Surface catalysis and active injection coupled aerodynamic thermal environment prediction method and device

Abstract

The invention provides a surface catalysis and active injection coupled aerodynamic thermal environment prediction method, device, equipment and medium, and the method comprises the steps: calculating the surface catalysis reaction generation rate according to the temperature, pressure and component mass fraction of the surface of an aircraft; the surface component mass fraction gradient is calculated according to the surface active injection mass flow rate and the surface catalytic reaction generation rate; and according to the surface mass flow rate, the temperature and the component mass fraction gradient, the surface heat flow under the surface catalysis and active injection coupling effect is determined. The method solves the problem that an existing thermal environment prediction technology can only consider the surface catalysis effect or the surface active injection effect independently, improves the prediction precision of the surface thermal environment of the high-speed aircraft, and is of great significance to research and engineering calculation in the technical field of computational aerodynamics.

Description

Technical Field

[0001] This invention relates to the field of computational aerodynamics, and in particular to a method, apparatus, equipment and medium for predicting aerodynamic thermal environment by surface catalysis and active ejection coupling. Background Technology

[0002] Under aerodynamic heating conditions, heat protection of local high heat flux areas such as the nose and leading edge of various high-speed aircraft is a bottleneck problem that urgently needs to be solved. The improvement of passive heat protection capabilities is difficult to meet the requirements of long-term non-ablative heat protection. Active ejector cooling technology (sweating cooling) utilizes the latent heat of phase change of the cooling medium and the mass ejection effect of working fluid vapor on the surface of porous structures to achieve extremely high heat protection efficiency, and has now become one of the important directions for the development of future thermal protection systems.

[0003] During cross-space and cross-velocity flight, the surface of an aircraft employing active ejector cooling technology, under the scouring action of high-temperature, high-speed gas, exhibits a coupling phenomenon between atomic catalytic recombination and the ejection of the cooling medium into the flow field. This coupling phenomenon manifests dynamically with space and time at microscopic, mesoscopic, and macroscopic scales, changing with the flight state. Existing aerodynamic thermal prediction techniques can only consider the influence of a single catalytic or ejector effect, such as using the catalytic recombination coefficient in engineering. To characterize the catalytic effect of the surface: ; In the formula, For the catalytic reaction rate, It is the gas constant. It is the surface temperature. Based on this, the boundary conditions are defined as follows: ; In the formula, It is the density of the gas. Component mass fraction It is the diffusion coefficient of the component. It is the surface component mass fraction gradient.

[0004] Surface density is obtained from surface active ejection calculations based on the conservation principle. ,speed and pressure : ; In the formula, It is the flow field pressure. It is the gas constant of the surface gas mixture, and the calculation formula is as follows: ; In the formula, and Let S be the mass fraction of a certain component s and the gas constant, respectively. Since there is currently a lack of reasonable methods to calculate the mass fraction of surface components (a type I boundary condition) or the mass fraction gradient of components (a type II boundary condition) under the coupling effect of surface catalysis and active ejection, the mass fraction of the surface is usually determined by giving the mass ratio of the incoming flow component to the cooling working fluid.

[0005] Researchers have long recognized the catalytic and active ejection coupling effect on the surface of aircraft using active ejection cooling technology. Developing targeted numerical methods can significantly improve the accuracy of predicting the thermal environment of aircraft surfaces and promote the rapid design iteration and engineering application of active ejection cooling thermal protection systems. However, due to the complexity of the thermal, mechanical, and chemical coupling mechanism between high-temperature, high-speed flow and surface interaction, researchers have not yet been able to establish an aerodynamic thermal prediction model that can comprehensively consider the coupling between surface catalysis and active ejection, and there is also a lack of relevant aerodynamic thermal numerical prediction technologies. Summary of the Invention

[0006] To overcome the problems existing in related technologies, this disclosure provides a method, apparatus, equipment and medium for predicting the aerodynamic thermal environment by surface catalysis and active ejection coupling, so as to solve the technical problems in related technologies.

[0007] This specification provides one or more embodiments of a method for predicting the aerodynamic thermal environment coupled with surface catalysis and active ejection, including the following steps: The surface catalytic reaction formation rate was calculated based on the temperature, pressure, and component mass fraction of the aircraft surface. The surface component mass fraction gradient is calculated based on the surface active ejection mass flow rate and the surface catalytic reaction generation rate. The surface heat flux under the coupling effect of surface catalysis and active ejection is determined based on the surface mass flow rate, temperature and component mass fraction gradient.

[0008] Furthermore, the surface catalytic reaction generation rate is calculated based on the temperature, pressure, and component mass fraction of the aircraft surface using the following formula: ; In the formula, , , and These correspond to the catalytic reaction production rates of nitrogen atoms, oxygen atoms, nitrogen gas, and oxygen gas, respectively. and These are the surface density and temperature of the aircraft material, respectively. and These represent the mass fractions of nitrogen and oxygen atoms on the surface of the aircraft material, respectively. and These are the gas constants for nitrogen and oxygen atoms, respectively. and These are the catalytic recombination coefficients for nitrogen and oxygen atoms, respectively.

[0009] Furthermore, the calculation of the surface component mass fraction gradient based on the surface active ejection mass flow rate and the surface catalytic reaction generation rate is specifically as follows: ; In the formula, , , , and These represent the mass fractions of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the cooling working fluid, respectively. For active ejector mass flow rate; , , , and These represent the mass fractions of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and cooling fluid on the surface of the aircraft. , , , and These are the molecular diffusion coefficients for nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the cooling working fluid, respectively.

[0010] Furthermore, the surface heat flux determined based on the surface mass flow rate, temperature, and component mass fraction gradient under the coupling effect of surface catalysis and active ejection is specifically as follows: ; In the formula, , , , and These are the total enthalpy of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the cooling working fluid, respectively. It is the thermal conductivity of the mixed gas, It is the surface temperature gradient of the aircraft.

[0011] This specification provides one or more embodiments of a surface catalysis and active ejection coupled aerodynamic thermal environment prediction device, comprising: The first calculation module is used to calculate the surface catalytic reaction generation rate based on the temperature, pressure and component mass fraction of the aircraft surface; The second calculation module calculates the surface component mass fraction gradient based on the surface active ejection mass flow rate and the surface catalytic reaction generation rate. The surface heat flow determination module is used to determine the surface heat flow under the coupling effect of surface catalysis and active ejection based on the surface mass flow rate, temperature and component mass fraction gradient.

[0012] Furthermore, the first calculation module calculates the surface catalytic reaction generation rate using the following formula: ; Furthermore, the second calculation module calculates the surface component mass fraction gradient using the following formula: ; Furthermore, the surface heat flow determination module determines the surface heat flow under the coupling effect of surface catalysis and active ejection specifically as follows: ; This specification provides a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor, when executing the computer program, implements the surface catalysis and active ejection coupled aerodynamic thermal environment prediction method as described in any of the preceding embodiments.

[0013] This specification provides one or more embodiments of a computer-readable storage medium storing a computer program that, when executed by a processor, implements the surface catalysis and active ejection coupled aerodynamic environment prediction method as described in any of the preceding claims.

[0014] This disclosure provides a method, apparatus, equipment, and medium for predicting the aerodynamic thermal environment through surface catalysis and active ejection coupling. Its advantages lie in calculating the surface catalytic reaction generation rate based on the temperature, pressure, and component mass fraction of the aircraft surface; determining the surface component mass fraction gradient based on the surface mass conservation relationship; and finally determining the surface heat flow under the coupling effect of surface catalysis and active ejection based on the surface mass flow rate, temperature, and component mass fraction gradient. This achieves thermal environment prediction under the coupling effect of surface catalysis and active ejection. The method disclosed here solves the problem that existing thermal environment prediction technologies can only consider surface catalysis or surface active ejection alone, improving the accuracy of high-speed aircraft surface thermal environment prediction. This has significant implications for research and engineering calculations in the field of computational aerodynamics. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in one or more embodiments of this specification or in the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments recorded in this specification. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 A flowchart illustrating a surface catalysis and active ejection coupled aerodynamic thermal environment prediction method provided for one or more embodiments of this specification; Figure 2 A comparison chart of surface quality ejector thermal environment predicted by numerical calculation and ground wind tunnel test data provided for one or more embodiments of this specification; Figure 3 A comparison chart of numerical calculation predictions of surface catalytic thermal environment and ground wind tunnel test data provided for one or more embodiments of this specification; Figure 4 A schematic diagram of a surface catalysis and active ejection coupling cooling model used in one or more embodiments of this specification; Figure 5 Heat flux distribution near the stagnation point of a model under different surface catalytic recombination coefficients is provided for one or more embodiments of this specification. Figure 6 Block diagram of a surface catalysis and active ejection coupled aerodynamic thermal environment prediction device provided for one or more embodiments of this specification; Figure 7 This is a schematic diagram of the structure of a computer device provided for one or more embodiments of this specification. Detailed Implementation

[0017] To enable those skilled in the art to better understand the technical solutions in one or more embodiments of this specification, the technical solutions in one or more embodiments of this specification will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this specification, and not all of the embodiments. Based on one or more embodiments of this specification, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of this invention.

[0018] The present invention will now be described in detail with reference to specific embodiments and accompanying drawings.

[0019] Method Implementation Examples According to embodiments of the present invention, a method for predicting the aerodynamic and thermal environment coupled with surface catalysis and active ejection is provided, such as... Figure 1 The diagram shown is a flowchart of the surface catalysis and active ejection coupled aerodynamic thermal environment prediction method provided in this embodiment. The surface catalysis and active ejection coupled aerodynamic thermal environment prediction method according to this embodiment includes the following steps: Step S1: Calculate the surface catalytic reaction generation rate based on the temperature, pressure, and component mass fraction of the aircraft surface. Here, pressure refers to the gas pressure in the flow field, and "component" refers to the substances contained in the gas mixture; in this patent context, it can be oxygen atoms, nitrogen atoms, oxygen gas, nitrogen gas, and the active ejector working fluid. "Component" is a technical term in the field of fluid mechanics.

[0020] Step S2: Calculate the surface component mass fraction gradient based on the surface active ejection mass flow rate and the surface catalytic reaction generation rate.

[0021] Step S3: Determine the surface heat flow under the coupling effect of surface catalysis and active ejection based on the surface mass flow rate, temperature and component mass fraction gradient.

[0022] The surface catalysis and active ejection coupled aerodynamic thermal environment prediction method provided in this embodiment calculates the surface catalytic reaction generation rate based on the temperature, pressure, and component mass fraction of the aircraft surface. It determines the surface component mass fraction gradient based on the surface mass conservation relationship, and finally determines the surface heat flow under the surface catalysis and active ejection coupling effect based on the surface mass flow rate, temperature, and component mass fraction gradient. This achieves thermal environment prediction under the surface catalysis and active ejection coupling effect. This method solves the problem that existing thermal environment prediction technologies can only consider surface catalysis or surface active ejection effects alone, improving the accuracy of high-speed aircraft surface thermal environment prediction. It is of great significance to research and engineering calculations in the field of computational aerodynamics.

[0023] In one embodiment, the surface catalytic reaction formation rate is calculated based on the temperature, pressure, and component mass fraction of the aircraft surface, as follows: ; In the formula, , , and These correspond to the catalytic reaction production rates of nitrogen atoms, oxygen atoms, nitrogen gas, and oxygen gas, respectively. and These are the surface density and temperature of the aircraft, respectively. and These represent the mass fractions of nitrogen and oxygen atoms on the surface of the aircraft material, respectively. and These are the gas constants for nitrogen and oxygen atoms, respectively. and These are the catalytic recombination coefficients for nitrogen and oxygen atoms, respectively. Specific values ​​should be determined experimentally. In this embodiment, the metal material is selected... Non-metallic materials .

[0024] In this embodiment, the surface component mass fraction gradient is calculated based on the surface active entrainment mass flow rate and the surface catalytic reaction generation rate as follows: ; In the formula, , , , and These represent the mass fractions of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the cooling working fluid, respectively. For active ejector mass flow rate; , , , and These represent the mass fractions of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and cooling fluid on the surface of the aircraft. , , , and These are the molecular diffusion coefficients for nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the cooling working fluid, respectively.

[0025] In one embodiment, the surface heat flow under the coupling effect of surface catalysis and active ejection is determined based on the surface mass flow rate, temperature, and component mass fraction gradient as follows: ; In the formula, , , , and These are the total enthalpy of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the cooling working fluid, respectively. It is the thermal conductivity of the mixed gas, It is the surface temperature gradient of the aircraft.

[0026] The effectiveness of this method is illustrated below with specific examples.

[0027] Example 1.

[0028] This embodiment uses the results of ground wind tunnel tests conducted by Marvin and Akin on pointed-cone ejectors to numerically verify the surface quality ejector thermal environment prediction capability of the present invention. The free-flowing working fluid in the test was air, with a temperature of 69.72 K, static pressure of 700.83 Pa, Mach number of 7.4, angle of attack of 0°, and the wall was set as an isothermal wall at 308.32 K. The mass flow rate to the incoming mass flow rate ratios were 0%, 0.0410%, 0.0823%, and 0.1445%, respectively. Figure 2 The image shown is a comparison between the numerically calculated predicted surface quality ejector thermal environment and the ground wind tunnel test data in this example; from Figure 2 It can be seen that the dimensionless heat flux distribution on the wall predicted by numerical simulation is consistent with the variation law of experimental measurement values ​​and the agreement is good, which verifies the effectiveness of the present invention in predicting the surface quality ejector thermal environment.

[0029] Example 2.

[0030] This example uses a ground-based catalytic test on the surface of a 35mm spherical column to numerically verify the predictive ability of the surface catalytic thermal environment of this invention. The ground-based test had a total enthalpy of 16.5 MJ / kg and a total pressure of 0.32 MPa. The working fluid was air, and the test model was a 35mm spherical column heat flux measurement model. The surface was coated with 500nm layers of Au (nearly fully catalytic wall) and SiO2 (nearly non-catalytic wall) using a sputtering method to modify the surface catalytic properties. Figure 3 As shown, this is a comparison chart of the surface catalytic thermal environment predicted by numerical calculation and the ground wind tunnel test data in this example. The comparison of the numerical calculation and experimental measurement heat flow results shows that the surface heat flow distribution predicted by numerical calculation is consistent with the experimental measurement value, which verifies the effectiveness of the present invention in predicting the surface catalytic thermal environment.

[0031] Example 3.

[0032] This example uses a blunt cone model with a 10mm diameter opening in the stagnation zone (the opening is filled with a porous medium, and H2O is used as the cooling medium). This can be used as a reference. Figure 4 This is a schematic diagram of the surface catalysis and active ejection coupled cooling model used, with the free-flow condition representing the typical flight state of a high-speed aircraft. It is used to illustrate the predictive capability of this patent for the aerodynamic and thermal environment of surface catalysis and active ejection coupled systems. Figure 5 The results show the effects of no active ejection and ejection mass flow rate of 0.5 kg / (s*m) under the conditions of surface catalytic coefficient γ=0 and γ=1. 2 The thermal environment distribution (heat flow distribution) near the model stagnation point was compared with the heat flow distribution near the model stagnation point under different surface catalysis composite coefficients. It can be seen that the heat flow of the case with surface catalysis coefficient γ=0 is higher than that of the case with γ=1. The heat flow of the active ejection case in the ejection region is lower than that of the case without active ejection. This is consistent with the general understanding of the influence of surface catalysis effect and active ejection effect on thermal environment, and verifies the predictive ability of this patent for the aerodynamic thermal environment coupled with surface catalysis and active ejection.

[0033] Device Examples According to embodiments of the present invention, a surface catalysis and active ejection coupled aerodynamic thermal environment prediction device is provided, such as... Figure 6 The diagram shown is a block diagram of the surface catalysis and active ejection coupled aerodynamic thermal environment prediction device provided in this embodiment. According to an embodiment of the present invention, the surface catalysis and active ejection coupled aerodynamic thermal environment prediction device includes: The first calculation module 10 is used to calculate the surface catalytic reaction generation rate based on the temperature, pressure and component mass fraction of the aircraft surface.

[0034] The second calculation module 20 calculates the surface component mass fraction gradient based on the surface active ejection mass flow rate and the surface catalytic reaction generation rate.

[0035] The surface heat flow determination module 30 is used to determine the surface heat flow under the coupling effect of surface catalysis and active ejection based on the surface mass flow rate, temperature and component mass fraction gradient.

[0036] The surface catalysis and active ejection coupled aerodynamic thermal environment prediction device provided in this embodiment includes a first calculation module 10 for calculating the surface catalytic reaction generation rate based on the temperature, pressure, and component mass fraction of the aircraft surface; a second calculation module 20 for determining the surface component mass fraction gradient based on the surface mass conservation relationship; and finally, a surface heat flow determination module 30 for determining the surface heat flow under the surface catalysis and active ejection coupling effect based on the surface mass flow rate, temperature, and component mass fraction gradient. This realizes the prediction of the thermal environment under the surface catalysis and active ejection coupling effect. The method in this embodiment solves the problem that existing thermal environment prediction technologies can only consider surface catalysis or surface active ejection effects alone, improves the accuracy of high-speed aircraft surface thermal environment prediction, and has important significance for research and engineering calculation in the field of computational aerodynamics.

[0037] In this embodiment, the first calculation module 10 calculates the surface catalytic reaction generation rate using the following formula: ; In the formula, , , and These correspond to the catalytic reaction production rates of nitrogen atoms, oxygen atoms, nitrogen gas, and oxygen gas, respectively. and These are the surface density and temperature of the aircraft material, respectively. and These represent the mass fractions of nitrogen and oxygen atoms on the surface of the aircraft material, respectively. and These are the gas constants for nitrogen and oxygen atoms, respectively. and These are the catalytic recombination coefficients for nitrogen and oxygen atoms, respectively.

[0038] In this embodiment, the second calculation module 20 calculates the surface component mass fraction gradient using the following formula: ; In the formula, , , , and These represent the mass fractions of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the cooling working fluid, respectively. For active ejector mass flow rate; , , , and These represent the mass fractions of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and cooling fluid on the surface of the aircraft. , , , and These are the molecular diffusion coefficients for nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the cooling working fluid, respectively.

[0039] In this embodiment, the surface heat flow determination module 30 determines the surface heat flow under the coupling effect of surface catalysis and active ejection as follows: ; In the formula, , , , and These are the total enthalpy of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the cooling working fluid, respectively. It is the thermal conductivity of the mixed gas, It is the surface temperature gradient of the aircraft.

[0040] like Figure 7 As shown, the present invention also provides a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the surface catalysis and active ejection coupled aerodynamic thermal environment prediction method described in the above embodiments.

[0041] The present invention also provides a computer-readable storage medium storing a computer program thereon. When the computer program is executed by a processor, it implements the surface catalysis and active ejection coupled aerodynamic thermal environment prediction method described in the above embodiments. When the computer program is executed by the processor, it implements the following method steps: Step S1: Calculate the surface catalytic reaction formation rate based on the temperature, pressure, and component mass fraction of the aircraft surface.

[0042] Step S2: Calculate the surface component mass fraction gradient based on the surface active ejection mass flow rate and the surface catalytic reaction generation rate.

[0043] Step S3: Determine the surface heat flow under the coupling effect of surface catalysis and active ejection based on the surface mass flow rate, temperature and component mass fraction gradient.

[0044] Those skilled in the art will understand that all or part of the processes in the methods of the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods. Any references to memory, storage, databases, or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), dual data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), Rambus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0045] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to mutually. Each embodiment focuses on describing the differences from other embodiments. In particular, for apparatus or system embodiments, since they are basically similar to method embodiments, the description is relatively simple; relevant parts can be referred to the descriptions in the method embodiments. The apparatus and system embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without creative effort.

[0046] Furthermore, the functional modules in the various embodiments of this disclosure can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or in the form of hardware plus software functional modules.

[0047] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention, and the contents not described in detail in the specification of the present invention are well known to those skilled in the art.

Claims

1. A method for predicting the aerodynamic thermal environment coupled with surface catalysis and active ejection, characterized in that, Includes the following steps: The surface catalytic reaction formation rate was calculated based on the temperature, pressure, and component mass fraction of the aircraft surface. The surface component mass fraction gradient is calculated based on the surface active ejection mass flow rate and the surface catalytic reaction generation rate. The surface heat flux under the coupling effect of surface catalysis and active ejection is determined based on the surface mass flow rate, temperature and component mass fraction gradient.

2. The surface catalysis and active ejection coupled aerodynamic thermal environment prediction method as described in claim 1, characterized in that, The surface catalytic reaction generation rate is calculated based on the temperature, pressure, and component mass fraction of the aircraft surface using the following formula: ； In the formula, , , and These correspond to the catalytic reaction production rates of nitrogen atoms, oxygen atoms, nitrogen gas, and oxygen gas, respectively. and These are the surface density and temperature of the aircraft, respectively. and These represent the mass fractions of nitrogen and oxygen atoms on the surface of the aircraft. and The gas constants for nitrogen and oxygen atoms are respectively. and These are the catalytic recombination coefficients for nitrogen and oxygen atoms, respectively.

3. The surface catalysis and active ejection coupled aerodynamic thermal environment prediction method as described in claim 1, characterized in that, The calculation of the surface component mass fraction gradient based on the surface active ejection mass flow rate and the surface catalytic reaction generation rate is specifically as follows: ； In the formula, , , , and These represent the mass fractions of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the cooling working fluid, respectively. For active ejector mass flow rate; , , , and These represent the mass fractions of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and coolant on the surface of the aircraft. , , , and These are the molecular diffusion coefficients for nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the cooling working fluid, respectively.

4. The surface catalysis and active ejection coupled aerodynamic thermal environment prediction method as described in claim 1, characterized in that, The surface heat flux under the coupling effect of surface catalysis and active ejection is determined based on the surface mass flow rate, temperature, and component mass fraction gradient as follows: ； In the formula, , , , and These are the total enthalpy of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the active ejector working fluid, respectively. For the thermal conductivity of the mixed gas, This represents the surface temperature gradient of the aircraft.

5. A surface catalysis and active ejection coupled aerodynamic thermal environment prediction device, characterized in that, include: The first calculation module is used to calculate the surface catalytic reaction generation rate based on the temperature, pressure and component mass fraction of the aircraft surface; The second calculation module calculates the surface component mass fraction gradient based on the surface active ejection mass flow rate and the surface catalytic reaction generation rate. The surface heat flow determination module is used to determine the surface heat flow under the coupling effect of surface catalysis and active ejection based on the surface mass flow rate, temperature and component mass fraction gradient.

6. The surface catalysis and active ejection coupled aerodynamic thermal environment prediction device as described in claim 5, characterized in that, The first calculation module calculates the surface catalytic reaction generation rate using the following formula: ； In the formula, , , and These correspond to the catalytic reaction production rates of nitrogen atoms, oxygen atoms, nitrogen gas, and oxygen gas, respectively. and These are the surface density and temperature of the aircraft, respectively. and These represent the mass fractions of nitrogen and oxygen atoms on the surface of the aircraft. and The gas constants for nitrogen and oxygen atoms are respectively. and These are the catalytic recombination coefficients for nitrogen and oxygen atoms, respectively.

7. The surface catalysis and active ejection coupled aerodynamic thermal environment prediction device as described in claim 5, characterized in that, The second calculation module calculates the surface component mass fraction gradient using the following formula: ； In the formula, , , , and These represent the mass fractions of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the cooling working fluid, respectively. For active ejector mass flow rate; , , , and These represent the mass fractions of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and coolant on the surface of the aircraft. , , , and These are the molecular diffusion coefficients for nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the cooling working fluid, respectively.

8. The surface catalysis and active ejection coupled aerodynamic thermal environment prediction device as described in claim 5, characterized in that, The surface heat flow determination module determines the surface heat flow under the coupling effect of surface catalysis and active ejection as follows: ； In the formula, , , , and These are the total enthalpy of nitrogen atoms, oxygen atoms, nitrogen gas, oxygen gas, and the cooling working fluid, respectively. It is the thermal conductivity of the mixed gas, It is the surface temperature gradient of the aircraft.

9. A computer device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the surface catalysis and active ejection coupled aerodynamic environment prediction method as described in any one of claims 1 to 4.

10. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it implements the surface catalysis and active ejection coupled aerodynamic thermal environment prediction method as described in any one of claims 1 to 4.

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