CN106742060A - A kind of ground predicting method of Aerodynamic Heating and material catalysis characteristics coupling effect - Google Patents

Abstract

The invention discloses a ground prediction method for the coupling effect of aerodynamic heat and material catalytic properties, which includes: using a theoretical method to analyze the material surface heat flow under the condition of different material surface catalytic properties; The functional relationship of the change of catalytic recombination coefficient; based on the flight state and aerodynamic shape, the thermal environment of typical parts is evaluated, and the thermal environment engineering calculation results of typical parts are combined with the functional relationship of the catalytic effect of the material surface with the change of the catalytic recombination coefficient of the material surface. Prediction of the heat flow response history of the aircraft surface in the flight state; use the heat transfer method to realize the prediction of the internal temperature response history of the aircraft in the flight state. The invention realizes the accurate description of the coupling effect of the aerodynamic heat and the catalytic properties of the material, and provides strong support for the refined design of the design of the anti-heat insulation system under the coupling effect of the aerodynamic heat and the catalytic properties of the material.

Description

A Ground Prediction Method of Coupling Effects of Aerothermal and Material Catalytic Properties

technical field

The invention belongs to the technical field of aircraft testing, in particular to a ground prediction method for coupling effects of aerodynamic heat and material catalytic properties.

Background technique

When the aircraft flies at high speed, it will form a strong bow shock wave around the head. Due to the viscous dissipation effect and the strong compression of the shock wave, part of the huge kinetic energy loss is converted into the internal energy of the gas in the shock layer. When the incoming air passes through the shock wave, it is heated to thousands of degrees or even tens of thousands of degrees to form a high-temperature gas layer. The degrees of freedom of translation, rotation and vibration of gas molecules are excited, dissociated or even ionized by energy. The impact of vibrational energy excitation, molecular dissociation, atomic recombination, chemical reaction between components, and ionization on the flow field parameters is collectively referred to as the high-temperature real gas effect. The high-temperature real gas effect not only produces severe aerodynamic heating on the surface of the aircraft, but also has a strong nonlinear coupling with the heat-resistant material on the surface of the aircraft. The recombination rate of dissociated atoms on the surface of the heat-resistant material directly affects the chemical heating of the surface of the heat-resistant material on the surface of the body by the chemical non-equilibrium shock layer.

Due to the lack of in-depth analysis and relevant data, the traditional design cannot accurately describe the coupling effect of aerodynamic heat and material catalytic properties, resulting in a conservative design of the thermal protection system, which brings great difficulties to the optimal design of the thermal protection system .

Contents of the invention

The technical problem of the present invention is to overcome the deficiencies of the prior art, and provide a ground prediction method for the coupling effect of aerothermal and material catalytic properties, aiming at accurately describing the coupling effect of aerothermal and material catalytic properties, providing aerothermal and material catalytic properties. The refined design of the anti-insulation system design under the coupling effect of material catalytic properties provides strong support.

In order to solve the above technical problems, the present invention discloses a ground prediction method for coupling effects of aerodynamic heat and material catalytic properties, including:

Analyze the material surface heat flow under the condition of different material surface catalytic properties, and obtain the surface heat flow under different catalytic properties of the material surface under the flying state;

Carry out fitting analysis on the surface heat flow under the different catalytic characteristic conditions of the material surface obtained in the flight state, obtain the functional relationship of the catalytic effect of the material surface with the change of the catalytic recombination coefficient of the material surface;

Engineering calculations are carried out on the surface heat flow of typical parts of materials by using engineering algorithms, and the fully catalyzed material surface heat flow of typical parts that changes with ballistic time is obtained;

According to the fully catalyzed material surface heat flow of the typical part that changes with the ballistic time and the actual material surface material catalytic composite coefficient of the typical part, combined with the above functional relationship, the partial catalyzed material surface heat flow of the typical part under the flight state is obtained as a function of the trajectory change process;

Using the heat transfer method to analyze the change history of the surface heat flow of the partially catalyzed material in the typical part of the flight state with the trajectory, and obtain the internal temperature distribution of the typical part of the flight state under different surface catalytic characteristics, and the internal temperature Variation history with ballistic time.

In the ground prediction method of the coupling effect of aerodynamic heat and material catalytic properties, the surface heat flow of the material surface under different material surface catalytic properties is analyzed, and the surface heat flow under different catalytic properties of the material surface in the flight state is obtained, including:

The high-temperature non-equilibrium three-dimensional flow field is numerically simulated by solving the chemical reaction flow N-S equation with component source terms, and the general expression of the material surface heat flow under the condition of different material surface catalytic properties is obtained based on the dimensionless form governing equation:

Among them, q ₀ represents the material surface heat flow under the condition of different material surface catalytic properties, q represents the translational heat flow, q _v represents the vibration heat flow, k represents the translational heat transfer coefficient, T represents the translational temperature, n represents the normal coordinate of the material surface, k _V represents the thermal conductivity of vibration, T _V represents the vibration temperature, N _s represents the total number of components, the subscript i represents the parameter of the i-th component, ρ, M, h, D and c represent the air density and the molar mass of the component, respectively , enthalpy, diffusion coefficient and mass fraction, E _V represents the total vibrational energy of molecular components;

Among them, the catalytic properties of the material surface conditions are as follows:

in, is the surface recombination rate of the material, is the gas constant, γ is the catalytic recombination coefficient of the material surface;

The catalytic properties of the material surface conditions As a boundary condition, it is brought into the control equation in the dimensionless form to obtain the surface heat flow under the condition of different catalytic properties on the surface of the material in the flight state.

In the ground prediction method for the coupling effect of aerodynamic heat and material catalytic properties, the obtained surface heat flow under different catalytic properties of the material surface in the flight state is analyzed by fitting and analysis, and the catalytic effect of the material surface is changed with the catalytic performance of the material surface. The functional relationship of compound coefficient changes, including:

The surface heat flow under the conditions of different catalytic properties of the material surface in the flight state was fitted and analyzed, and the following functional relationship was obtained:

q _h /q _f ＝φlog(γ)

Among them, q _h represents the surface heat flow of the material under the partial catalytic characteristic condition, q _f represents the material surface heat flow under the complete catalytic characteristic condition, φ=q _f ^A , and A is a constant value coefficient.

In the ground prediction method of the above-mentioned coupling effect of aerothermal and material catalytic properties, the governing equation in the dimensionless form is as follows:

in,

u _j τ _xj ＝uτ _xx +vτ _xy +wτ _xz

Among them, u, v, and w are the velocity components in the three coordinate directions of x, y, and z, τ represents the shear stress, E represents the total translational energy of molecular components, w _i represents the chemical non-equilibrium source term, and w _V represents Vibration non-equilibrium energy source item, μ represents dynamic viscosity, q represents translational heat flow, p represents pressure, Indicates the divergence of velocity.

In the above-mentioned ground prediction method for the coupling effect of aerodynamic heat and material catalytic properties, engineering calculations are carried out on the surface heat flow of typical parts of materials by using engineering algorithms, and the fully catalyzed material surface heat flow of typical parts that changes with ballistic time is obtained, including:

When the typical position is the stagnation point of the tip, the heat flow on the surface of the material at the stagnation point of the tip is calculated by using the compressibility-corrected F-R formula calculation method to obtain the heat flow on the surface of the material that is completely catalyzed by the stagnation point of the tip that changes with the ballistic time.

In the above-mentioned ground prediction method for the coupling effect of aerodynamic heat and material catalytic properties, engineering calculations are carried out on the surface heat flow of typical parts of materials by using engineering algorithms, and the fully catalyzed material surface heat flow of typical parts that changes with ballistic time is obtained, including:

When the typical part is a ball head, the heat flow on the surface of the ball head material is calculated by using the "axisymmetric analogy" method based on accurate streamlines, and the heat flow on the surface of the material surface completely catalyzed by the ball head that changes with the ballistic time is obtained.

In the ground prediction method for the coupling effect of aerodynamic heat and material catalytic properties, the heat flow of the material surface that is completely catalyzed at the typical position that changes with the ballistic time and the actual material surface material catalytic recombination coefficient of the typical position, combined with the above According to the functional relationship, the change history of the surface heat flow of the partially catalyzed material surface with the ballistic trajectory in the typical part of the flight state is obtained, including:

Substituting the fully catalyzed material surface heat flow and the real material surface material catalytic recombination coefficient of the typical part that changes with the ballistic time into the functional relationship q _h /q _f = φlog(γ), the typical part under the flight state is obtained Variation history of heat flux on the surface of partially catalyzed materials with ballistics.

In the above-mentioned ground prediction method of the coupled effect of aerodynamic heat and material catalytic properties, the heat transfer method is used to analyze the change history of the surface heat flow of the partially catalyzed material surface in the typical part of the flight state with the ballistic trajectory, and the flight state is obtained. The internal temperature distribution of typical parts under different surface catalytic properties, and the change history of the internal temperature with ballistic time, including:

Using the obtained change history of heat flow on the surface of the material partially catalyzed by the typical part of the flight state with the trajectory as the boundary condition of the three-dimensional heat transfer control equations, the three-dimensional heat transfer control equations are solved, and the typical parts of the flight state are different. The internal temperature distribution under surface catalytic properties, and the history of said internal temperature as a function of ballistic time.

The present invention has the following advantages:

Aiming at the problem of lack of coupling effect evaluation method for high-speed aircraft aerothermal and material catalytic properties, the present invention proposes a method for responding to the high-speed aircraft's aerodynamic thermal environment and temperature field in the flight state through the aircraft's flight state, aerodynamic shape and aircraft surface material catalytic properties. method of forecasting. Realized the ground prediction of the heat flow response history of the aircraft surface and the internal temperature response history of the aircraft under any surface catalytic properties, provided a feasible solution for the quantitative evaluation of the coupling effect of aerothermal and material catalytic properties of high-speed aircraft The fine design of the anti-heat insulation system under the design provides strong support.

Description of drawings

Fig. 1 is a flow chart of the steps of a ground prediction method for coupling effects of aerodynamic heat and material catalytic properties in an embodiment of the present invention;

Fig. 2 is the change history of heat flow on the surface of the terminal stagnation point material under two extreme material surface catalytic conditions (completely non-catalyzed, fully catalyzed) in the embodiment of the present invention;

Fig. 3 is the change history of heat flow on the surface of the ball head material under two extreme material surface catalytic conditions (completely non-catalyzed, fully catalyzed) in the embodiment of the present invention;

Fig. 4 is the variation history of the surface temperature at the stagnation point of the tip under two extreme material surface catalytic conditions (completely non-catalyzed and fully catalyzed) in the embodiment of the present invention.

detailed description

In order to make the purpose, technical solution and advantages of the present invention clearer, the following will further describe the public implementation manners of the present invention in detail with reference to the accompanying drawings.

Referring to FIG. 1 , it shows a flow chart of the steps of a ground prediction method for coupling effects of aerothermal and material catalytic properties in an embodiment of the present invention. In this embodiment, the ground prediction method of the coupling effect of aerothermal and material catalytic properties includes:

Step 101, analyzing the heat flow on the material surface under the condition of different material surface catalytic properties, and obtaining the surface heat flow under the condition of different catalytic properties on the material surface in the flying state.

In this embodiment, the numerical simulation of the high-temperature non-equilibrium three-dimensional flow field can be carried out by solving the chemical reaction flow N-S equation with component source terms, and the heat flow of the material surface under the condition of different material surface catalytic characteristics can be obtained based on the dimensionless form governing equation General expression:

Among them, q ₀ represents the material surface heat flow under the condition of different material surface catalytic properties, q represents the translational heat flow, q _v represents the vibration heat flow, k represents the translational heat transfer coefficient, T represents the translational temperature, n represents the normal coordinate of the material surface, k _V represents the thermal conductivity of vibration, T _V represents the vibration temperature, N _s represents the total number of components, the subscript i represents the parameter of the i-th component, ρ, M, h, D and c represent the air density and the molar mass of the component, respectively , enthalpy, diffusion coefficient and mass fraction, E _V represents the total vibrational energy of molecular components;

In this embodiment, since the surface reaction and the high-enthalpy dissociated gas flow are coupled through the chemical non-equilibrium boundary layer, the catalytic characteristic condition of the surface of the material can be As a boundary condition, it is brought into the control equation in the dimensionless form to obtain the surface heat flow under the condition of different catalytic properties on the surface of the material in the flight state.

Among them, for limited catalytic conditions, the conditions of material surface catalytic properties can be as follows:

in, is the surface recombination rate of the material, is the gas constant, and γ is the catalytic recombination coefficient of the material surface. Preferably, the dimensionless form governing equation can be as follows:

in,

u _j τ _xj ＝uτ _xx +vτ _xy +wτ _xz

Among them, u, v, and w are the velocity components in the three coordinate directions of x, y, and z, τ represents the shear stress, E represents the total translational energy of molecular components, w _i represents the chemical non-equilibrium source term, and w _V represents Vibration non-equilibrium energy source item, μ represents dynamic viscosity, q represents translational heat flow, p represents pressure, Indicates the divergence of velocity.

Step 102, performing a fitting analysis on the obtained surface heat flow under different catalytic properties on the material surface in the flying state, to obtain a functional relationship between the catalytic effect of the material surface and the change of the catalytic recombination coefficient of the material surface.

In this embodiment, the surface heat flow under the conditions of different catalytic properties of the material surface in the flight state is fitted and analyzed, and the following functional relationship is obtained:

q _h /q _f ＝φlog(γ)

In this embodiment, the ratio of q _h to q _f can be used to characterize the surface catalytic effect of the material. Among them, q _h represents the surface heat flow of the material under the partial catalytic characteristic condition, q _f represents the material surface heat flow under the complete catalytic characteristic condition, φ=q _f ^A , and A is a constant value coefficient.

In step 103, engineering calculations are performed on the surface heat flow of typical parts of the material by using engineering algorithms to obtain the fully catalyzed material surface heat flow of typical parts that changes with ballistic time.

In this embodiment, typical locations include, but are not limited to: stagnation point at the end, large area of the cone body, and leading edge of the wing. Different engineering algorithms can be used to solve the heat flow on the material surface for different typical parts. Calculated to obtain the heat flow on the surface of the material that is fully catalyzed by the terminal stagnation point as a function of the ballistic time. When the typical part is a ball head, the heat flow on the surface of the ball head material is calculated by using the "axisymmetric analogy" method based on accurate streamlines, and the heat flow on the surface of the material surface completely catalyzed by the ball head that changes with the ballistic time is obtained.

Step 104, according to the fully catalyzed material surface heat flow of the typical part that changes with the ballistic time and the actual material surface material catalytic composite coefficient of the typical part, combined with the above functional relationship, the partial catalyzed material surface heat flow of the typical part in the flight state is obtained Variations with trajectory.

In this embodiment, the fully catalyzed material surface heat flow and the real material surface material catalytic recombination coefficient of the typical site that changes with ballistic time can be substituted into the functional relationship q _h /q _f =φlog(γ) , to obtain the change history of heat flux on the surface of the partially catalyzed material surface with the ballistic trajectory in the typical part of the flight state. Fig. 2 shows the change history of heat flow on the surface of the terminal stagnation point material under two extreme material surface catalytic conditions (completely non-catalyzed and fully catalyzed) in the embodiment of the present invention. Fig. 3 shows the change history of heat flow on the surface of the ball head material under two extreme material surface catalytic conditions (completely non-catalyzed and fully catalyzed) in the embodiment of the present invention.

Step 105, using the method of heat transfer to analyze the change history of the surface heat flow of the partially catalyzed material in the typical part of the flight state with the ballistic trajectory, to obtain the internal temperature distribution of the typical part in the flight state under different surface catalytic characteristics, and the obtained Describe the change history of internal temperature with ballistic time.

In this embodiment, the obtained change history of heat flow on the surface of the partially catalyzed material surface in a typical part of the flight state with ballistics can be used as the boundary condition of the three-dimensional heat transfer governing equations, and the three-dimensional heat transfer governing equations are solved to obtain The internal temperature distribution of the typical part of the flight state under different surface catalytic properties, and the change history of the internal temperature with the ballistic time. Fig. 4 shows the change history of the surface temperature at the stagnation point of the tip under two extreme material surface catalytic conditions (completely non-catalyzed and fully catalyzed) in the embodiment of the present invention.

In summary, the present invention aims at the problem of the lack of coupling effect evaluation method of high-speed aircraft aerothermal and material catalytic properties, and proposes a method for evaluating the aerodynamic thermal properties of high-speed aircraft under the flight state through the aircraft flight state, aerodynamic shape and aircraft surface material catalytic properties. A method for predicting environmental and temperature field responses. Realized the ground prediction of the heat flow response history of the aircraft surface and the internal temperature response history of the aircraft under any surface catalytic properties, provided a feasible solution for the quantitative evaluation of the coupling effect of aerothermal and material catalytic properties of high-speed aircraft The fine design of the anti-heat insulation system under the design provides strong support.

The above description is only the best specific implementation mode of the present invention, but the scope of protection of the present invention is not limited thereto. Any person skilled in the art can easily conceive of changes or modifications within the technical scope disclosed in the present invention. Replacement should be covered within the protection scope of the present invention.

The content that is not described in detail in the specification of the present invention belongs to the well-known technology of those skilled in the art.

Claims (8)

1. A ground forecasting method for the coupling effect of aerodynamic heat and material catalytic properties, comprising:

analyzing the material surface heat flows under different material surface catalytic characteristic conditions to obtain the surface heat flows of the material surface under different catalytic characteristic conditions in a flight state;

fitting and analyzing the obtained surface heat flow of the material surface under different catalytic characteristic conditions in the flying state to obtain a functional relation of the material surface catalytic effect changing along with the material surface catalytic recombination coefficient;

performing engineering calculation on the surface heat flow of the material at the typical part by adopting an engineering algorithm to obtain the surface heat flow of the material which is completely catalyzed by the typical part and changes along with the ballistic time;

according to the complete catalytic material surface heat flow of the typical part changing along with the ballistic time and the actual material surface material catalytic recombination coefficient of the typical part, combining the functional relation to obtain the change process of the partial catalytic material surface heat flow of the typical part along with the ballistic under the flight state;

and analyzing the obtained change history of the surface heat flow of the material partially catalyzed by the typical part in the flying state along with the trajectory by adopting a thermal transmission method to obtain the internal temperature distribution of the typical part in the flying state under different surface catalysis characteristics and the change history of the internal temperature along with the trajectory time.

2. The method of claim 1, wherein analyzing the material surface heat flow under different material surface catalytic properties to obtain the surface heat flow under different catalytic properties of the material surface in flight comprises:

numerical simulation is carried out on the high-temperature unbalanced three-dimensional flow field by solving a chemical reaction flow N-S equation with component source terms, and a general expression of material surface heat flow under different material surface catalytic characteristic conditions is obtained based on a dimensionless form control equation:

$\left\{\begin{array}{c}{q}_0=q+q_V\\ q=k\frac{\∂T}{\∂n}+k_V\frac{\∂T_V}{\∂n}+\underset{i=1}{\overset{N_s}{\mathrm{\Σ}}}{\mathrm{\ρD}}_i{h}_i\frac{\∂c_i}{\∂n}\\ q_V=k_V\frac{\∂T_V}{\∂n}+\underset{M_i}{\mathrm{\Σ}}{\mathrm{\ρD}}_i{E}_{Vi}\frac{\∂c_i}{\∂n}\end{array}\right.$

wherein q is₀Representing the surface heat flow of the material under the condition of different surface catalytic characteristics of the material, q represents the translational heat flow, q represents the surface catalytic characteristics of the material_vRepresenting the vibration heat flow, k representing the translation heat conduction coefficient, T representing the translation temperature, n representing the normal coordinate of the material surface, k_VDenotes the coefficient of vibrational heat transfer, T_VDenotes the vibration temperature, N_sDenotes the total number of components, the index i denotes the parameter for the ith component, p, M, h, D and c denote the air density, the molar mass of the components, the enthalpy, the diffusion coefficient and the mass fraction, respectively, E_VRepresenting the total vibrational energy of the molecular components;

wherein, the material surface catalysis characteristic conditions are as follows:

wherein, is made of woodThe material surface recombination rate is increased, and the material surface recombination rate is increased,is a gas constant, and gamma is a catalytic recombination coefficient of the surface of the material;

subjecting the material to surface catalysisAnd substituting the control equation of the dimensionless form as a boundary condition to obtain the surface heat flow of the material surface under different catalytic characteristic conditions in the flight state.

3. The method according to claim 1 or 2, wherein the fitting analysis of the obtained surface heat flows of the material surface under different catalytic properties in the flight state to obtain a functional relationship of the material surface catalytic effect with the change of the material surface catalytic recombination coefficient comprises:

and performing fitting analysis on the surface heat flow of the material surface under different catalytic characteristic conditions in the flight state to obtain the following functional relationship:

q_h/q_f＝φlog(γ)

wherein q is_hHeat flow on the surface of the material, q, representing the condition of the catalytic properties of the part_fDenotes the heat flow on the surface of the material under the condition of complete catalytic properties,. phi. -. q_f ^AAnd A is a constant coefficient.

4. The method of claim 2, wherein the dimensionless form control equation is as follows:

$\frac{\∂Q}{\∂t}+\frac{\∂F}{\∂x}+\frac{\∂G}{\∂y}+\frac{\∂H}{\∂z}=\frac{1}{R_e}(\frac{\∂F_V}{\∂x}+\frac{\∂G_V}{\∂y}+\frac{\∂H_V}{\∂z})+W$

wherein,

$\begin{array}{cccc}Q=\left[\begin{array}{c}{\mathrm{\ρ}}_i\\ {\mathrm{\ρE}}_V\\ \mathrm{\ρ}\\ \mathrm{\ρ}u\\ \mathrm{\ρ}v\\ \mathrm{\ρ}w\\ \mathrm{\ρ}E\end{array}\right]& F=\left[\begin{array}{c}{\mathrm{\ρ}}_{i}u\\ {\mathrm{\ρE}}_{V}u\\ \mathrm{\ρ}u\\ {\mathrm{\ρu}}^2+p\\ \mathrm{\ρ}uv\\ \mathrm{\ρ}uw\\ \left(\mathrm{\ρ}E+p\right)u\end{array}\right]& G=\left[\begin{array}{c}{\mathrm{\ρ}}_{i}v\\ {\mathrm{\ρE}}_{V}v\\ \mathrm{\ρ}v\\ \mathrm{\ρ}uv\\ {\mathrm{\ρv}}^2+p\\ \mathrm{\ρ}vw\\ \left(\mathrm{\ρ}E+p\right)v\end{array}\right]& H=\left[\begin{array}{c}{\mathrm{\ρ}}_{i}w\\ {\mathrm{\ρE}}_{V}w\\ \mathrm{\ρ}w\\ \mathrm{\ρ}uw\\ \mathrm{\ρ}vw\\ {\mathrm{\ρw}}^2+p\\ \left(\mathrm{\ρ}E+p\right)w\end{array}\right]\end{array}$

$\begin{array}{cccc}{F}_V=\left[\begin{array}{c}{\mathrm{\ρD}}_i\frac{\∂c_i}{\∂x}\\ q_{Vx}\\ 0\\ {\mathrm{\τ}}_{xx}\\ {\mathrm{\τ}}_{xy}\\ {\mathrm{\τ}}_{xz}\\ q_x+u_j{\mathrm{\τ}}_{xj}\end{array}\right]& G_V=\left[\begin{array}{c}{\mathrm{\ρD}}_i\frac{\∂c_i}{\∂y}\\ q_{Vy}\\ 0\\ {\mathrm{\τ}}_{xy}\\ {\mathrm{\τ}}_{yy}\\ {\mathrm{\τ}}_{yz}\\ q_y+u_j{\mathrm{\τ}}_{yj}\end{array}\right]& H_V=\left[\begin{array}{c}{\mathrm{\ρD}}_i\frac{\∂c_i}{\∂z}\\ q_{Vz}\\ 0\\ {\mathrm{\τ}}_{xz}\\ {\mathrm{\τ}}_{yz}\\ {\mathrm{\τ}}_{zz}\\ q_z+u_j{\mathrm{\τ}}_{zj}\end{array}\right]& W=\left[\begin{array}{c}{w}_i\\ w_V\\ 0\\ 0\\ 0\\ 0\\ 0\end{array}\right]\end{array}$

$\begin{array}{cc}{u}_j{\mathrm{\τ}}_{xj}={\mathrm{u\τ}}_{xx}+{\mathrm{v\τ}}_{xy}+{\mathrm{w\τ}}_{xz}& {\mathrm{\τ}}_{xx}=-\frac{2}{3}\mathrm{\μ}(\▿\·\stackrel{\→}{V})+2\mathrm{\μ}\frac{\∂u}{\∂x}\end{array}$

$\begin{array}{cc}{\mathrm{\τ}}_{yy}=-\frac{2}{3}\mathrm{\μ}(\▿\·\stackrel{\→}{V})+2\mathrm{\μ}\frac{\∂v}{\∂y}& {\mathrm{\τ}}_{zz}=-\frac{2}{3}\mathrm{\μ}(\▿\·\stackrel{\→}{V})+2\mathrm{\μ}\frac{\∂w}{\∂z}\end{array}$

$\begin{array}{cccc}{\mathrm{\τ}}_{xy}=\mathrm{\μ}(\frac{\∂u}{\∂y}+\frac{\∂v}{\∂x})& {\mathrm{\τ}}_{yz}=\mathrm{\μ}(\frac{\∂w}{\∂y}+\frac{\∂v}{\∂z})& {\mathrm{\τ}}_{xz}=\mathrm{\μ}(\frac{\∂u}{\∂z}+\frac{\∂w}{\∂x})& \▿\·\stackrel{\→}{V}=\frac{\∂u}{\∂x}+\frac{\∂v}{\∂y}+\frac{\∂w}{\∂z};\end{array}$

wherein u, v and w are velocity components in x, y and z coordinate directions, tau represents shear stress, E represents total translational energy of molecular components, and w represents total translational energy of molecular components_iRepresenting a chemical non-equilibrium source term, w_VRepresents vibration unbalance energy source term, mu represents dynamic viscosity, q represents translational heat flow, p represents pressure,indicating the divergence of the velocity.

5. The method of claim 1, wherein the engineering calculation of the surface heat flow of the material at the representative site using an engineering algorithm to obtain the surface heat flow of the material fully catalyzed at the representative site as a function of ballistic time comprises:

and when the typical part is the end stagnation point, calculating the surface heat flow of the end stagnation point material by adopting a compressibility-corrected F-R formula calculation method to obtain the surface heat flow of the material which is completely catalyzed by the end stagnation point and changes along with the ballistic time.

6. The method of claim 1, wherein the engineering calculation of the surface heat flow of the material at the representative site using an engineering algorithm to obtain the surface heat flow of the material fully catalyzed at the representative site as a function of ballistic time comprises:

when the typical part is a ball head, calculating the surface heat flow of the ball head material by adopting an axis symmetry analogy method based on an accurate streamline to obtain the surface heat flow of the material completely catalyzed by the ball head along with the change of ballistic time.

7. The method according to claim 3, wherein the obtaining of the variation history of the surface heat flow of the material partially catalyzed by the typical site in the flying state along with the trajectory by combining the functional relationship between the surface heat flow of the material completely catalyzed by the typical site changing along with the trajectory time and the catalytic recombination coefficient of the surface heat flow of the actual material of the typical site comprises:

substituting the material surface heat flow completely catalyzed by the typical position changing along with the trajectory time and the real material surface material catalytic recombination coefficient of the typical position into a functional relation q_h/q_fThe change course of the heat flow of the material surface partially catalyzed by a typical part in a flight state along with the trajectory is obtained.

8. The method according to claim 1, wherein the obtained change history of the surface heat flow of the material partially catalyzed by the typical part under the flight condition along with the trajectory is analyzed by a thermal transmission method to obtain the internal temperature distribution of the typical part under the typical flight condition under different surface catalysis characteristics, and the change history of the internal temperature along with the trajectory time comprises:

and solving the three-dimensional heat transfer control equation set by taking the obtained change history of the surface heat flow of the material partially catalyzed by the typical part in the flying state along with the trajectory as a boundary condition of the three-dimensional heat transfer control equation set to obtain the internal temperature distribution of the typical part in the flying state under different surface catalysis characteristics and the change history of the internal temperature along with the trajectory time.