated each time, repeated calculation is avoided, and the speed of the three-field coupling analysis is greatly improved, the time required for analysis is greatly reduced, and the accuracy of the results is maintained.

[0042] Further, whether further aerodynamic elastic analysis is needed is determined according to the change of the thermal load, so that the accuracy of the results is ensured. BRIEF DESCRIPTION OF DRAWINGS

[0043] The disclosure of the present application will become more readily understood by referring to the accompanying drawings. It will be readily understood to those skilled in the art that the drawings are not limited to the present application, and are not intended to limit the scope of protection of the present application. In addition, similar numbers in the figures are used to represent similar components, wherein:

[0044] Figure 1 is a main step flow diagram of the aerothermal structure three-field coupling analysis method according to an embodiment of the present application;

[0045] Figure 2 is a flowchart of a method for analyzing based on initial geometric shape and initial aerodynamic force parameters to obtain local airflow parameters according to an embodiment of the present application;

[0046] Figure 3 is a flowchart of a method for aerodynamic heat analysis based on local airflow parameters and obtained wall surface temperature to obtain surface heat flow of a wing surface according to an embodiment of the present application;

[0047] Figure 4 is a flowchart of a method for heat conduction analysis based on surface heat flow of a wing surface to obtain new temperature distribution and temperature change of the wing surface according to an embodiment of the present application;

[0048] Figure 5 is a flowchart of a method for obtaining cycle conditions based on temperature change according to an embodiment of the present application. DETAILED DESCRIPTION

[0049] Some embodiments of the present application will be described below with reference to the accompanying drawings. It should be understood by those skilled in the art that these embodiments are only used to explain the technical principles of the present application, and are not intended to limit the protection scope of the present application.

[0050] Embodiment One

[0051] Reference is made to the accompanying drawings Figure 1 , Figure 1 is a flowchart of main steps of a method for aerothermo-structural three-field coupling analysis according to an embodiment of the present application. As shown in Figure 1 , the method for aerothermo-structural three-field coupling analysis in the embodiment of the present application mainly includes the following steps S1-S5.

[0052] The present application provides a method for aerothermo-structural three-field coupling analysis, including the following steps:

[0053] Step S1, obtaining relevant parameters of a hypersonic speed aircraft to be analyzed, the relevant parameters at least including initial geometric shape and initial aerodynamic force parameters of a wing surface of the hypersonic speed aircraft to be analyzed;

[0054] Step S2, analyzing based on the initial geometric shape and the initial aerodynamic force parameters to obtain local airflow parameters;

[0055] Step S3, performing aerodynamic heat analysis based on the local airflow parameters and obtained wall surface temperature to obtain surface heat flow of the wing surface;

[0056] Step S4, performing heat conduction analysis based on the surface heat flow of the wing surface to obtain new temperature distribution and temperature change of the wing surface;

[0057] Step S5, obtaining a cycle condition based on the temperature change; and outputting a coupling result if the cycle condition is met, the coupling result including at least a surface heat flow, a new temperature distribution of the structure of the airfoil, and a temperature change.

[0058] In this embodiment, the initial geometric shape of the airfoil of the hypersonic vehicle to be analyzed refers to the external shape and size of the airfoil of the vehicle in the initial state.

[0059] Based on the above steps S1-S5, the coupling analysis method is used in this method, and the influence of temperature change on material properties and structure is considered, so that more accurate results are obtained. At the same time, the number of iteration calculations is controlled by setting the cycle condition in this method, so that the calculation process is more efficient.

[0060] In one embodiment, as shown in Figure 2 Step S2, performing analysis based on the initial geometric shape and initial aerodynamic force parameters to obtain local airflow parameters including at least:

[0061] Step S21, performing aerodynamic force analysis on the airfoil to obtain aerodynamic loads and inertial loads of the airfoil.

[0062] Step S22, performing static force analysis based on the initial geometric shape and aerodynamic force parameters of the hypersonic vehicle to be analyzed to obtain local airflow parameters.

[0063] In this embodiment, in the vehicle, the aerodynamic loads on the airfoil are mainly composed of aerodynamic forces and inertial loads. The aerodynamic force is the force caused by the pressure of the airflow on the airfoil. Through aerodynamic force analysis, the aerodynamic loads such as lift, drag and lateral force on the airfoil can be calculated. When the vehicle is subjected to external disturbance or performs specific motion, the airfoil will generate inertial load. The inertial load is the force caused by the mass and acceleration of the airfoil. For example, during flight or maneuvering, the airfoil will be subjected to inertial force caused by the acceleration and rotation of the aircraft. Therefore, aerodynamic force analysis is performed to calculate the aerodynamic loads of the airfoil and understand the pressure and mechanical effects on the airfoil in air flow. The inertial load is obtained by considering the motion and acceleration of the vehicle through structural dynamics analysis. The analysis of these two loads is to ensure the structural strength and stability of the airfoil and the safety and performance of the vehicle.

[0064] In one embodiment, step S21, performing aerodynamic force analysis on the airfoil to obtain aerodynamic loads and inertial loads of the airfoil including:

[0065] Step S211, discretize the surface of the wing of the hypersonic vehicle to be analyzed into a plurality of nodes; measure or calculate the pressure distribution on the surface of each node; convert the pressure distribution into force; distribute the obtained force to the nodes, and determine the size and direction of the force on each node according to the geometric structure of the wing, that is, obtain the aerodynamic load on each node;

[0066] In this embodiment, the number of nodes can be selected according to actual conditions, and more nodes can improve the calculation accuracy. Then, the potential flow theory or other methods are used to solve the pressure distribution. According to the third-order piston theory, the pressure distribution can be converted into lift, drag and moment. The obtained force is distributed to each node, and the size and direction of the force on each node are determined according to the geometric structure of the wing. The obtained force can also be distributed to each node by the node position, area and other parameters, and the size and direction of the force on each node are determined according to the geometric structure of the wing. This can be determined by the node position, area and other parameters.

[0067] Step S212, obtain the total mass of the hypersonic vehicle to be analyzed and the overloads of the hypersonic vehicle to be analyzed in x, y and z directions; based on the total mass of the hypersonic vehicle to be analyzed and the overloads of the hypersonic vehicle to be analyzed in x, y and z directions, calculate the inertial load of the hypersonic vehicle to be analyzed.

[0068] In this embodiment, the total mass of the hypersonic vehicle to be analyzed and the overloads in x, y and z directions can be obtained by actual measurement or other design parameters, and then according to Newton's second law, the inertial force on each node of the vehicle can be obtained.

[0069] Alternatively, in an alternative way, the boundary element method can also be used, the wing surface is discretized into small facets, the velocity gradient and pressure distribution on the boundary are calculated, and the aerodynamic load is obtained; by establishing a mathematical model and considering the mass, stiffness and damping parameters of the structure, the force response of the structure in motion can be obtained, and the inertial load can be obtained.

[0070] Of course, the method for obtaining the aerodynamic load and the inertial load of the wing is not limited to the two methods listed above, as long as the aerodynamic load and the inertial load of the wing are obtained.

[0071] In one embodiment, step S22, based on the initial geometric shape and aerodynamic force parameters of the hypersonic vehicle to be analyzed, static force analysis is performed to obtain local airflow parameters, including:

[0072] Step S221, apply secondary dynamic load to the wing;

[0073] Specifically, first, the nature and action point of the secondary dynamic load need to be determined. Generally, the secondary dynamic load can be caused by simulating a specific motion state or applying a specific force. For example, a bending load along the span direction can be applied, or a shear load along the profile direction can be applied.

[0074] Step S222, obtaining the initial displacement of the nodes of the airfoil under the secondary dynamic load;

[0075] Specifically, by the structural analysis method, the initial displacement of the nodes of the airfoil under the secondary dynamic load can be calculated.

[0076] Step S223, re-computing the aerodynamic force of the airfoil after the displacement of the nodes occurs by an iterative method, combining the aerodynamic force of the airfoil after the displacement of the nodes occurs with the initial displacement of the nodes, re-computing the displacement of the nodes, then using the updated displacement of the nodes to re-compute the aerodynamic force, and repeating this step until the displacement of the nodes and the aerodynamic force converge;

[0077] Specifically, first, the initial displacement of the nodes is assumed to be zero, and the initial aerodynamic force of the airfoil is calculated according to the initial geometric shape and aerodynamic parameters. Then, the displacement of the airfoil under the secondary dynamic load is calculated according to the initial displacement of the nodes, and the aerodynamic force of the airfoil is re-computed using the result of the displacement calculation. It should be noted that since the displacement changes the geometric shape of the airfoil, the aerodynamic force will also change accordingly. The updated aerodynamic force and the initial displacement are combined to re-compute the displacement of the nodes. The updated displacement of the nodes is compared with the displacement of the last time, and if the difference between the two is less than a preset convergence criterion (such as a set convergence threshold), it is determined that the convergence is reached, otherwise the next iteration is performed in step S223.

[0078] Step S224, obtaining the local flow parameters based on the aerodynamic force at the time of convergence.

[0079] Specifically, when the calculation of the displacement of the nodes and the aerodynamic force reaches convergence, the local flow parameters can be inferred from the results of the aerodynamic force at the time of convergence. The local flow parameters can include Mach number, pressure, temperature, etc.

[0080] Alternatively, in an alternative way, the process of obtaining the local flow parameters based on the initial geometric shape and aerodynamic parameters of the hypersonic vehicle to be analyzed can also be: using the aerodynamic force model to calculate the aerodynamic parameters of the vehicle in the local flow, including the aerodynamic force coefficients, lift, drag, etc., according to the geometric shape of the vehicle and the flight conditions;

[0081] Then, the structural stiffness matrix of the vehicle is calculated using the structural mechanics theory according to the given structural materials and geometric parameters of the vehicle;

[0082] The aerodynamic force parameters and the structural stiffness matrix are input into the static force analysis model to perform static force balance calculation. In the static force balance calculation, the initial load of the aircraft is applied to each node, and the displacement of the node is calculated based on the structural stiffness matrix;

[0083] According to the static force balance condition, the internal force matrix can be obtained by multiplying the structural stiffness matrix by the node displacement. The aerodynamic force model is used to convert the geometric shape and aerodynamic force parameters into an aerodynamic force matrix. The aerodynamic force matrix describes the aerodynamic force acting on the nodes of the aircraft. In the static force balance state, the internal force and the aerodynamic force should cancel each other out. Therefore, the internal force matrix and the aerodynamic force matrix can be equal to obtain an equation group, and the unknown local airflow parameters can be obtained by solving the equation group.

[0084] Of course, the method of performing static force analysis based on the initial geometric shape and aerodynamic force parameters of the hypersonic aircraft to be analyzed to obtain the local airflow parameters is not limited to the two methods listed above. No matter what the situation is, as long as the local airflow parameters are obtained.

[0085] In one embodiment, step S222, obtaining the initial displacement of the nodes of the airfoil under the secondary dynamic load includes:

[0086] According to the given secondary dynamic load, the initial load acting on each node is calculated;

[0087] Obtaining the structural stiffness matrix of the airfoil;

[0088] Based on the initial load on each node and the structural stiffness matrix, the initial displacement of the node is obtained.

[0089] Specifically, the initial load acting on each node is combined into a load vector, and the structural stiffness matrix is combined into a stiffness matrix. The load vector and the stiffness matrix are multiplied to obtain an equation, and the initial displacement of the node can be obtained by solving the equation group.

[0090] In one embodiment, as shown in Figure 3 Step S3, based on the local airflow parameters and the obtained wall temperature, performing aerodynamic heat analysis to obtain the surface heat flux of the airfoil includes:

[0091] Step S31, obtaining the temperature of each node, and obtaining the wall temperature based on the average of all the node temperatures;

[0092] In this embodiment, based on the principle of heat conduction, the temperature of each node can be obtained by calculating the heat balance equation for each node. This requires considering factors such as heat conduction, radiative heat transfer, and convective heat transfer between nodes. By solving the heat balance equations, the temperature of each node can be obtained. The average temperature of all nodes is then taken as the wall temperature. This is to obtain the average temperature of the entire surface on the airfoil for subsequent aerodynamic thermal analysis.

[0093] Step S32: Perform aerodynamic thermal analysis simulation using the local airflow parameters and the wall temperature as inputs;

[0094] In this embodiment, the obtained local airflow parameters and wall temperature are used as inputs to perform aerodynamic thermal analysis simulation. During the simulation, the influence of the boundary layer and turbulence on heat transfer is considered, and the heat transfer process of the airfoil under given conditions can be obtained.

[0095] Step S33: Calculate the heat transfer process on the airfoil surface based on the aerodynamic thermal analysis simulation process to obtain the surface heat flow of the airfoil.

[0096] In this embodiment, the heat transfer process on the airfoil surface is calculated based on the results of aerodynamic thermal analysis simulation. The effects of thermal convection, thermal radiation, and thermal radiation can be considered. By calculating the heat transfer equation and energy balance equation, the heat flow on the airfoil surface can be obtained.

[0097] Alternatively, in an alternative approach, the friction coefficients at different locations on the wing surface in the incompressible flow are obtained using the Eckert reference method and the Reynolds analogy. Then, the heat flux of the wing surface is calculated using the flat plate heat flux formula, and the surface heat flux is calculated using the radiative heat dissipation formula. The difference between the heat flux and radiative heat dissipation of the wing surface is the actual surface heat flux.

[0098] The process of obtaining the friction coefficient includes: using fluid dynamics theory and computational fluid dynamics (CFD) methods to perform numerical simulation or experimental measurement on the airfoil to obtain flow field variables at different locations; calculating the corresponding Reynolds number based on the obtained flow field variables; applying the Reynolds analogy method to obtain the friction coefficient for different Reynolds number ranges; and then using the Eckert reference method to correct the friction coefficient obtained by the Reynolds analogy method.

[0099] In one embodiment, such as Figure 4 As shown, step S4, performing heat conduction analysis based on the surface heat flow of the wing surface to obtain the new temperature distribution and temperature changes of the wing surface structure, includes:

[0100] Step S41: Obtain the node temperature before heat conduction;

[0101] In this embodiment, the temperature of each node before heat conduction analysis needs to be obtained.

[0102] Step S42, calculating the current temperature of the node based on the surface heat flux, updating the node temperature before heat conduction based on the current temperature of the node;

[0103] In this embodiment, the current temperature of the node is calculated based on the surface heat flux and the heat conduction equation. For example, the finite difference method or the finite element method is used for discretization and solution to obtain the current temperature of each node. The obtained current temperature of the node is updated with the previous node temperature before heat conduction. This update is to simulate the temperature change during heat conduction, and the temperature of each node after heat conduction can be obtained through iterative calculation. The update process can be performed using an iterative method (such as iterative calculation, Newton iteration, etc.) until the convergence condition is met.

[0104] Step S43, obtaining the current structural temperature of the airfoil based on the current temperature of the node, and obtaining the new temperature distribution and temperature change of the airfoil based on the current structural temperature of all the airfoils.

[0105] In this embodiment, the structural temperature on each airfoil is calculated based on the node temperature distribution. The temperature within a unit or a set of units can be obtained using weighted average, linear interpolation, etc. Then, based on the obtained airfoil structural temperature, the temperature distribution of the airfoil can be analyzed to intuitively obtain the new temperature distribution of the airfoil.

[0106] In one embodiment, as shown in Figure 5 Step S5, obtaining the cycle condition based on the temperature change includes:

[0107] Step S51, obtaining the thermal strain matrix of the airfoil based on the temperature change;

[0108] In this embodiment, the thermal strain of the airfoil at different positions is calculated based on the temperature change. The thermal strain can be calculated by the thermal expansion coefficient and the geometric shape of the airfoil. The thermal strain at different positions can be represented in the form of a matrix.

[0109] Step S52, obtaining the thermal load based on the structural stiffness matrix and the thermal strain matrix;

[0110] In this embodiment, the thermal load is obtained based on the product of the structural stiffness matrix and the thermal strain matrix.

[0111] Step S53, obtaining the cycle condition based on the change amount of the thermal load and the maximum number of iterations, the cycle condition being whether the change amount of the thermal load is less than a threshold value or whether the maximum number of iterations is reached.

[0112] In the embodiment, the thermal load difference between the current iteration step and the last iteration step is the thermal load change, a threshold is set to determine whether the thermal load change is less than the threshold. If the thermal load change is less than the threshold, it is considered to be converged, and the iteration is ended; otherwise, the next iteration is continued. The maximum number of iterations is set, and if the number of iterations reaches the maximum number, the iteration is stopped even if the thermal load change is still greater than the threshold.

[0113] Further, if the set number of cycles is not reached, the deformation under the temperature field is calculated again, the deformation of the node causes the change of the aerodynamic surface shape, and therefore the aerodynamic force continues to change, and the cycle is re-entered. That is, in each cycle, after the thermal deformation is calculated and the shape of the airfoil is updated, the change of the airfoil shape will cause the change of the aerodynamic force. Therefore, the aerodynamic force needs to be recalculated and used as a new input for the thermal deformation calculation in the next cycle. This process is repeated until the defined cycle ending condition is met.

[0114] Embodiment two

[0115] The application also provides an electronic device. In an embodiment of the device according to the application, the device comprises a processor and a storage device, the storage device can be configured to store a program for performing the gas-thermal structure three-field coupling analysis method of the above-mentioned method embodiments, and the processor can be configured to execute the program in the storage device, which includes but is not limited to the program for performing the gas-thermal structure three-field coupling analysis method of the above-mentioned method embodiments. For the convenience of description, only the parts related to the embodiments of the application are shown, and the specific technical details not disclosed are referred to the method part of the embodiments of the application. The control device can be a control device formed by various electronic devices.

[0116] Embodiment three

[0117] The application also provides a computer readable storage medium. In an embodiment of the computer readable storage medium according to the application, the computer readable storage medium can be configured to store a program for performing the gas-thermal structure three-field coupling analysis method of the above-mentioned method embodiments, which can be loaded and run by a processor to realize the above-mentioned gas-thermal structure three-field coupling analysis method. For the convenience of description, only the parts related to the embodiments of the application are shown, and the specific technical details not disclosed are referred to the method part of the embodiments of the application. The computer readable storage medium can be a storage device formed by various electronic devices, and optionally, the computer readable storage medium in the embodiments of the application is a non-transitory computer readable storage medium.

[0118] The technical scheme of the present application has been described in combination with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the protection scope of the present application is obviously not limited to these specific embodiments. Those skilled in the art can make equivalent changes or replacements to the original technical features without departing from the principles of the present application, and the technical schemes after these changes or replacements will all fall within the protection scope of the present application.

Claims

1. A method for analyzing a gas-thermal structure three-field coupling, characterized in that, The method comprises the following steps: acquiring relevant parameters of a hypersonic vehicle to be analyzed, wherein the relevant parameters at least include initial geometric shape of a wing surface of the hypersonic vehicle to be analyzed and initial aerodynamic force parameters; analyzing the initial geometric shape and the initial aerodynamic force parameters to obtain local airflow parameters; performing aerodynamic heat analysis based on the local airflow parameters and the acquired wall surface temperature to obtain surface heat flow of the wing surface; performing heat conduction analysis based on the surface heat flow of the wing surface to obtain new temperature distribution and temperature change of the structure of the wing surface; acquiring cycle conditions based on the temperature change, specifically comprising: calculating thermal strain of the wing surface at different positions according to the temperature change, combining the thermal expansion coefficient with the geometric shape of the wing surface, and constructing a thermal strain matrix; acquiring thermal load by multiplying the structural stiffness matrix and the thermal strain matrix; acquiring cycle conditions based on the change amount of the thermal load and the maximum number of iterations, wherein the cycle conditions are whether the change amount of the thermal load is less than a threshold value or whether the maximum number of iterations is reached; if the cycle conditions are met, outputting coupling results, wherein the coupling results at least include surface heat flow, new temperature distribution and temperature change of the structure of the wing surface.

2. The method of claim 1, wherein, The analyzing the initial geometric shape and the initial aerodynamic force parameters to obtain local airflow parameters at least includes: performing aerodynamic force analysis on the wing surface to obtain aerodynamic load and inertial load of the wing surface; performing static force analysis based on the initial geometric shape and the aerodynamic force parameters of the hypersonic vehicle to be analyzed to obtain local airflow parameters.

3. The method of claim 2, wherein, The performing aerodynamic force analysis on the wing surface to obtain aerodynamic load and inertial load of the wing surface includes: discretizing the surface of the wing surface of the hypersonic vehicle to be analyzed into multiple nodes; measuring or calculating pressure distribution on the surface of each node; converting the pressure distribution into force; and distributing the obtained force to the nodes to determine the size and direction of the force on each node according to the geometric structure of the wing surface, thereby obtaining the aerodynamic load on each node; acquiring total mass of the hypersonic vehicle to be analyzed and overloads of the hypersonic vehicle to be analyzed in x, y and z directions; and calculating inertial load of the hypersonic vehicle to be analyzed based on the total mass of the hypersonic vehicle to be analyzed and the overloads of the hypersonic vehicle to be analyzed in x, y and z directions.

4. The method of claim 2, wherein, The performing static force analysis based on the initial geometric shape and the aerodynamic force parameters of the hypersonic vehicle to be analyzed to obtain local airflow parameters includes: applying secondary dynamic load to the wing surface; acquiring initial displacement of the nodes of the wing surface under the secondary dynamic load; recomputing aerodynamic force of the wing surface after the nodes are displaced by an iterative method; combining the aerodynamic force of the wing surface after the nodes are displaced with the initial displacement of the nodes; re-computing displacement of the nodes; using the updated displacement of the nodes to re-compute the aerodynamic force; and repeating the above steps until the displacement of the nodes and the aerodynamic force converge; acquiring the local airflow parameters based on the aerodynamic force at the time of convergence.

5. The method of claim 4, wherein, The acquiring initial displacement of the nodes of the wing surface under the secondary dynamic load includes: calculating initial load acting on each node according to the given secondary dynamic load; obtaining a structural stiffness matrix of the airfoil; obtaining a node initial displacement based on the initial load on each node and the structural stiffness matrix.

6. The method of claim 2, wherein, performing aerodynamic heating analysis based on the local airflow parameters and the obtained wall temperature to obtain a surface heat flux of the airfoil, including: obtaining a temperature of each node and obtaining the wall temperature based on an average of all the node temperatures; performing aerodynamic heating analysis simulation with the local airflow parameters and the wall temperature as inputs; calculating a heat transfer process of the airfoil surface based on the aerodynamic heating analysis simulation to obtain the surface heat flux of the airfoil.

7. The method of claim 3, wherein, performing heat conduction analysis based on the surface heat flux of the airfoil to obtain a new temperature distribution and temperature change of the airfoil, including: obtaining a node temperature before heat conduction; calculating a current temperature of a node based on the surface heat flux and updating the node temperature before heat conduction based on the current temperature of the node; obtaining a current structural temperature of the airfoil based on the current temperature of the node and obtaining a new temperature distribution and temperature change of the airfoil based on all the current structural temperatures of the airfoil.

8. An electronic device comprising a processor and a storage device, said storage device being adapted to store a plurality of program codes, characterized in that, The program code is adapted to be loaded and run by the processor to perform the method of aerothermo-structural three-field coupling analysis according to any one of claims 1 to 7.

9. A computer readable storage medium having stored therein a plurality of program codes, characterized in that, The program code is adapted to be loaded and run by the processor to perform the method of aerothermo-structural three-field coupling analysis according to any one of claims 1 to 7.

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