Radiation heat flux prediction method, device, equipment and medium based on convergent flow field

Abstract

The present application discloses a radiation heat flux prediction method, device, equipment and medium based on a convergent flow field, which relates to the technical field of aerodynamics. On the basis of the initial convergent flow field result, the initial radiation source term is calculated using the Step model spectral model and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the first radiation source term and the first convergent flow field result under the optical thin approximation; on the basis of the first convergent flow field result, the first radiation source term is calculated using the Step model spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the second radiation source term and the second convergent flow field result; on the basis of the second convergent flow field result, the second radiation source term is calculated using the Line‑by‑Line spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to reduce the amount of numerical simulation calculations of aerodynamic radiation coupling and improve the efficiency of the coupling calculation process.

Description

Technical Field

[0001] The present invention relates to the technical field of aerodynamics, and in particular to a method, device, equipment and medium for predicting radiation heat flow based on a convergent flow field. Background Art

[0002] When the lunar return capsule, planetary entry vehicle, target high-speed aircraft, etc. pass through the atmosphere, due to their high flight speed, the aircraft will interact strongly with the atmosphere and generate shock waves. The strong shock wave compression makes the flow field heat up rapidly. Taking the earth's atmosphere as an example, the flow field temperature in the shock wave layer can exceed 10000K. At such a high temperature, the gas components in the aircraft flow field will undergo thermochemical reactions such as vibration and bound electron excitation, dissociation and ionization, and surface reactions such as catalysis and ablation will occur on the surface of the aircraft. At the same time, high-speed flight will cause the flow characteristic time scale to become smaller, resulting in non-equilibrium effects caused by the difference in the characteristic time scales of flow and different thermochemical effects. The above is also called the high-temperature gas thermochemical non-equilibrium effect of the target high-speed aircraft. At this time, the components (molecules, atoms, ions and electrons) in the high-temperature flow field are excited to different degrees and undergo radiation transitions, which will produce a strong light radiation effect. In this extreme environment, in addition to the convective heat flow and component diffusion heat flow of the high-temperature atmosphere, the aircraft surface must also consider the continuous radiation heating formed by the components of the high-temperature gas flow field. When the flight speed is high and the head size is large, radiation heating will dominate the total heat flux. Conventional numerical simulations of thermochemical nonequilibrium flows are relatively complex. After superimposing radiation transmission, the direct and tight coupling between radiation and high-temperature thermochemical reaction processes makes the calculations more difficult and costly. The outward radiation of energy from high-temperature gases will lead to radiation "cooling", inhibit the progress of thermochemical reactions, and affect the flow field temperature and composition. In the coupled simulation of high-temperature thermochemical nonequilibrium flows and radiation effects, if high-precision spectroscopy and high-precision radiation transmission solution methods are used, the amount of calculations will increase significantly and the calculation efficiency will decrease.

[0003] It can be seen from the above that how to reduce the amount of calculation in the numerical simulation of aerodynamic radiation coupling and improve the calculation efficiency in the coupling calculation process is a problem to be solved in this field. Summary of the invention

[0004] In view of this, the purpose of the present invention is to provide a method, device, equipment and medium for predicting radiation heat flow based on convergent flow field, which can reduce the amount of calculation in the numerical simulation of aerodynamic radiation coupling and improve the calculation efficiency in the coupling calculation process. The specific scheme is as follows:

[0005] In a first aspect, the present application discloses a method for predicting radiation heat flow based on a convergent flow field, comprising:

[0006] Constructing a flow field solution calculation grid for a target high-speed aircraft, and setting a target high-temperature gas physical and chemical model and incoming flow parameters corresponding to the target high-speed aircraft;

[0007] Generate a target high-temperature thermochemical non-equilibrium flow field solution equation based on the flow field solution calculation grid, the target high-temperature gas physical and chemical model, and the incoming flow parameters, set an initial radiation source term, and calculate an initial convergent flow field result;

[0008] Based on the initial convergent flow field result, the aerodynamic radiation coupling calculation of the initial radiation source term is performed using the Step model spectral model and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the first radiation source term and the first convergent flow field result under the optical thin approximation;

[0009] Based on the first convergent flow field result, the first radiation source term is subjected to aerodynamic radiation coupling calculation using the Step model spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain a second radiation source term and a second convergent flow field result;

[0010] Based on the result of the second convergent flow field, the second radiation source term is subjected to aerodynamic-radiation coupling calculation using the Line-by-Line spectral model, the radiation transfer solution method, and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the target convergent flow field;

[0011] The target convergent flow field is used to predict the radiation heat flux of the target high-speed aircraft.

[0012] Optionally, the generating a target high-temperature thermochemical non-equilibrium flow field solution equation based on the flow field solution calculation grid, the target high-temperature gas physical and chemical model and the incoming flow parameters, setting an initial radiation source term and calculating an initial convergent flow field result includes:

[0013] Using a preset high-temperature gas thermochemical non-equilibrium flow field numerical simulation method, and based on the flow field solution calculation grid, the target high-temperature gas physical and chemical model, and the incoming flow parameters, a target high-temperature thermochemical non-equilibrium flow field solution equation is generated;

[0014] An initial radiation source term is set, and the initial radiation source term is iteratively calculated until the flow field converges to obtain an initial converged flow field result.

[0015] Optionally, based on the initial convergent flow field result, the initial radiation source term is subjected to aerodynamic radiation coupling calculation using a Step model spectral model and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain a first radiation source term and a first convergent flow field result under optical thin approximation, including:

[0016] Based on the initial convergent flow field results, the absorption coefficient of the target high temperature gas spectrum is calculated using the Step model spectrum model;

[0017] The absorption coefficient of the target high-temperature gas spectrum and the initial radiation source term are input into the theoretical formula of the radiation source term under the optically thin approximation to obtain the radiation source term under the optically thin approximation, and the radiation source term under the optically thin approximation is input into the target high-temperature thermochemical non-equilibrium flow field solution equation for calculation to obtain the first radiation source term under the optically thin approximation and the first convergent flow field result.

[0018] Optionally, the theoretical formula of the radiation source term under the optical thin approximation is:

[0019] ;

[0020] in, is the radiation source term, is the circumference constant, is the position vector, , is the spectral frequency, is the high temperature gas spectral absorption coefficient, is the blackbody spectral radiation intensity.

[0021] Optionally, the step of inputting the radiation source term under the optically thin approximation into the target high-temperature thermochemical non-equilibrium flow field solution equation for calculation to obtain a first radiation source term under the optically thin approximation and a first convergent flow field result includes:

[0022] Inputting the radiation source term under the optical thin approximation into the target high-temperature thermochemical non-equilibrium flow field solution equation for calculation, obtaining the current radiation source term, and recording the current iteration step length;

[0023] Determine whether the current iteration step is within the preset first iteration step interval. If the current iteration step is within the preset first iteration step interval, perform iterative calculation until the current iteration step is no longer within the preset first iteration step interval, then jump to the process of calculating the absorption coefficient of the target high-temperature gas spectrum to obtain the first radiation source term and the first convergent flow field result under the optical thin approximation.

[0024] Optionally, based on the first convergent flow field result, the first radiation source term is subjected to aerodynamic radiation coupling calculation using the Step model spectral model, the radiation transfer solution method, and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain a second radiation source term and a second convergent flow field result, including:

[0025] Based on the first convergent flow field result, the first radiation source term is subjected to aerodynamic radiation coupling calculation using the Step model spectral model, the radiation transfer solution method, the target high-temperature thermochemical non-equilibrium flow field solution equation, and the radiation source term theoretical formula based on the discrete coordinate method to obtain the current radiation source term and record the current iteration step length; the radiation transfer solution method includes the discrete coordinate method;

[0026] Determine whether the current iteration step is within the preset second iteration step interval. If the current iteration step is within the preset second iteration step interval, perform iterative calculation until the current iteration step is not within the preset second iteration step interval, then jump to the process of performing aerodynamic radiation coupling calculation on the first radiation source term to obtain a second radiation source term and a second convergent flow field result;

[0027] Accordingly, based on the result of the second convergent flow field, the second radiation source term is subjected to aerodynamic radiation coupling calculation using the Line-by-Line spectral model, the radiation transfer solution method, and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the target convergent flow field, including:

[0028] Based on the second convergent flow field result, the second radiation source term is calculated by aerodynamic radiation coupling using the Line-by-Line spectral model, the radiation transfer solution method, and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the current radiation source term and record the current iteration step size;

[0029] Determine whether the current iteration step is within the preset third iteration step interval. If the current iteration step is within the preset third iteration step interval, perform iterative calculation until the current iteration step is no longer within the preset third iteration step interval, then jump to the process of performing aerodynamic-radiation coupling calculation on the second radiation source item to obtain the target convergent flow field.

[0030] Optionally, the theoretical formula of the radiation source term based on the discrete coordinate method is:

[0031] ;

[0032] in, is the radiation source term, is the circumference constant, is the position vector, , is the spectral frequency, is the high temperature gas spectral absorption coefficient, is the blackbody spectral radiation intensity, I is the local spectral radiation intensity, is the radiation propagation direction vector, is the spatial solid angle.

[0033] In a second aspect, the present application discloses a radiation heat flow prediction device based on a convergent flow field, comprising:

[0034] A grid construction and parameter setting module is used to construct a flow field solution calculation grid for a target high-speed aircraft, and to set a target high-temperature gas physical and chemical model and incoming flow parameters corresponding to the target high-speed aircraft;

[0035] A solution equation generation module, used to generate a target high-temperature thermochemical non-equilibrium flow field solution equation based on the flow field solution calculation grid, the target high-temperature gas physical and chemical model and the incoming flow parameters, set an initial radiation source term and calculate an initial convergent flow field result;

[0036] A first radiation source term calculation module is used to perform aerodynamic radiation coupling calculation on the initial radiation source term based on the initial convergent flow field result by using the Stepmodel spectral model and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the first radiation source term and the first convergent flow field result under the optical thin approximation;

[0037] A second radiation source term calculation module is used to perform aerodynamic radiation coupling calculation on the first radiation source term based on the first convergent flow field result by using the Stepmodel spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain a second radiation source term and a second convergent flow field result;

[0038] a target convergent flow field calculation module, for performing aerodynamic radiation coupling calculation on the second radiation source term based on the result of the second convergent flow field by using the Line-by-Line spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the target convergent flow field;

[0039] The radiation heat flux prediction module is used to predict the radiation heat flux of the target high-speed aircraft using the target convergent flow field.

[0040] In a third aspect, the present application discloses an electronic device, comprising:

[0041] Memory, used to store computer programs;

[0042] The processor is used to execute the computer program to implement the aforementioned radiation heat flow prediction method based on convergent flow field.

[0043] In a fourth aspect, the present application discloses a computer storage medium for storing a computer program; wherein, when the computer program is executed by a processor, the steps of the aforementioned disclosed method for predicting radiation heat flow based on a convergent flow field are implemented.

[0044] It can be seen that the present application provides a method for predicting radiation heat flux based on a convergent flow field, including constructing a flow field solution calculation grid for a target high-speed aircraft, and setting a target high-temperature gas physicochemical model and incoming flow parameters corresponding to the target high-speed aircraft; generating a target high-temperature thermochemical non-equilibrium flow field solution equation based on the flow field solution calculation grid, the target high-temperature gas physicochemical model and the incoming flow parameters, setting an initial radiation source term and calculating an initial convergent flow field result; on the basis of the initial convergent flow field result, using the Step model spectral model and the target high-temperature thermochemical non-equilibrium flow field solution equation to perform aerodynamic radiation coupling calculation on the initial radiation source term, and obtaining a first radiation source term and a first convergent flow field result under optical thin approximation; on the basis of the first convergent flow field result, using the Step model spectral model and the target high-temperature thermochemical non-equilibrium flow field solution equation. The first radiation source term is subjected to aerodynamic-radiation coupling calculation using the model spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the second radiation source term and the second convergent flow field result; based on the second convergent flow field result, the second radiation source term is subjected to aerodynamic-radiation coupling calculation using the Line-by-Line spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the target convergent flow field; the radiation heat flux of the target high-speed aircraft is predicted using the target convergent flow field. The present application first constructs a flow field solution calculation grid for the target high-speed aircraft, and sets the target high-temperature gas physicochemical model and incoming flow parameters corresponding to the target high-speed aircraft, and then improves the computational efficiency of the aerodynamic radiation coupling numerical simulation, including a four-stage acceleration process: initial high-temperature flow field calculation without radiation, aerodynamic radiation coupling calculation based on the Step model spectral model and optical thin approximation, aerodynamic radiation coupling calculation based on the Step model spectral model and radiation transfer solution method, and aerodynamic radiation coupling calculation based on the Line-by-Line spectral model and radiation transfer solution method to obtain the target convergent flow field, and use the target convergent flow field to predict the radiation heat flux of the target high-speed aircraft. In the aerodynamic radiation coupling calculation, it is not necessary to update the radiation source term information at each step, thereby greatly reducing the amount of calculation and improving the computational efficiency in the coupling calculation process. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0046] Figure 1 A flow chart of a radiation heat flow prediction method based on a convergent flow field disclosed in the present application;

[0047] Figure 2 A flowchart of accelerated calculation for coupled simulation of thermochemical nonequilibrium flow and radiation effect disclosed in this application;

[0048] Figure 3 This is a schematic diagram of the structure of a radiation heat flow prediction device based on a convergent flow field disclosed in this application;

[0049] Figure 4 A structural diagram of an electronic device provided for this application. DETAILED DESCRIPTION

[0050] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0051] When the lunar return capsule, planetary entry vehicle, target high-speed aircraft, etc. pass through the atmosphere, due to their high flight speed, the aircraft will interact strongly with the atmosphere and generate shock waves. The strong shock wave compression makes the flow field heat up rapidly. Taking the earth's atmosphere as an example, the flow field temperature in the shock wave layer can exceed 10000K. At such a high temperature, the gas components in the aircraft flow field will undergo thermochemical reactions such as vibration and bound electron excitation, dissociation and ionization, and surface reactions such as catalysis and ablation will occur on the surface of the aircraft. At the same time, high-speed flight will cause the flow characteristic time scale to become smaller, resulting in non-equilibrium effects caused by the difference in the characteristic time scales of flow and different thermochemical effects. The above is also called the high-temperature gas thermochemical non-equilibrium effect of the target high-speed aircraft. At this time, the components (molecules, atoms, ions and electrons) in the high-temperature flow field are excited to different degrees and undergo radiation transitions, which will produce a strong light radiation effect. In this extreme environment, in addition to the convective heat flow and component diffusion heat flow of the high-temperature atmosphere, the aircraft surface must also consider the continuous radiation heating formed by the components of the high-temperature gas flow field. When the flight speed is high and the head size is large, radiation heating will dominate the total heat flux. Conventional numerical simulations of thermochemical nonequilibrium flows are relatively complex. After superimposing radiation transmission, the direct and tight coupling between radiation and high-temperature thermochemical reaction processes makes the calculations more difficult and costly. The outward radiation of energy from high-temperature gases will lead to radiation "cooling", inhibit the progress of thermochemical reactions, and affect the flow field temperature and composition. In the coupled simulation of high-temperature thermochemical nonequilibrium flows and radiation effects, if high-precision spectra and high-precision radiation transmission solution methods are used, the amount of calculation will increase significantly and the computational efficiency will decrease. As can be seen from the above, how to reduce the amount of calculation in the numerical simulation of aerodynamic radiation coupling and improve the computational efficiency in the coupled calculation process is a problem to be solved in this field.

[0052] In view of the problem of a substantial increase in the amount of calculation in the numerical simulation of aerodynamic radiation coupling, the present invention proposes an accelerated calculation method for the coupled simulation of thermochemical non-equilibrium flow and radiation effect, which can greatly improve the calculation efficiency in the coupled calculation process. The CFD (Computational Fluid Dynamics) flow field solution includes finite difference and finite volume methods, and there are also multiple methods for radiation transport solution. The present invention takes the CFD finite difference method and the radiation transport DOM (Discrete Ordinates Method) as examples to provide a step-by-step coupling acceleration strategy and calculation framework, but is not limited to the coupling process of these two methods. The radiation spectrum model adopts the Step model spectrum model and the Line-by-Line spectrum model. Since the characteristic optical thickness of the high-temperature flow field of a high-speed aircraft is generally small, a relatively simple optical thin approximation method can be used to solve the preliminary aerodynamic radiation coupling flow field, and the optical thin approximation method adds very little calculation. After obtaining the convergent flow field in the intermediate process, advanced methods with high accuracy but large amount of calculation are gradually adopted.

[0053] See also Figure 1 As shown, the embodiment of the present invention discloses a radiation heat flow prediction method based on a convergent flow field, which may specifically include:

[0054] Step S11: constructing a flow field solution calculation grid for the target high-speed aircraft, and setting a target high-temperature gas physical and chemical model and incoming flow parameters corresponding to the target high-speed aircraft.

[0055] In this embodiment, for any target high-speed aircraft, a flow field solution calculation grid is constructed, and the target high-temperature gas physical and chemical model, incoming flow parameters, etc. are input to complete the calculation preparation.

[0056] Step S12: Generate a target high-temperature thermochemical non-equilibrium flow field solution equation based on the flow field solution calculation grid, the target high-temperature gas physical and chemical model and the incoming flow parameters, set an initial radiation source term and calculate an initial convergent flow field result.

[0057] In this embodiment, a preset high-temperature gas thermochemical non-equilibrium flow field numerical simulation method is used, and the target high-temperature thermochemical non-equilibrium flow field solution equation is generated based on the flow field solution calculation grid, the target high-temperature gas physical and chemical model, and the incoming flow parameters; the initial radiation source term is set, and the initial radiation source term is iteratively calculated until the flow field converges to obtain an initial converged flow field result.

[0058] Specifically, when performing the initial field calculation, the radiation effect is temporarily not considered, that is, the initial radiation source term is set, and , iterative calculation until the flow field converges, and obtain the initial field of high-temperature non-equilibrium flow without radiation coupling (that is, the initial converged flow field result). Take the CFD finite difference method as an example, and introduce MPI (Message Passing Interface) parallelism to speed up the calculation efficiency.

[0059] The target high-temperature thermochemical non-equilibrium flow field solution equations include different forms such as one temperature, two temperatures, three temperatures and multiple vibration temperatures. Since the microscopic transition and radiation process are closely related to the vibration and electron temperature, at least two temperatures or more solution equations are required. Taking the two-temperature thermochemical non-equilibrium model as an example, its dimensionless solution equation is as follows:

[0060] ;

[0061] Where t and (x, y, z) represent time and coordinates respectively, Re is the incoming flow Reynolds number, Q is a conserved variable, , , and , , They correspond to the convection terms and viscosity terms in three directions respectively, is the thermochemical non-equilibrium source term. The specific forms of the conservation quantity and source term are as follows:

[0062] ;

[0063] ;

[0064] Among them, u, v, w, , E represent the velocity, density and total energy of the gas in three directions respectively, the subscript i is the gas component number, i=1, 2,…, Ns, Ns is the total number of gas components, and are the density and chemical non-equilibrium source term of component i, , is the total vibrational-electronic energy and the vibrational-electronic energy nonequilibrium source term, is the radiation source term.

[0065] Step S13: Based on the initial convergent flow field results, the initial radiation source term is calculated by aerodynamic radiation coupling using the Step model spectral model and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the first radiation source term and the first convergent flow field result under the optical thin approximation.

[0066] In this embodiment, based on the initial convergent flow field results, the absorption coefficient of the target high-temperature gas spectrum is calculated using the Step model spectral model; the absorption coefficient of the target high-temperature gas spectrum and the initial radiation source term are input into the theoretical formula of the radiation source term under the optical thin approximation to obtain the radiation source term under the optical thin approximation, and the radiation source term under the optical thin approximation is input into the target high-temperature thermochemical non-equilibrium flow field solution equation for calculation to obtain the first radiation source term under the optical thin approximation and the first convergent flow field result.

[0067] The theoretical formula of the radiation source term under the optical thin approximation is:

[0068] ;

[0069] in, is the radiation source term, is the circumference constant, is the position vector, , is the spectral frequency, is the high temperature gas spectral absorption coefficient, is the blackbody spectral radiation intensity.

[0070] After calculating the absorption coefficient of the target high-temperature gas spectrum, the radiation source term under the optical thin approximation is input into the target high-temperature thermochemical non-equilibrium flow field solution equation for calculation to obtain the current radiation source term, and record the current iteration step; determine whether the current iteration step is within the preset first iteration step interval. If the current iteration step is within the preset first iteration step interval, perform iterative calculation until the current iteration step is no longer within the preset first iteration step interval, then jump to the process of calculating the absorption coefficient of the target high-temperature gas spectrum to obtain the first radiation source term under the optical thin approximation and the first convergent flow field result.

[0071] Specifically, based on the initial convergent flow field results, the Step model spectral model is used to calculate the first radiation source term under the optical thin approximation: Under the optical thin approximation, the radiation source term The calculation form is very simple. There is no need to solve the radiation transport equation. It only needs to integrate the emission intensity within the band, and the additional calculation amount is very small. After adopting the simplified spectral band model, the calculation amount can be further reduced.

[0072] Optically thin approximation The theoretical formula is shown above, and It is generally a function of the flow field parameters and spectral bands at the local location. The calculation is as follows:

[0073] ;

[0074] in, is the Stefan-Boltzmann constant, T is the electron representative temperature under the current thermochemical non-equilibrium model, is the position vector, subscript m is the spectral band number, m=1, 2, ..., M, and is the Planck average absorption coefficient of the mth spectral band of the high-temperature gas and the blackbody radiation intensity spectral band integral weight. The integral form calculated according to the spectral frequency ν is as follows:

[0075] ;

[0076] ;

[0077] At this time, the spectral model can choose a simple model with M=1 or 2, that is, a gray gas model or a two-step model.

[0078] Then, the radiation source term under the optical thin approximation is input into the target high-temperature thermochemical non-equilibrium flow field solution equation for calculation. Based on the initial converged flow field results, the non-equilibrium flow field calculation of the coupled radiation source term is carried out. In the iterative process of the aerodynamic radiation coupling calculation, the first iteration step interval is The radiation source term is not updated, but the radiation source term under the optical thin approximation is kept unchanged to reduce the amount of calculation. After that, the radiation source term under the optical thin approximation is repeatedly updated, and then the process of calculating the absorption coefficient of the target high-temperature gas spectrum is repeated until the first convergent flow field result of the aerodynamic radiation coupling calculation based on the Stepmodel spectral model and the optical thin approximation is obtained.

[0079] Step S14: Based on the first convergent flow field result, the first radiation source term is subjected to aerodynamic-radiation coupling calculation using the Step model spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain a second radiation source term and a second convergent flow field result.

[0080] In this embodiment, based on the first convergent flow field result, the Step model spectral model, the radiation transfer solution method, the target high-temperature thermochemical non-equilibrium flow field solution equation and the radiation source term theoretical formula based on the discrete coordinate method are used to perform aerodynamic radiation coupling calculation on the first radiation source term to obtain the current radiation source term and record the current iteration step; the radiation transfer solution method includes the discrete coordinate method; it is determined whether the current iteration step is within the preset second iteration step interval. If the current iteration step is within the preset second iteration step interval, iterative calculation is performed until the current iteration step is not within the preset second iteration step interval, then the process of performing aerodynamic radiation coupling calculation on the first radiation source term is jumped to obtain the second radiation source term and the second convergent flow field result.

[0081] Specifically, based on the results of the first convergent flow field, the Step model spectral model is used, and a higher precision radiation transport solution method, such as the discrete coordinate method DOM, is used to solve the radiation transport equation and calculate the second radiation source term. The radiation transport equation in the high temperature gas flow field is in the form of:

[0082] ;

[0083] Where I is the local spectral radiation intensity, is the radiation propagation direction vector, For its j-direction component, the above formula shrinks and sums the subscript j to meet the Einstein summation convention. The basic idea of ​​the discrete coordinate method is to discretize the radiation propagation direction according to a predetermined criterion, then iterate and solve it, and finally sum it statistically. Based on the discrete coordinate method, the above equation is discretized according to L spatial angular directions and M spectral bands, and the form is as follows:

[0084] ;

[0085] Wherein, the superscript l is the spatial angle direction number, l = 1, 2, ..., L, is the blackbody spectral radiation intensity of the mth spectral band, is the spectral radiation intensity of high temperature gas in the lth spatial angle direction and the mth spectral band, and the corresponding calculation method is:

[0086] ;

[0087] ;

[0088] The formula After expansion, a diagonal linear equation system is formed, and the main coefficients are determined by the coordinate position x and the propagation direction vector The decision can be given in the initial calculation and does not need to be calculated in the iterative process to improve the computational efficiency.

[0089] formula Conventional direct methods and iterative methods can be used to solve the problem, such as the TDMA (Tridiagonal Matrix Algorithm) chase method and the ADI (Alternating Direction Implicit) alternating implicit iterative method. And, after the iteration converges, the high-temperature gas spectral radiation intensity in each spatial angular direction and spectral band is obtained. , and then obtain the radiation source term . The theoretical formula is:

[0090] ;

[0091] Among them, Ω is the spatial solid angle, which means that the spectral radiation intensity of the high-temperature gas should be integrated over the entire 4π spatial solid angle. Similarly, after discretizing the above formula according to L spatial angle directions and M spectral bands, we get:

[0092] ;

[0093] in, is the weight of the lth spatial angle discrete direction, which will be given synchronously when determining the spatial angle discrete direction vector B.

[0094] Then, the above steps obtained Substitute it into the target high-temperature thermochemical non-equilibrium flow field solution equation, and further carry out the non-equilibrium flow field calculation of the coupled radiation source term based on the first convergent flow field result. The radiation source term is not updated, but the above steps are obtained Remain unchanged to reduce the amount of calculation. Arrive at the second iteration step interval After that, repeat the update of the radiation source item , and then repeat the process of aerodynamic radiation coupling calculation for the first radiation source item until the second convergent flow field result of aerodynamic radiation coupling calculation based on the step model spectral model and discrete coordinate method is obtained.

[0095] Step S15: Based on the second convergent flow field result, the second radiation source term is subjected to aerodynamic-radiation coupling calculation using the Line-by-Line spectral model, the radiation transfer solution method, and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the target convergent flow field.

[0096] In this embodiment, based on the result of the second convergent flow field, the Line-by-Line spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation are used to perform aerodynamic radiation coupling calculation on the second radiation source term to obtain the current radiation source term, and record the current iteration step; determine whether the current iteration step is within the preset third iteration step interval. If the current iteration step is within the preset third iteration step interval, perform iterative calculation until the current iteration step is no longer within the preset third iteration step interval, then jump to the process of performing aerodynamic radiation coupling calculation on the second radiation source term to obtain the target convergent flow field.

[0097] The theoretical formula of the radiation source term based on the discrete coordinate method is:

[0098] ;

[0099] in, is the radiation source term, is the circumference constant, is the position vector, , is the spectral frequency, is the high temperature gas spectral absorption coefficient, is the blackbody spectral radiation intensity, I is the local spectral radiation intensity, is the radiation propagation direction vector, is the spatial solid angle.

[0100] Specifically, based on the results of the second convergent flow field, a high-precision Line-by-Line spectral model and a high-precision radiation transport solution method, such as the discrete coordinate method DOM, are used to solve the radiation transport equation and calculate the radiation source term. When calculating based on the Line-by-Line spectral model, the basic solution method is consistent with the above steps. Since the Line-by-Line spectral model can obtain detailed spectral information of the entire spectrum, the discrete spectral band interval is The smaller it is, the more the number of discrete spectral band intervals M is.

[0101] The above steps obtained Substitute the target high-temperature thermochemical non-equilibrium flow field solution equation into the solution equation, and carry out the final non-equilibrium flow field calculation of the coupled radiation source term based on the second convergent flow field result. The radiation source term is not updated, but the above steps are obtained Remain unchanged to reduce the amount of calculation. Arrive at the third iteration step interval After that, repeat the update of the radiation source item , and then repeat the process of aerodynamic radiation coupling calculation for the second radiation source item until the target convergent flow field of aerodynamic radiation coupling calculation based on Line-by-Line spectral model and discrete coordinate method is obtained.

[0102] Step S16: using the target convergent flow field to predict the radiation heat flux of the target high-speed aircraft.

[0103] In the coupled simulation of high-temperature thermochemical nonequilibrium flow and radiation effects, if high-precision spectroscopy and high-precision radiation transfer solution methods are used, the amount of calculation will increase significantly and the calculation efficiency will decrease. This application proposes an accelerated calculation method for coupled simulation of thermochemical nonequilibrium flow and radiation effects, which can greatly improve the calculation efficiency during the coupled calculation process. The specific process of accelerated calculation is as follows: Figure 2 As shown in the figure, firstly, a flow field solution calculation grid is constructed for the target high-speed aircraft, and the target high-temperature gas physical and chemical model and the incoming flow parameters corresponding to the target high-speed aircraft are set. Then, the radiation source term is ignored to obtain the conventional non-radiative high-temperature thermochemical non-equilibrium flow field; then, the aerodynamic radiation coupling calculation is based on the Step model spectral model and the optical thin approximation; then, the aerodynamic radiation coupling calculation is based on the Step model spectral model and the advanced radiation transfer solution method; finally, the aerodynamic radiation coupling calculation is based on the Line-by-Line spectral model and the advanced radiation transfer solution method to calculate the final converged aerodynamic radiation coupling flow field. At the same time, in the aerodynamic radiation coupling iteration process, it is not necessary to update the radiation source term at each step. It can be assumed that the radiation source term remains unchanged within a certain flow field calculation interval step, and the radiation field is solved to update the radiation source term after the step interval is reached. For the spectral model used in the calculation, a simple gray gas or Step model spectral model with low computational complexity can be selected in the early convergence process, and a high-precision Line-by-Line spectral model can be used in the final convergence calculation.

[0104] The main process demonstrated in this application includes a four-level acceleration process: non-radiative high-temperature flow field calculation → aerodynamic radiation coupling calculation based on the Stepmodel spectral model and optical thin approximation → aerodynamic radiation coupling calculation based on the Stepmodel spectral model and advanced radiation transfer solution method → ​​aerodynamic radiation coupling calculation based on the Line-by-Line spectral model and advanced radiation transfer solution method. This method can further significantly reduce the amount of calculation and improve the calculation efficiency.

[0105] In this embodiment, a flow field solution calculation grid is constructed for a target high-speed aircraft, and a target high-temperature gas physicochemical model and incoming flow parameters corresponding to the target high-speed aircraft are set; a target high-temperature thermochemical non-equilibrium flow field solution equation is generated based on the flow field solution calculation grid, the target high-temperature gas physicochemical model and the incoming flow parameters, an initial radiation source term is set and an initial convergent flow field result is calculated; on the basis of the initial convergent flow field result, the initial radiation source term is calculated by aerodynamic radiation coupling using the Step model spectral model and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain a first radiation source term and a first convergent flow field result under optical thin approximation; on the basis of the first convergent flow field result, the Step model spectral model is used to calculate the initial radiation source term by aerodynamic radiation coupling, and a first radiation source term and a first convergent flow field result under optical thin approximation are obtained; on the basis of the first convergent flow field result, the Step model is used to calculate the initial radiation source term by aerodynamic radiation coupling, and a first radiation source term and a first convergent flow field result are obtained by aerodynamic radiation coupling using the Step model spectral model and the target high-temperature thermochemical non-equilibrium flow field solution equation. The first radiation source term is subjected to aerodynamic-radiation coupling calculation using the model spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the second radiation source term and the second convergent flow field result; based on the second convergent flow field result, the second radiation source term is subjected to aerodynamic-radiation coupling calculation using the Line-by-Line spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the target convergent flow field; the radiation heat flux of the target high-speed aircraft is predicted using the target convergent flow field. The present application first constructs a flow field solution calculation grid for the target high-speed aircraft, and sets the target high-temperature gas physicochemical model and incoming flow parameters corresponding to the target high-speed aircraft, and then improves the computational efficiency of the aerodynamic radiation coupling numerical simulation, including a four-stage acceleration process: initial high-temperature flow field calculation without radiation, aerodynamic radiation coupling calculation based on the Step model spectral model and optical thin approximation, aerodynamic radiation coupling calculation based on the Step model spectral model and radiation transfer solution method, and aerodynamic radiation coupling calculation based on the Line-by-Line spectral model and radiation transfer solution method to obtain the target convergent flow field, and use the target convergent flow field to predict the radiation heat flux of the target high-speed aircraft. In the aerodynamic radiation coupling calculation, it is not necessary to update the radiation source term information at each step, thereby greatly reducing the amount of calculation and improving the computational efficiency in the coupling calculation process.

[0106] See also Figure 3 As shown, the embodiment of the present invention discloses a radiation heat flow prediction device based on a convergent flow field, which may specifically include:

[0107] The grid construction and parameter setting module 11 is used to construct a flow field solution calculation grid for the target high-speed aircraft, and set the target high-temperature gas physical and chemical model and incoming flow parameters corresponding to the target high-speed aircraft;

[0108] The solution equation generation module 12 is used to generate the target high-temperature thermochemical non-equilibrium flow field solution equation based on the flow field solution calculation grid, the target high-temperature gas physical and chemical model and the incoming flow parameters, set the initial radiation source term and calculate the initial convergent flow field result;

[0109] A first radiation source term calculation module 13 is used to perform aerodynamic radiation coupling calculation on the initial radiation source term based on the initial convergent flow field result by using the Stepmodel spectral model and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the first radiation source term and the first convergent flow field result under the optical thin approximation;

[0110] A second radiation source term calculation module 14 is used to perform aerodynamic radiation coupling calculation on the first radiation source term based on the first convergent flow field result by using the Step model spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain a second radiation source term and a second convergent flow field result;

[0111] A target convergent flow field calculation module 15 is used to perform aerodynamic radiation coupling calculation on the second radiation source term based on the second convergent flow field result by using the Line-by-Line spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain a target convergent flow field;

[0112] The radiation heat flux prediction module 16 is used to predict the radiation heat flux of the target high-speed aircraft using the target convergent flow field.

[0113] In some specific embodiments, the equation generation module 12 may specifically include:

[0114] A flow field solution equation generation module, used to generate a target high-temperature thermochemical non-equilibrium flow field solution equation based on a preset high-temperature gas thermochemical non-equilibrium flow field numerical simulation method and the flow field solution calculation grid, the target high-temperature gas physical and chemical model, and the incoming flow parameters;

[0115] The initial convergent flow field result calculation module is used to set the initial radiation source term and iteratively calculate the initial radiation source term until the flow field converges to obtain the initial convergent flow field result.

[0116] In some specific embodiments, the first radiation source term calculation module 13 may specifically include:

[0117] An absorption coefficient calculation module, used to calculate the absorption coefficient of the target high-temperature gas spectrum using a step model spectrum model based on the initial convergent flow field result;

[0118] The first radiation source term calculation module is used to input the absorption coefficient of the target high-temperature gas spectrum and the initial radiation source term into the theoretical formula of the radiation source term under the optical thin approximation to obtain the radiation source term under the optical thin approximation, and input the radiation source term under the optical thin approximation into the target high-temperature thermochemical non-equilibrium flow field solution equation for calculation to obtain the first radiation source term under the optical thin approximation and the first convergent flow field result.

[0119] In some specific embodiments, the theoretical formula of the radiation source term under the optical thin approximation is:

[0120] ;

[0121] in, is the radiation source term, is the circumference constant, is the position vector, , is the spectral frequency, is the high temperature gas spectral absorption coefficient, is the blackbody spectral radiation intensity.

[0122] In some specific embodiments, the first radiation source term calculation module 13 may specifically include:

[0123] An input module, used to input the radiation source term under the optical thin approximation into the target high-temperature thermochemical non-equilibrium flow field solution equation for calculation, obtain the current radiation source term, and record the current iteration step;

[0124] The first iteration step interval judgment module is used to judge whether the current iteration step is within the preset first iteration step interval. If the current iteration step is within the preset first iteration step interval, iterative calculation is performed until the current iteration step is no longer within the preset first iteration step interval, then jumping to the process of calculating the absorption coefficient of the target high-temperature gas spectrum to obtain the first radiation source term and the first convergent flow field result under the optical thin approximation.

[0125] In some specific embodiments, the second radiation source term calculation module 14 may specifically include:

[0126] An iterative step length recording module is used to perform aerodynamic radiation coupling calculation on the first radiation source term based on the first convergent flow field result by using the Stepmodel spectral model, the radiation transfer solution method, the target high-temperature thermochemical non-equilibrium flow field solution equation, and the radiation source term theoretical formula based on the discrete coordinate method to obtain the current radiation source term and record the current iterative step length; the radiation transfer solution method includes the discrete coordinate method;

[0127] The second iteration step interval judgment module is used to judge whether the current iteration step is within the preset second iteration step interval. If the current iteration step is within the preset second iteration step interval, iterative calculation is performed until the current iteration step is no longer within the preset second iteration step interval, then the process of performing aerodynamic radiation coupling calculation on the first radiation source item is jumped to obtain the second radiation source item and the second convergent flow field result.

[0128] In some specific embodiments, the target convergence flow field calculation module 15 may specifically include:

[0129] A second radiation source term coupling calculation module is used to perform aerodynamic radiation coupling calculation on the second radiation source term based on the second convergent flow field result by using the Line-by-Line spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the current radiation source term and record the current iteration step size;

[0130] The third iteration step interval judgment module is used to judge whether the current iteration step is within the preset third iteration step interval. If the current iteration step is within the preset third iteration step interval, iterative calculation is performed until the current iteration step is not within the preset third iteration step interval, then jumping to the process of performing aerodynamic radiation coupling calculation on the second radiation source item to obtain the target convergent flow field.

[0131] In some specific embodiments, the theoretical formula of the radiation source term based on the discrete coordinate method is:

[0132] ;

[0133] in, is the radiation source term, is the circumference constant, is the position vector, , is the spectral frequency, is the high temperature gas spectral absorption coefficient, is the blackbody spectral radiation intensity, I is the local spectral radiation intensity, is the radiation propagation direction vector, is the spatial solid angle.

[0134] Figure 4A schematic diagram of the structure of an electronic device provided in an embodiment of the present application. The electronic device 20 may specifically include: at least one processor 21, at least one memory 22, a power supply 23, a communication interface 24, an input / output interface 25, and a communication bus 26. The memory 22 is used to store a computer program, which is loaded and executed by the processor 21 to implement the relevant steps in the method for predicting radiation heat flow based on a convergent flow field performed by the electronic device disclosed in any of the aforementioned embodiments.

[0135] In this embodiment, the power supply 23 is used to provide working voltage for each hardware device on the electronic device 20; the communication interface 24 can create a data transmission channel between the electronic device 20 and the external device, and the communication protocol it follows is any communication protocol that can be applied to the technical solution of the present application, and is not specifically limited here; the input and output interface 25 is used to obtain external input data or output data to the outside world, and its specific interface type can be selected according to specific application needs and is not specifically limited here.

[0136] In addition, the memory 22, as a carrier for storing resources, can be a read-only memory, a random access memory, a disk or an optical disk, etc. The resources stored thereon include an operating system 221, a computer program 222 and data 223, etc. The storage method can be temporary storage or permanent storage.

[0137] Among them, the operating system 221 is used to manage and control the hardware devices and computer program 222 on the electronic device 20, so as to realize the operation and processing of the data 223 in the memory 22 by the processor 21, which can be Windows, Unix, Linux, etc. In addition to including a computer program that can be used to complete the radiation heat flow prediction method based on the convergent flow field performed by the electronic device 20 disclosed in any of the aforementioned embodiments, the computer program 222 can also further include a computer program that can be used to complete other specific tasks. In addition to including data transmitted from an external device received by the radiation heat flow prediction device based on the convergent flow field, the data 223 can also include data collected by its own input and output interface 25, etc.

[0138] The steps of the method or algorithm described in conjunction with the embodiments disclosed herein may be implemented directly using hardware, a software module executed by a processor, or a combination of the two. The software module may be placed in a random access memory (RAM), a memory, a read-only memory (ROM), an electrically programmable ROM, an electrically erasable programmable ROM, a register, a hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art.

[0139] Furthermore, an embodiment of the present application also discloses a computer-readable storage medium, in which a computer program is stored. When the computer program is loaded and executed by a processor, the steps of the radiation heat flow prediction method based on the convergent flow field disclosed in any of the aforementioned embodiments are implemented.

[0140] Finally, it should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0141] The above is a detailed introduction to the radiation heat flux prediction method, device, equipment and storage medium based on the convergent flow field provided by the present invention. Specific examples are used in this article to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea; at the same time, for general technical personnel in this field, according to the idea of ​​the present invention, there will be changes in the specific implementation method and application scope. In summary, the content of this specification should not be understood as a limitation on the present invention.

Claims

1. A radiation heat flow prediction method based on convergent flow field, characterized in that: include: Constructing a flow field solution calculation grid for a target high-speed aircraft, and setting a target high-temperature gas physical and chemical model and incoming flow parameters corresponding to the target high-speed aircraft; Generate a target high-temperature thermochemical non-equilibrium flow field solution equation based on the flow field solution calculation grid, the target high-temperature gas physical and chemical model, and the incoming flow parameters, set an initial radiation source term, and calculate an initial convergent flow field result; Based on the initial convergent flow field result, the aerodynamic radiation coupling calculation of the initial radiation source term is performed using the Step model spectral model and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the first radiation source term and the first convergent flow field result under the optical thin approximation; Based on the first convergent flow field result, the first radiation source term is subjected to aerodynamic radiation coupling calculation using the Step model spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain a second radiation source term and a second convergent flow field result; Based on the result of the second convergent flow field, the second radiation source term is subjected to aerodynamic-radiation coupling calculation using the Line-by-Line spectral model, the radiation transfer solution method, and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the target convergent flow field; The target convergent flow field is used to predict the radiation heat flux of the target high-speed aircraft.

2. The method for predicting radiation heat flow based on convergent flow field according to claim 1, characterized in that: The method generates a target high-temperature thermochemical non-equilibrium flow field solution equation based on the flow field solution calculation grid, the target high-temperature gas physical and chemical model, and the incoming flow parameters, sets an initial radiation source term, and calculates an initial convergent flow field result, including: Using a preset high-temperature gas thermochemical non-equilibrium flow field numerical simulation method, and based on the flow field solution calculation grid, the target high-temperature gas physical and chemical model, and the incoming flow parameters, a target high-temperature thermochemical non-equilibrium flow field solution equation is generated; An initial radiation source term is set, and the initial radiation source term is iteratively calculated until the flow field converges to obtain an initial converged flow field result.

3. The method for predicting radiation heat flow based on convergent flow field according to claim 1, characterized in that: Based on the initial convergent flow field result, the initial radiation source term is calculated by aerodynamic radiation coupling using the Step model spectral model and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the first radiation source term and the first convergent flow field result under the optical thin approximation, including: Based on the initial convergent flow field results, the absorption coefficient of the target high temperature gas spectrum is calculated using the Step model spectrum model; The absorption coefficient of the target high-temperature gas spectrum and the initial radiation source term are input into the theoretical formula of the radiation source term under the optically thin approximation to obtain the radiation source term under the optically thin approximation, and the radiation source term under the optically thin approximation is input into the target high-temperature thermochemical non-equilibrium flow field solution equation for calculation to obtain the first radiation source term under the optically thin approximation and the first convergent flow field result.

4. The method for predicting radiation heat flow based on convergent flow field according to claim 3, characterized in that: The theoretical formula of the radiation source term under the optical thin approximation is: ； in, is the radiation source term, is the circumference constant, is the position vector, , is the spectral frequency, is the high temperature gas spectral absorption coefficient, is the blackbody spectral radiation intensity.

5. The method for predicting radiation heat flow based on convergent flow field according to claim 3, characterized in that: The step of inputting the radiation source term under the optical thin approximation into the target high temperature thermochemical non-equilibrium flow field solution equation for calculation to obtain the first radiation source term under the optical thin approximation and the first convergent flow field result includes: Inputting the radiation source term under the optical thin approximation into the target high-temperature thermochemical non-equilibrium flow field solution equation for calculation, obtaining the current radiation source term, and recording the current iteration step length; Determine whether the current iteration step is within the preset first iteration step interval. If the current iteration step is within the preset first iteration step interval, perform iterative calculation until the current iteration step is no longer within the preset first iteration step interval, then jump to the process of calculating the absorption coefficient of the target high-temperature gas spectrum to obtain the first radiation source term and the first convergent flow field result under the optical thin approximation.

6. The method for predicting radiation heat flow based on convergent flow field according to any one of claims 1 to 5, characterized in that: Based on the first convergent flow field result, the first radiation source term is subjected to aerodynamic radiation coupling calculation using the Step model spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain a second radiation source term and a second convergent flow field result, including: Based on the first convergent flow field result, the first radiation source term is subjected to aerodynamic radiation coupling calculation using the Step model spectral model, the radiation transfer solution method, the target high-temperature thermochemical non-equilibrium flow field solution equation, and the radiation source term theoretical formula based on the discrete coordinate method to obtain the current radiation source term and record the current iteration step length; the radiation transfer solution method includes the discrete coordinate method; Determine whether the current iteration step is within the preset second iteration step interval. If the current iteration step is within the preset second iteration step interval, perform iterative calculation until the current iteration step is not within the preset second iteration step interval, then jump to the process of performing aerodynamic radiation coupling calculation on the first radiation source term to obtain a second radiation source term and a second convergent flow field result; Accordingly, based on the result of the second convergent flow field, the second radiation source term is subjected to aerodynamic radiation coupling calculation using the Line-by-Line spectral model, the radiation transfer solution method, and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the target convergent flow field, including: Based on the second convergent flow field result, the second radiation source term is calculated by aerodynamic radiation coupling using the Line-by-Line spectral model, the radiation transfer solution method, and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the current radiation source term and record the current iteration step size; Determine whether the current iteration step is within the preset third iteration step interval. If the current iteration step is within the preset third iteration step interval, perform iterative calculation until the current iteration step is no longer within the preset third iteration step interval, then jump to the process of performing aerodynamic-radiation coupling calculation on the second radiation source item to obtain the target convergent flow field.

7. The method for predicting radiation heat flow based on convergent flow field according to claim 6, characterized in that: The theoretical formula of the radiation source term based on the discrete coordinate method is: ； in, is the radiation source term, is the circumference constant, is the position vector, , is the spectral frequency, is the high temperature gas spectral absorption coefficient, is the blackbody spectral radiation intensity, I is the local spectral radiation intensity, is the radiation propagation direction vector, is the spatial solid angle.

8. A radiation heat flow prediction device based on convergent flow field, characterized in that: include: A grid construction and parameter setting module is used to construct a flow field solution calculation grid for a target high-speed aircraft, and to set a target high-temperature gas physical and chemical model and incoming flow parameters corresponding to the target high-speed aircraft; A solution equation generation module, used to generate a target high-temperature thermochemical non-equilibrium flow field solution equation based on the flow field solution calculation grid, the target high-temperature gas physical and chemical model and the incoming flow parameters, set an initial radiation source term and calculate an initial convergent flow field result; A first radiation source term calculation module is used to perform aerodynamic radiation coupling calculation on the initial radiation source term based on the initial convergent flow field result by using a step model spectral model and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the first radiation source term and the first convergent flow field result under the optical thin approximation; A second radiation source term calculation module is used to perform aerodynamic radiation coupling calculation on the first radiation source term based on the first convergent flow field result by using the Stepmodel spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain a second radiation source term and a second convergent flow field result; a target convergent flow field calculation module, for performing aerodynamic radiation coupling calculation on the second radiation source term based on the result of the second convergent flow field by using the Line-by-Line spectral model, the radiation transfer solution method and the target high-temperature thermochemical non-equilibrium flow field solution equation to obtain the target convergent flow field; The radiation heat flux prediction module is used to predict the radiation heat flux of the target high-speed aircraft using the target convergent flow field.

9. An electronic device, characterized in that: include: Memory, used to store computer programs; A processor is used to execute the computer program to implement the radiation heat flow prediction method based on convergent flow field as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that: Used to store a computer program; wherein, when the computer program is executed by a processor, the radiation heat flow prediction method based on a convergent flow field as described in any one of claims 1 to 7 is implemented.

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