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

Abstract

The invention discloses a kind of Aerodynamic Heating and the ground predicting method of material catalysis characteristics coupling effect, including：The material surface hot-fluid under the conditions of different materials surface catalysis characteristic is analyzed using theoretical method；The functional relation that material surface catalytic effect changes with material surface catalysis recombination coefficient is set up according to analysis result；Engineering evaluation is carried out to typical parts thermal environment based on state of flight and aerodynamic configuration, typical parts thermal environment engineering calculation result is combined with material surface catalytic effect with the functional relation that material surface catalysis recombination coefficient changes, the indication of aircraft surface thermal fluid activity course under state of flight is realized；Using thermal conduction study method, the indication of aircraft interior temperature-responsive course under state of flight is realized.The accurate description of the coupling effect to Aerodynamic Heating Yu material catalysis characteristics is realized by the present invention, for the anti-insulation system design minute design under Aerodynamic Heating and the effect of material catalysis characteristics coupling effect provides powerful support.

Description

Ground prediction method for coupling effect of aerodynamic heat and material catalytic characteristics

Technical Field

The invention belongs to the technical field of aircraft testing, and particularly relates to a ground prediction method for a coupling effect of aerodynamic heat and material catalytic characteristics.

Background

When the aircraft flies at high speed, a strong bow shock wave is formed around the head. Due to viscous dissipation effects and the intense compression of the shock wave, a portion of the large kinetic energy loss is converted into the internal energy of the gas within the shock layer. The incoming air is heated to thousands of degrees or even tens of thousands of degrees to form a high-temperature gas layer when passing through the shock wave, the translational, rotational and vibration freedom degrees of gas molecules are excited, dissociated and even ionized by the energy action, and the phenomena of excitation of vibration energy, molecular dissociation, atomic recombination, chemical reaction among components, ionization and the like generated at high temperature and the influence phenomena on flow field parameters are collectively called as high-temperature real gas effect. The high-temperature real gas effect not only generates serious pneumatic heating on the surface of the aircraft, but also generates strong nonlinear coupling effect with the heat-proof material on the surface of the aircraft body. The recombination rate of the dissociated atoms on the surface of the heat-proof material directly influences the chemical heating of the chemical non-equilibrium shock wave layer on the surface of the heat-proof material on the surface of the organism.

Due to the lack of deep analysis and related data in the traditional design, the coupling effect of aerodynamic heat and material catalysis characteristics cannot be accurately described, so that the design of a thermal protection system is conservative, and great difficulty is brought to the optimal design of the thermal protection system.

Disclosure of Invention

The technical problem of the invention is solved: the method overcomes the defects of the prior art, provides a ground prediction method of the coupling effect of the catalytic characteristics of the aerodynamic heat and the material, aims to accurately describe the coupling effect of the catalytic characteristics of the aerodynamic heat and the material, and provides powerful support for the design refinement of the heat insulation prevention system under the effect of the coupling effect of the catalytic characteristics of the aerodynamic heat and the material.

In order to solve the technical problem, the invention discloses a ground prediction method for a coupling effect of aerodynamic heat and material catalytic characteristics, which comprises the following steps:

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.

In the above ground prediction method of coupling effect between aerodynamic heat and material catalytic characteristics, the analyzing the surface heat flow of the material under different conditions of the material surface catalytic characteristics to obtain the surface heat flow of the material surface under different conditions of the material surface catalytic characteristics in a flight state includes:

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:

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 the recombination rate of the surface of the material,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.

In the above ground prediction method of coupling effect between aerodynamic heat and material catalytic characteristics, the fitting analysis of the obtained surface heat flow of the material surface under different catalytic characteristics in the flight state to obtain a functional relationship of the material surface catalytic effect varying with the material surface catalytic recombination coefficient includes:

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.

In the above ground prediction method of the coupling effect of the aerodynamic heat and the material catalytic property, the dimensionless formal control equation is as follows:

wherein,

u_jτ_xj＝uτ_xx+vτ_xy+wτ_xz

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.

In the above ground prediction method of coupling effect between aerodynamic heat and material catalytic characteristics, the engineering calculation is performed on the material surface heat flow of the typical location by using an engineering algorithm to obtain the material surface heat flow completely catalyzed by the typical location changing with ballistic time, and the method includes:

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.

In the above ground prediction method of coupling effect between aerodynamic heat and material catalytic characteristics, the engineering calculation is performed on the material surface heat flow of the typical location by using an engineering algorithm to obtain the material surface heat flow completely catalyzed by the typical location changing with ballistic time, and the method includes:

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.

In the above ground prediction method for the coupling effect of aerodynamic heat and material catalytic characteristics, the obtaining a variation history of the material surface heat flow partially catalyzed by the typical part in the flight state along with the trajectory according to the material surface heat flow completely catalyzed by the typical part along with the trajectory time and the actual material surface material catalytic recombination coefficient of the typical part by combining the above functional relationship includes:

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.

In the above ground prediction method for the coupling effect of aerodynamic heat and material catalytic characteristics, the analysis of the variation history of the surface heat flow of the material partially catalyzed by the typical part under the flight condition with the trajectory by using the thermal conductivity method obtains the internal temperature distribution of the typical part under the flight condition under different surface catalytic characteristics, and the variation history of the internal temperature 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.

The invention has the following advantages:

the invention provides a method for predicting the response of a high-speed aircraft aerodynamic thermal environment and a temperature field in a flight state through the flight state, the aerodynamic shape and the catalytic characteristics of the surface material of the aircraft, aiming at the problem of lacking a coupling effect evaluation method of the aerodynamic thermal and material catalytic characteristics of the high-speed aircraft. The ground prediction of the aircraft surface heat flow response course and the aircraft internal temperature response course under any surface catalysis characteristic is realized, a feasible scheme is provided for quantitative evaluation of the coupling effect of the aerodynamic heat and material catalysis characteristic of the high-speed aircraft, and powerful support is provided for the design refinement of the heat insulation prevention system under the effect of the coupling effect of the aerodynamic heat and material catalysis characteristic.

Drawings

FIG. 1 is a flow chart illustrating the steps of a method for ground forecasting the coupling effect of aerodynamic heat and material catalytic properties in an embodiment of the present invention;

FIG. 2 is a graph showing the heat flow history of the surface of the end-stop material under two extreme material surface catalysis conditions (completely non-catalytic and completely catalytic) in an example of the present invention;

FIG. 3 is the heat flow change course of the ball head material surface under two limiting material surface catalysis conditions (completely non-catalytic and completely catalytic) in the embodiment of the present invention;

FIG. 4 is a graph of the temperature history of the end-stop surface under two limiting material surface catalysis conditions (completely non-catalyzed, completely catalyzed) in an example of the present invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, common embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

Referring to FIG. 1, a flow chart of steps of a ground predictive method of aerodynamic thermal to material catalytic property coupling effects in an embodiment of the invention is shown. In this embodiment, the method for ground prediction of the coupling effect of the aerodynamic heat and the catalytic property of the material comprises the following steps:

step 101, analyzing the material surface heat flow under different material surface catalysis characteristic conditions to obtain the surface heat flow under different catalysis characteristic conditions of the material surface in a flight state.

In this embodiment, the numerical simulation of the high-temperature unbalanced three-dimensional flow field can be performed by solving the chemical reaction flow N-S equation with the 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 control equation:

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;

in this embodiment, due to the surfaceThe reaction and the high enthalpy dissociation gas flow are mutually coupled through a chemical non-equilibrium boundary layer, so that the material can be subjected to surface catalysis characteristic conditionsAnd 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.

Wherein, for the limited catalysis condition, the material surface catalysis characteristic condition can be as follows:

wherein, is the recombination rate of the surface of the material,is the gas constant, and gamma is the catalytic recombination coefficient of the material surface. Preferably, the dimensionless formal control equation may be as follows:

wherein,

u_jτ_xj＝uτ_xx+vτ_xy+wτ_xz

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.

102, performing fitting analysis on the obtained surface heat flows of the material surface under different catalytic characteristic conditions in the flight state to obtain a functional relation of the material surface catalytic effect changing along with the material surface catalytic recombination coefficient.

In this embodiment, fitting analysis is performed on the surface heat flows of the material surface in the flight state under different catalytic property conditions, so as to obtain the following functional relationship:

q_h/q_f＝φlog(γ)

in this embodiment, q may be used_hAnd q is_fThe ratio of (A) to (B) characterizes the catalytic effect of the material surface. 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.

And 103, performing engineering calculation on the surface heat flow of the material of 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.

In this embodiment, typical locations include, but are not limited to: end stagnation points, large cone area, wing leading edges and the like. Different typical parts can be solved by adopting different engineering algorithms, for example, when the typical part is a terminal stagnation point, the surface heat flow of the terminal stagnation point material is calculated by adopting a compressibility-corrected F-R formula calculation method, so that the surface heat flow of the material completely catalyzed by the terminal stagnation point changing along with the ballistic time is obtained. 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.

And step 104, obtaining the variation process of the heat flow of the material surface catalyzed by the typical part partially in the flight state along with the trajectory by combining the functional relation according to the heat flow of the material surface completely catalyzed by the typical part along with the trajectory time and the catalytic recombination coefficient of the actual material surface of the typical part.

In this embodiment, the material surface heat flow completely catalyzed by the typical site changing with ballistic time and the real material surface material catalytic recombination coefficient of the typical site can be substituted into the 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. Referring to fig. 2, the heat flow history of the surface of the end-stop material under two extreme material surface catalysis conditions (completely non-catalytic and completely catalytic) in the example of the present invention is shown. Fig. 3 shows the heat flow history on the surface of the ball head material under two limiting material surface catalysis conditions (completely non-catalytic and completely catalytic) in the embodiment of the invention.

And 105, 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, and obtaining 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.

In this embodiment, the obtained change history of the surface heat flow of the material partially catalyzed by the typical part in the flight state along with the trajectory can be used as a boundary condition of a three-dimensional heat transfer control equation system, and the three-dimensional heat transfer control equation system is solved to obtain the internal temperature distribution of the typical part in the flight state under different surface catalysis characteristics and the change history of the internal temperature along with the trajectory time. Referring to FIG. 4, the temperature history of the end-stop surface under two limiting material surface catalysis conditions (completely non-catalyzed, completely catalyzed) in the example of the present invention is shown.

In conclusion, the invention provides a method for predicting the response of the aerodynamic heating environment and the temperature field of the high-speed aircraft in the flight state through the flight state, the aerodynamic shape and the catalytic characteristics of the surface material of the aircraft, aiming at the problem of the lack of the method for evaluating the coupling effect of the aerodynamic heating and the catalytic characteristics of the material of the high-speed aircraft. The ground prediction of the aircraft surface heat flow response course and the aircraft internal temperature response course under any surface catalysis characteristic is realized, a feasible scheme is provided for quantitative evaluation of the coupling effect of the aerodynamic heat and material catalysis characteristic of the high-speed aircraft, and powerful support is provided for the design refinement of the heat insulation prevention system under the effect of the coupling effect of the aerodynamic heat and material catalysis characteristic.

The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.

Those skilled in the art will appreciate that the invention may be practiced without these specific details.

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.