阅读说明：本技术 热沉推力室瞬态传热计算方法和系统 (Heat sink thrust chamber transient heat transfer calculation method and system ) 是由 金平 吕俊杰 戚亚群 刘炳阳 李睿智 蔡国飙 于 2021-07-23 设计创作，主要内容包括：本发明提供了一种热沉推力室瞬态传热计算方法和系统,包括：获取目标热沉推力室的初始热力学参数；基于初始热力学参数,对目标热沉推力室的燃气侧壁面温度进行迭代计算,得到目标燃气侧壁面温度；基于目标燃气侧壁面温度,得到目标热沉推力室的瞬态温度和热流密度。本发明缓解了现有技术中存在的缺乏关于液氧/甲烷发动机热沉推力室瞬态传热计算方法的技术问题。(The invention provides a heat sink thrust chamber transient heat transfer calculation method and a heat sink thrust chamber transient heat transfer calculation system, wherein the heat sink thrust chamber transient heat transfer calculation method comprises the following steps: acquiring initial thermodynamic parameters of a target heat sink thrust chamber; performing iterative calculation on the gas side wall surface temperature of the target heat sink thrust chamber based on the initial thermodynamic parameters to obtain the target gas side wall surface temperature; and obtaining the transient temperature and the heat flux density of the target heat sink thrust chamber based on the temperature of the side wall surface of the target gas. The invention solves the technical problem of the lack of a calculation method for transient heat transfer of the heat sink thrust chamber of the liquid oxygen/methane engine in the prior art.)

1. A heat sink thrust chamber transient heat transfer calculation method is characterized by comprising the following steps:

acquiring initial thermodynamic parameters of a target heat sink thrust chamber;

performing iterative calculation on the gas side wall surface temperature of the target heat sink thrust chamber based on the initial thermodynamic parameters to obtain a target gas side wall surface temperature;

obtaining the transient temperature and the heat flux density of the target heat sink thrust chamber based on the temperature of the side wall surface of the target gas;

the iterative computation includes:

setting an initial value of the temperature of the side wall surface of the fuel gas;

calculating the gas convection heat transfer coefficient of the target heat sink thrust chamber based on the initial thermodynamic parameter and the initial value;

based on the convective heat transfer coefficient of the fuel gas, obtaining an iterative value of the temperature of the side wall surface of the fuel gas by using a one-dimensional flat unsteady state heat transfer calculation method;

replacing the initial value with the iteration value to perform next iteration calculation until the difference value between the iteration value and the initial value is smaller than a preset value;

and taking the iteration value as the target gas side wall surface temperature.

2. The method of claim 1, wherein the initial thermodynamic parameters comprise: the heat sink thrust chamber comprises an inner wall initial temperature, a gas pressure, a gas specific heat, a gas viscosity, a Plantt number, a characteristic speed, a specific heat ratio, a Mach number, a heat diffusion coefficient of an inner wall, a heat conductivity coefficient of the inner wall, a material density of the inner wall and geometric parameters of the target heat sink thrust chamber.

3. The method of claim 1, wherein calculating the gas convective heat transfer coefficient of the target heat sink thrust cell based on the initial thermodynamic parameter and the initial value comprises:

calculating the convective heat transfer coefficient of the fuel gas by the following calculation formula:

wherein the content of the first and second substances,h_gc is constant coefficient, D is the convective heat transfer coefficient of the fuel gas_tIs the diameter of the throat, c_pIs specific heat of fuel gas, mu is viscosity of fuel gas, Pr is prandtl number, p_cIs the pressure of the thrust chamber, c^*For characteristic velocity, R is the throat radius of curvature, A_tIs the nozzle throat area, A is the local interface area, sigma is a dimensionless factor, T_wgIs the initial value, T_stThe near-wall gas temperature, gamma is the specific heat ratio, and Ma is the Mach number.

4. The method of claim 3, wherein the target heat sink thrust chamber is a liquid oxygen/methane engine heat sink thrust chamber; the method further comprises the following steps: correcting the constant coefficient by the following equation: c 'is 1.5C, where C' is a constant coefficient after correction.

5. The method of claim 1, wherein obtaining an iterative value of the gas side wall surface temperature based on the gas convective heat transfer coefficient by using a one-dimensional flat-plate unsteady heat transfer calculation method comprises:

calculating the iteration value by the following calculation formula:

T(η，t)＝[A₁(exp(-μ_nF₀cos(μ_nη)))](T₀-T_st)+T_st

wherein A is₁＝1.0101+0.2575×(1-exp(-0.4271B_i))， T (η, T) is the iteration value, A1 is the first fitting coefficient, μ_nIs a characteristic value, F₀Is Fourier number, eta is axial position, T₀Is the initial temperature of the inner wall, T_stNear wall gas temperature, B_iIs the pile number, h_gAnd delta is the thickness of the inner wall, alpha is the thermal diffusion coefficient, and t is the time.

6. The method of claim 5, wherein deriving the transient temperature and heat flux density of the target heat sink thrust chamber based on the target gas side wall temperature comprises:

calculating the pythagorean number and the fourier number based on the target gas side wall temperature;

and obtaining the transient temperature and the heat flux density of the target heat sink thrust chamber by using a one-dimensional flat plate unsteady state heat transfer calculation method based on the pythoready number and the Fourier number.

7. The method of claim 6, further comprising:

calculating the heat flow density by the following calculation:

wherein the content of the first and second substances, is the heat flux density, B₁Is the second fitting coefficient, rho is the density of the inner wall material, c_p' is the specific heat of the inner wall.

8. A heat sink thrust chamber transient heat transfer computing system, comprising: the device comprises an acquisition module, an iteration module and a calculation module; wherein the content of the first and second substances,

the acquisition module is used for acquiring initial thermodynamic parameters of the target heat sink thrust chamber;

the iteration module is used for carrying out iterative calculation on the gas side wall surface temperature of the target heat sink thrust chamber based on the initial thermodynamic parameters to obtain a target gas side wall surface temperature;

the calculation module is used for obtaining the transient temperature and the heat flux density of the target heat sink thrust chamber based on the temperature of the side wall surface of the target gas;

the iteration module is further configured to:

setting an initial value of the temperature of the side wall surface of the fuel gas;

calculating the gas convection heat transfer coefficient of the target heat sink thrust chamber based on the initial thermodynamic parameter and the initial value;

based on the convective heat transfer coefficient of the fuel gas, obtaining an iterative value of the temperature of the side wall surface of the fuel gas by using a one-dimensional flat unsteady state heat transfer calculation method;

replacing the initial value with the iteration value to perform next iteration calculation until the difference value between the iteration value and the initial value is smaller than a preset value;

and taking the iteration value as the target gas side wall surface temperature.

9. An electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, wherein the steps of the method of any of the preceding claims 1 to 7 are implemented when the computer program is executed by the processor.

10. A computer-readable medium having non-volatile program code executable by a processor, wherein the program code causes the processor to perform the method of any of claims 1-7.

Technical Field

The invention relates to the technical field of rocket thrust chamber heat transfer calculation, in particular to a heat sink thrust chamber transient heat transfer calculation method and system.

Background

The heat sink thrust chamber is widely applied to a scale test, and the processes of propellant injection, mixing, combustion and the like can be researched. Compared with a regenerative cooling thrust chamber, the regenerative cooling thrust chamber is different in that no cooling channel is arranged, so that the system is simple, the operation is convenient, the test period is short, the expenditure is saved, and the normal operation of the researched subject can be ensured. At present, research on a transient heat transfer calculation method of a liquid oxygen/methane engine heat sink thrust chamber is lacked.

Disclosure of Invention

In view of the above, the present invention provides a method and a system for calculating the transient heat transfer of a heat sink thrust chamber, so as to alleviate the technical problem of the prior art that the method for calculating the transient heat transfer of the heat sink thrust chamber of a liquid oxygen/methane engine is lacked.

In a first aspect, an embodiment of the present invention provides a heat sink thrust chamber transient heat transfer calculation method, including: acquiring initial thermodynamic parameters of a target heat sink thrust chamber; performing iterative calculation on the gas side wall surface temperature of the target heat sink thrust chamber based on the initial thermodynamic parameters to obtain a target gas side wall surface temperature; obtaining the transient temperature and the heat flux density of the target heat sink thrust chamber based on the temperature of the side wall surface of the target gas; the iterative computation includes: setting an initial value of the temperature of the side wall surface of the fuel gas; calculating the gas convection heat transfer coefficient of the target heat sink thrust chamber based on the initial thermodynamic parameter and the initial value; based on the convective heat transfer coefficient of the fuel gas, obtaining an iterative value of the temperature of the side wall surface of the fuel gas by using a one-dimensional flat unsteady state heat transfer calculation method; replacing the initial value with the iteration value to perform next iteration calculation until the difference value between the iteration value and the initial value is smaller than a preset value; and taking the iteration value as the target gas side wall surface temperature.

Further, the initial thermodynamic parameters include: the heat sink thrust chamber comprises an inner wall initial temperature, a gas pressure, a gas specific heat, a gas viscosity, a Plantt number, a characteristic speed, a specific heat ratio, a Mach number, a heat diffusion coefficient of an inner wall, a heat conductivity coefficient of the inner wall, a material density of the inner wall and geometric parameters of the target heat sink thrust chamber.

Further, calculating a gas convective heat transfer coefficient of the target heat sink thrust chamber based on the initial thermodynamic parameter and the initial value, comprising: calculating the convective heat transfer coefficient of the fuel gas by the following calculation formula:wherein the content of the first and second substances, h_gc is constant coefficient, D is the convective heat transfer coefficient of the fuel gas_tIs the diameter of the throat, c_pIs specific heat of fuel gas, mu is viscosity of fuel gas, Pr is prandtl number, p_cIs the pressure of the thrust chamber, c^*For characteristic velocity, R is the throat radius of curvature, A_tIs the nozzle throat area, A is the local interface area, sigma is a dimensionless factor, T_wgIs the initial value, T_stThe near-wall gas temperature, gamma is the specific heat ratio, and Ma is the Mach number.

Further, the target heat sink thrust chamber is a liquid oxygen/methane engine heat sink thrust chamber; the method further comprises the following steps: correcting the constant coefficient by the following equation: c 'is 1.5C, where C' is a constant coefficient after correction.

Further, based on the convective heat transfer coefficient of the gas, obtaining an iterative value of the gas side wall surface temperature by using a one-dimensional flat unsteady state heat transfer calculation method, comprising: calculating the iteration value by the following calculation formula: t (eta, T) ═ A₁(exp(-μ_nF₀cos(μ_nη)))](T₀-T_st)+T_st(ii) a Wherein A is₁＝1.0101+0.2575×(1-exp(-0.4271B_i))， T (η, T) is the iteration value, A₁Is the first fitting coefficient, mu_nIs a characteristic value, F₀Is Fourier number, eta is axial position, T₀Is the initial temperature of the inner wall, T_stNear wall gas temperature, B_iIs the pile number, h_gAnd delta is the thickness of the inner wall, alpha is the thermal diffusion coefficient, and t is the time.

Further, obtaining the transient temperature and the heat flux density of the target heat sink thrust chamber based on the target gas side wall surface temperature comprises: calculating the pythagorean number and the fourier number based on the target gas side wall temperature; and obtaining the transient temperature and the heat flux density of the target heat sink thrust chamber by using a one-dimensional flat plate unsteady state heat transfer calculation method based on the pythoready number and the Fourier number.

Further, the method further comprises: calculating the heat flow density by the following calculation:wherein the content of the first and second substances, is the heat flux density, B₁Is the second fitting coefficient, rho is the density of the inner wall material, c_p' is the specific heat of the inner wall.

In a second aspect, embodiments of the present invention further provide a heat sink thrust chamber transient heat transfer computing system, including: the device comprises an acquisition module, an iteration module and a calculation module; the acquisition module is used for acquiring initial thermodynamic parameters of the target heat sink thrust chamber; the iteration module is used for carrying out iterative calculation on the gas side wall surface temperature of the target heat sink thrust chamber based on the initial thermodynamic parameters to obtain a target gas side wall surface temperature; the calculation module is used for obtaining the transient temperature and the heat flux density of the target heat sink thrust chamber based on the temperature of the side wall surface of the target gas; the iteration module is further configured to: setting an initial value of the temperature of the side wall surface of the fuel gas; calculating the gas convection heat transfer coefficient of the target heat sink thrust chamber based on the initial thermodynamic parameter and the initial value; based on the convective heat transfer coefficient of the fuel gas, obtaining an iterative value of the temperature of the side wall surface of the fuel gas by using a one-dimensional flat unsteady state heat transfer calculation method; replacing the initial value with the iteration value to perform next iteration calculation until the difference value between the iteration value and the initial value is smaller than a preset value; and taking the iteration value as the target gas side wall surface temperature.

In a third aspect, an embodiment of the present invention further provides an electronic device, which includes a memory, a processor, and a computer program stored in the memory and executable on the processor, where the processor implements the steps of the method according to the first aspect when executing the computer program.

In a fourth aspect, the present invention further provides a computer-readable medium having non-volatile program code executable by a processor, where the program code causes the processor to execute the method according to the first aspect.

The invention provides a heat sink thrust chamber transient heat transfer calculation method and a heat sink thrust chamber transient heat transfer calculation system, wherein the heat sink thrust chamber transient heat transfer calculation method comprises the following steps: acquiring initial thermodynamic parameters of a target heat sink thrust chamber; performing iterative calculation on the gas side wall surface temperature of the target heat sink thrust chamber based on the initial thermodynamic parameters to obtain the target gas side wall surface temperature; and obtaining the transient temperature and the heat flux density of the target heat sink thrust chamber based on the temperature of the side wall surface of the target gas. The invention calculates the one-dimensional transient heat transfer of the heat sink thrust chamber by the one-dimensional flat unsteady heat transfer calculation method, so that the calculation process is simple, convenient and accurate, and the technical problem of the lack of the calculation method of the transient heat transfer of the heat sink thrust chamber of the liquid oxygen/methane engine in the prior art is solved.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.

Fig. 1 is a flowchart of a heat sink thrust chamber transient heat transfer calculation method according to an embodiment of the present invention;

FIG. 2 is a flow chart of an iterative calculation provided by an embodiment of the present invention;

FIG. 3 is a schematic diagram of a one-dimensional flat plate heat transfer model according to an embodiment of the present invention;

fig. 4 is a schematic diagram of a heat sink thrust chamber transient heat transfer computing system according to an embodiment of the present invention.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The first embodiment is as follows:

fig. 1 is a flowchart of a heat sink thrust chamber transient heat transfer calculation method according to an embodiment of the present invention. As shown in fig. 1, the method specifically includes the following steps:

step S102, obtaining initial thermodynamic parameters of the target heat sink thrust chamber.

Optionally, the target heat sink thrust chamber comprises: liquid oxygen/methane engine heat sink thrust chamber. The initial thermodynamic parameters include: the gas temperature and the gas pressure obtained through measurement, and the specific heat, the viscosity, the Prandtl number, the characteristic speed, the specific heat ratio and the Mach number of the gas obtained through calculation; and the initial temperature of the inner wall of the target heat sink thrust chamber, the heat diffusion coefficient of the inner wall, the heat conductivity coefficient of the inner wall, the material density of the inner wall and the geometric parameters of the target heat sink thrust chamber.

And step S104, performing iterative calculation on the gas side wall surface temperature of the target heat sink thrust chamber based on the initial thermodynamic parameters to obtain the target gas side wall surface temperature.

And step S106, obtaining the transient temperature and the heat flux density of the target heat sink thrust chamber based on the temperature of the side wall surface of the target gas.

Specifically, fig. 2 is a flowchart of an iterative computation provided according to an embodiment of the present invention. As shown in fig. 2, step S104 further includes the following steps:

step S1041, setting an initial value of the temperature of the side wall surface of the fuel gas;

step S1042, calculating the gas convection heat transfer coefficient of the target heat sink thrust chamber based on the initial thermodynamic parameters and the initial values;

optionally, in the embodiment of the present invention, the modified bartz formula is used to calculate the convective heat transfer coefficient of the fuel gas;

step S1043, obtaining an iterative value of the gas side wall surface temperature by using a one-dimensional flat plate unsteady state heat transfer calculation method based on the gas convective heat transfer coefficient;

step S1044, replacing the initial value with an iteration value to perform next iteration calculation until the difference value between the iteration value and the initial value is less than a preset value;

in step S1045, the iteration value is set as the target gas side wall temperature.

The invention provides a heat sink thrust chamber transient heat transfer calculation method, which is characterized in that a one-dimensional transient heat transfer calculation method of a heat sink thrust chamber is adopted to calculate the one-dimensional transient heat transfer of the heat sink thrust chamber, so that the calculation process is simple, convenient and accurate, and the technical problem of the lack of the heat sink thrust chamber transient heat transfer calculation method of a liquid oxygen/methane engine in the prior art is solved.

Optionally, in this embodiment of the present invention, in step S1042, the convective heat transfer coefficient of the fuel gas is calculated by the following calculation formula:

wherein the content of the first and second substances,

h_gis the convective heat transfer coefficient of fuel gas, C is constant coefficient, D_tIs the diameter of the throat, c_pIs specific heat of fuel gas, mu is viscosity of fuel gas, Pr is prandtl number, p_cIs the pressure of the thrust chamber, c^*For characteristic velocity, R is the throat radius of curvature, A_tIs the nozzle throat area, A is the local interface area, sigma is a dimensionless factor, T_wgIs an initial value, T_stThe near-wall gas temperature, gamma is the specific heat ratio, and Ma is the Mach number.

In an embodiment of the invention, the target heat sink thrust chamber is a liquid oxygen/methane engine heat sink thrust chamber. The value of the constant coefficient C in the formula can be influenced by factors such as the size of the model, working conditions and the like, and the constant coefficient C is generally corrected in engineering so that the one-dimensional heat transfer calculation result is more consistent with the test result. Therefore, the embodiment of the present invention corrects the constant coefficient C in combination with actual test data, specifically, corrects the constant coefficient by the following equation: c 'is 1.5C, where C' is a constant coefficient after correction. Optionally, in an embodiment of the present invention, the value C' is 1.5C — 0.039.

The wall of the thrust chamber is suitable for a one-dimensional flat plate heat transfer model, namely, the temperature only changes along the thickness direction. FIG. 3 is a schematic diagram of a one-dimensional flat plate heat transfer model according to an embodiment of the present invention. As shown in FIG. 3, the infinite plate has an inner wall thickness of δ and an internal initial temperature of T₀At the initial instant, it is placed at a temperature T_stOne side of the fuel gas is heated, and the other side is a heat insulation wall surface. The temperature of the inner wall at different depths and different moments can be obtained by using a Camp approximate fitting formula method.

Specifically, in step S1043 of the embodiment of the present invention, the iteration value is calculated by the following calculation formula:

T(η,t)＝[A₁(exp(-μ_nF₀cos(μ_nη)))](T₀-T_st)+T_st

wherein the content of the first and second substances,

A₁＝1.0101+0.2575×(1-exp(-0.4271B_i))

t (η, T) is an iteration value, A₁Is the first fitting coefficient, mu_nIs a characteristic value, F₀Is Fourier number, eta is axial position, T₀Is the initial temperature of the inner wall, T_stNear wall gas temperature, B_iIs the pile number, h_gThe convective heat transfer coefficient of the fuel gas, delta the thickness of the inner wall, alpha the thermal diffusion coefficient and t the time.

Optionally, step S106 further includes the following steps:

step S1061, calculating a pythagorean number and a Fourier number based on the temperature of the side wall surface of the target gas;

and S1062, based on the pythoready number and the Fourier number, obtaining the transient temperature and the heat flux density of the target heat sink thrust chamber by using a one-dimensional flat plate unsteady state heat transfer calculation method.

Specifically, the heat flow density is calculated by the following calculation formula:

wherein the content of the first and second substances,

is the heat flow density, B₁Is the second fitting coefficient, rho is the density of the inner wall material, c_p' is the specific heat of the inner wall.

In the embodiment of the invention, firstly, the target gas side wall surface temperature T is calculated in an iterative mode through the relationship between the convective heat transfer coefficient and the gas side wall surface temperature_wgThen T is added_wgSubstituting into a one-dimensional flat plate heat transfer model to obtain an intermediate variable B_iAnd F₀And finally substituting the intermediate variable into a calculation formula of the temperature of the inner wall at different depths and different moments in the one-dimensional flat plate heat transfer model to calculate the transient temperature of the target heat sink thrust chamber, and calculating the heat flux density of the target heat sink thrust chamber through a heat flux density calculation formula.

The heat sink thrust chamber transient heat transfer calculation method provided by the embodiment of the invention solves the problem of transient heat transfer calculation of the heat sink thrust chamber of the liquid oxygen/methane engine, and the one-dimensional transient heat transfer of the heat sink thrust chamber is calculated by a one-dimensional flat unstable heat transfer calculation method, so that the calculation process is simple, convenient and accurate, and has strong engineering practice significance; the method provided by the embodiment of the invention establishes the relationship among the gas temperature, the wall temperature and the heat flow density, can realize mutual pushing among the gas temperature, the wall temperature and the heat flow density, and has important significance for understanding the heat transfer characteristics of the heat sink thrust chamber and obtaining the temperature and heat flow distribution information.

Example two:

fig. 4 is a schematic diagram of a heat sink thrust chamber transient heat transfer computing system provided in accordance with an embodiment of the present invention. As shown in fig. 4, the system includes: an acquisition module 10, an iteration module 20 and a calculation module 30.

Specifically, the obtaining module 10 is configured to obtain an initial thermodynamic parameter of the target heat sink thrust chamber.

And the iteration module 20 is configured to perform iterative computation on the gas side wall surface temperature of the target heat sink thrust chamber based on the initial thermodynamic parameter to obtain a target gas side wall surface temperature.

And the calculation module 30 is used for obtaining the transient temperature and the heat flux density of the target heat sink thrust chamber based on the temperature of the side wall surface of the target gas.

Specifically, the iteration module 20 is further configured to: setting an initial value of the temperature of the side wall surface of the fuel gas; calculating the gas convection heat transfer coefficient of the target heat sink thrust chamber based on the initial thermodynamic parameters and the initial values; based on the convective heat transfer coefficient of the fuel gas, obtaining an iterative value of the temperature of the side wall surface of the fuel gas by using a one-dimensional flat unsteady state heat transfer calculation method; replacing the initial value with an iteration value to perform next iteration calculation until the difference value between the iteration value and the initial value is smaller than a preset value; and taking the iteration value as the target gas side wall surface temperature.

The invention provides a heat sink thrust chamber transient heat transfer calculation system, which is characterized in that a one-dimensional transient heat transfer calculation method of a heat sink thrust chamber is adopted to calculate the one-dimensional transient heat transfer of the heat sink thrust chamber, so that the calculation process is simple, convenient and accurate, and the technical problem of the lack of the heat sink thrust chamber transient heat transfer calculation method of a liquid oxygen/methane engine in the prior art is solved.

Specifically, the iteration module 20 calculates the convective heat transfer coefficient of the fuel gas by the following calculation formula:

wherein the content of the first and second substances,

h_gis the convective heat transfer coefficient of fuel gas, C is constant coefficient, D_tIs the diameter of the throat, c_pIs specific heat of fuel gas, mu is viscosity of fuel gas, Pr is prandtl number, p_cIs the pressure of the thrust chamber, c^*For characteristic velocity, R is the throat radius of curvature, A_tIs the nozzle throat area, A is the local interface area, and σ isDimensional factor, T_wgIs an initial value, T_stThe near-wall gas temperature, gamma is the specific heat ratio, and Ma is the Mach number.

Optionally, the constant coefficient is corrected by the following equation: c 'is 1.5C, where C' is a constant coefficient after correction. Optionally, in an embodiment of the present invention, the value C' is 1.5C — 0.039.

Specifically, the iteration module 20 further calculates an iteration value by the following calculation formula:

T(η,t)＝[A₁(exp(-μ_nF₀cos(μ_nη)))](T₀-T_st)+T_st

wherein the content of the first and second substances,

A₁＝1.0101+0.2575×(1-exp(-0.4271B_i))

t (η, T) is an iteration value, A₁Is the first fitting coefficient, mu_nIs a characteristic value, F₀Is Fourier number, eta is axial position, T₀Is the initial temperature of the inner wall, T_stNear wall gas temperature, B_iIs the pile number, h_gThe convective heat transfer coefficient of the fuel gas, delta the thickness of the inner wall, alpha the thermal diffusion coefficient and t the time.

Optionally, the calculation module 30 is further configured to: calculating a pythagorean number and a fourier number based on the temperature of the side wall surface of the target gas; and based on the pythoready number and the Fourier number, obtaining the transient temperature and the heat flux density of the target heat sink thrust chamber by using a one-dimensional flat unstable heat transfer calculation method.

Specifically, the calculation module 30 calculates the heat flux density by the following calculation formula:

wherein the content of the first and second substances,

is the heat flow density, B₁Is the second fitting coefficient, rho is the density of the inner wall material, c_p' is the specific heat of the inner wall.

The embodiment of the present invention further provides an electronic device, which includes a memory, a processor, and a computer program stored in the memory and capable of running on the processor, and when the processor executes the computer program, the steps of the method in the first embodiment are implemented.

The embodiment of the invention also provides a computer readable medium with a non-volatile program code executable by a processor, wherein the program code causes the processor to execute the method in the first embodiment.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.