A data-driven method for designing arc wind tunnel test conditions for thin-leading edge components

Abstract

This invention discloses a data-driven method for designing arc wind tunnel test conditions for thin-tipped leading-edge components, comprising: setting the test nozzle for the arc wind tunnel test and calculating the exit Mach number; calculating the outer surface temperature field of the thin-tipped leading-edge component under flight conditions and determining the characteristic temperature; designing the test states of the thin-tipped leading-edge component and constructing an arc wind tunnel test track using different test states; calculating the thermal response of each test state; evaluating the deviation of the outer surface temperature in conjunction with the characteristic temperature and determining whether the criteria are met; iteratively updating the leading-edge pressure and leading-edge recovery enthalpy in test states that do not meet the criteria using the secant method; calculating the test gas parameters for the arc wind tunnel test and updating the leading-edge heat flux density in the test states; after all aerodynamic thermal environment parameters in the test states have been updated, recalculating the thermal response of the test states and determining whether the criteria are met; and outputting the current arc wind tunnel test track when all test states meet the criteria.

Description

Technical Field

[0001] This invention belongs to the field of ground testing technology for aerodynamics and thermal protection structures of high-speed aircraft, specifically involving a data-driven method for designing arc wind tunnel test conditions for thin leading edge components. Background Technology

[0002] Thin-edge components, due to their superior aerodynamic characteristics, are widely used in critical components such as the inlet lips of scramjet engines, aerodynamic control surfaces of high-speed aircraft, and leading edges of strakes. This configuration not only significantly reduces aerodynamic drag but also effectively helps to achieve the predetermined flow field structure, thereby improving the overall performance of the aircraft.

[0003] However, compared to blunt leading edge designs, sharp and thin leading edges face more severe thermal loads under the same flight conditions, and their surface transient temperature changes are more drastic, which can easily lead to extreme heating or cooling phenomena in the structure, making the sharp leading edge configuration face serious reliability challenges.

[0004] In current design verification processes, aerodynamic-thermal-structural coupling analysis is commonly used as an auxiliary design tool. However, multiphysics coupling modeling is complex and uncertain, and due to factors such as manufacturing process deviations, numerical simulation results often deviate from actual operating conditions. Furthermore, ground-based arc wind tunnel tests suffer from mismatches in leading-edge thermal testing and verification due to differences between the ground and natural environments, which can potentially lead to catastrophic consequences in severe cases.

[0005] To ensure the reliability and feasibility of the design scheme, ground-based arc wind tunnel testing is an indispensable and important verification method. However, current ground-based test conditions cannot fully replicate the real high-altitude flight environment, and accurate measurement of heat flux at the thin leading edge is quite difficult in wind tunnel testing. The inadequacy of measurement methods, along with the differences between ground and air environments, leads to a significant mismatch between arc wind tunnel testing and the verification of leading-edge aerodynamic heating and structural thermal response under real flight conditions. This affects the validity of the test results, causing deviations in the evaluation of leading-edge thermal structure schemes and risk assessments, ultimately hindering the improvement of the reliability of thin leading-edge component designs. Summary of the Invention

[0006] The purpose of this invention is to provide a data-driven method for designing arc wind tunnel test conditions for thin leading edge components, which solves the mismatch between the service environment and structural thermal response of thin leading edge components during ground thermal testing and actual flight, thereby enabling the ground arc wind tunnel test environment to effectively approximate the leading edge surface thermal response state under real flight conditions.

[0007] To achieve the above objectives, the present invention employs the following technical solution:

[0008] A data-driven method for designing arc wind tunnel test conditions for thin-leading edge components includes:

[0009] Based on the aerodynamic thermal environment parameters of the thin leading edge component, the test nozzle for the electric arc wind tunnel test was set and the exit Mach number was calculated.

[0010] Based on the three-dimensional heat conduction equation, the temperature field of the outer surface of the thin leading edge component under flight conditions is calculated and the characteristic temperature is determined.

[0011] Design test conditions for thin-edge components and construct electric arc wind tunnel test tracks using different test conditions;

[0012] Using a thin leading-edge component as the test object, the thermal response of each test state was calculated;

[0013] Based on the thermal response of each test state, the deviation of the outer surface temperature is evaluated in conjunction with the characteristic temperature, and it is determined whether the test state meets the criteria.

[0014] The leading edge pressure and leading edge recovery enthalpy in test states that do not meet the criteria are updated iteratively using the secant method.

[0015] Based on the normal shock wave relationship, the test gas parameters of the electric arc wind tunnel test are calculated;

[0016] Using the test gas parameters, update the leading edge heat flux density in test states that do not meet the criteria;

[0017] After the leading edge pressure, leading edge recovery enthalpy, and leading edge heat flux density are all updated, it is determined again whether the test state meets the criteria.

[0018] Once all test conditions in the electric arc wind tunnel test track meet the criteria, the electric arc wind tunnel test track is output.

[0019] Furthermore, based on the three-dimensional heat conduction equation, the outer surface temperature field of the thin leading-edge component under flight conditions is calculated and the characteristic temperature is determined, including:

[0020] First, a three-dimensional Cartesian coordinate system is constructed for the thin leading edge component, and a three-dimensional heat conduction equation is established; boundary conditions are then set:

[0021] ;

[0022] In the formula, Effective heat flow to the outer surface of the thin leading edge component; The surface emissivity of the material for the thin leading-edge component; It is the Stefan-Boltzmann constant; To restore the enthalpy and heat flux density of the outer surface of the thin leading edge component; For wall enthalpy, The specific heat capacity at constant pressure of the test gas on the outer surface of the thin leading edge component; For the outer surface temperature field;

[0023] The external surface temperature field under flight conditions was obtained by solving the three-dimensional heat conduction equation. and from The outer surface temperature of the highest temperature region on the thin leading edge component is selected as the characteristic temperature. .

[0024] Furthermore, test conditions for the thin-edge components were designed, and different test conditions were used to construct an arc wind tunnel test track, including:

[0025] The aerothermal environment parameters of the thin leading edge component are discretized into a design space. Each test state consists of a set of durations. Leading edge pressure Enthalpy of recovery at the leading edge and leading edge heat flux density All test conditions form the arc wind tunnel test track.

[0026] Furthermore, using the thin leading-edge component as the test object, the thermal response of each test state was calculated, including:

[0027] First, a two-dimensional Cartesian coordinate system is constructed for the thin leading edge component, and a two-dimensional transient heat conduction equation is established;

[0028] In each test state, the two-dimensional structure temperature field is obtained by solving the two-dimensional transient heat conduction equation, and the leading edge surface temperature of the thin leading edge component is extracted as the thermal response.

[0029] Furthermore, based on the thermal response of each test state, the deviation of the outer surface temperature is evaluated in conjunction with the characteristic temperature, and it is determined whether the test state meets the criteria, including:

[0030] Calculate the deviation of the outer surface temperature ,in For thermal response, The characteristic temperature is used for determination; the following criteria are applied:

[0031] ;

[0032] in, This is the preset maximum temperature deviation.

[0033] Furthermore, the leading edge pressure and leading edge recovery enthalpy in test states that do not meet the criteria are iteratively updated using the secant method, including:

[0034] For leading edge pressure and the enthalpy of recovery of the leading edge Define function ,in This represents the deviation of the outer surface temperature. The maximum temperature deviation is preset; the solution is obtained using the secant method. The iterative formula is:

[0035] ;

[0036] ;

[0037] ;

[0038] ;

[0039] In the above formula, and These represent the leading edge pressure and the leading edge recovery enthalpy, respectively. The process variables of each iteration; and Indicates the first Leading edge pressure and leading edge recovery enthalpy in the next iteration; To be and Replacement function In and The expression that follows.

[0040] Furthermore, based on the normal shock wave relation, the test gas parameters for the electric arc wind tunnel test are calculated, including:

[0041] Updated leading edge pressure and the updated leading edge recovery enthalpy Combined with the exit Mach number of the test nozzle The gas pressure behind the leading edge normal shock wave of the thin-tipped leading edge assembly was calculated using the normal shock wave relation. Gas density after normal shock wave Gas temperature after normal shock wave ;based on , and Calculate the test gas parameters for the electric arc wind tunnel test in front of the normal shock wave, including the test gas density. static temperature of the test gas .

[0042] Furthermore, using the test gas parameters, updating the leading-edge heat flux density in test states that do not meet the criteria includes:

[0043] Updated leading edge heat flux density The expression is as follows:

[0044] ;

[0045] in, The density of the test gas; To test the gas velocity; The leading edge radius of the thin leading edge assembly; The dynamic viscosity of the test gas; The effective sweep angle of the leading edge of the thin leading edge assembly; The heat flux at the stagnation point of a spherical end with the same radius as the leading edge is calculated using the following formula:

[0046] ;

[0047] in, These are the theoretical fitting parameters; For reference density; For reference speed; The total enthalpy of the incoming flow is expressed as follows: ;in To test the static temperature of the gas, The specific heat capacity at constant pressure of the test gas on the outer surface of the thin leading edge component; This is the preset isothermal wall enthalpy value.

[0048] A terminal device includes a processor, a memory, and a computer program stored in the memory; when the processor executes the computer program, it implements the data-driven method for designing arc wind tunnel test conditions for thin leading edge components.

[0049] A computer-readable storage medium storing a computer program; when executed by a processor, the computer program implements the data-driven method for designing arc wind tunnel test conditions for thin leading-edge components.

[0050] Compared with the prior art, the present invention has the following technical features:

[0051] This invention, based on the leading-edge aerodynamic thermal environment under flight conditions, constructs simulation accuracy criteria for the temperature response of leading-edge test specimens to the actual leading-edge structure under different test conditions. It employs an iterative calculation method for aerodynamic thermal environment parameters with good computational robustness and superlinear convergence, systematically solving the verification mismatch problem between the actual flight environment and the ground test environment caused by differences in gas parameters and structural states. This invention provides a solid theoretical foundation and feasible technical route for ground verification test design of aircraft leading-edge structure schemes, material and process selection under nonlinear time-varying aerodynamic heating, demonstrating significant innovation and engineering practical value. Attached Figure Description

[0052] Figure 1 This is a schematic flowchart of the method of the present invention;

[0053] Figure 2 A schematic diagram showing the fitting of aerodynamic and thermal environment parameters with test conditions under continuously changing flight conditions;

[0054] Figure 3 This is a schematic diagram illustrating the relationship between the leading-edge test specimen and the simulated geometry and local structure of the actual rudder's leading edge.

[0055] Figure 4 A schematic diagram of a two-dimensional Cartesian coordinate system constructed for the thin leading edge component to calculate the thermal response for each test state;

[0056] Figure 5 This is a schematic diagram of the leading edge test specimen under the action of the test gas in the embodiment;

[0057] Figure 6 The example shows the leading edge surface temperature under test conditions, the leading edge surface temperature under flight conditions, and the deviation of the leading edge surface temperature at a certain moment.

[0058] Figure 7 This is a schematic diagram comparing the thermal environment at the leading edge with the preliminary design results of the arc wind tunnel test track in the embodiment; where (a) is a comparison of the leading edge pressure, (b) is a comparison of the leading edge recovery enthalpy, and (c) is a comparison of the leading edge heat flux density.

[0059] Figure 8 This is a schematic diagram showing the change in the leading edge surface temperature response of the wedge-shaped leading edge test specimen during the iterative calculation of the test conditions in the example, and its comparison with the leading edge surface temperature under flight conditions. Detailed Implementation

[0060] This invention provides a data-driven method for designing arc wind tunnel test conditions for thin-tipped leading-edge components. By systematically analyzing the differences in key parameters between ground test environments and real flight environments, and combining this with the thermal response characteristics of the thin-tipped leading-edge configuration, an optimized design scheme suitable for ground test conditions is established. This provides scientific technical support and feasible implementation methods for addressing the design issues of reasonable and reliable ground test conditions for thin-tipped leading-edge components. The design method of this invention specifically includes the following steps:

[0061] Step 1: Based on the aerodynamic thermal environment parameters of the thin leading edge component, set the test nozzle for the electric arc wind tunnel test and calculate the exit Mach number.

[0062] The aerodynamic thermal environment parameters include the leading edge pressure in the thin-edge assembly. and the enthalpy of recovery of the outer surface and outer surface heat flux density .

[0063] Based on the extreme aerodynamic and thermal environment parameters of the thin leading edge assembly throughout the flight, a test nozzle that meets the extreme aerodynamic and thermal environment parameters is selected; the extreme aerodynamic and thermal environment parameters include the maximum leading edge pressure, the highest recovery enthalpy, and the maximum heat flux density.

[0064] Exit Mach number of the test nozzle Calculated using the following formula:

[0065]

[0066] in The exit area of ​​the test nozzle, To test the throat area of ​​the nozzle, The specific heat ratio of the test gas.

[0067] like Figure 3 As shown, the thin leading edge component described in this solution refers to a component with a tapered leading edge structure.

[0068] Step 2: Based on the three-dimensional heat conduction equation, calculate the outer surface temperature field of the thin leading edge component under flight conditions and determine the characteristic temperature.

[0069] First, a three-dimensional Cartesian coordinate system is constructed for the thin leading edge component, and a three-dimensional heat conduction equation is established:

[0070]

[0071] in, The material density of the thin leading edge component; The specific heat capacity at constant pressure of the material; The thermal conductivity of the material; The coordinates are three axes in a three-dimensional rectangular coordinate system; For time; The temperature field of the thin-edge component is a three-dimensional structure that is a function of the three-axis coordinates and time. The initial condition is a uniform temperature. , This indicates the initial temperature.

[0072] Boundary conditions considering aerodynamic heating and surface radiation:

[0073]

[0074] In the formula, Effective heat flow to the outer surface of the thin leading edge component; The surface emissivity of the material for the thin leading-edge component; , is the Stefan-Boltzmann constant; Wall enthalpy; The specific heat capacity at constant pressure of the test gas on the outer surface of the thin leading edge component; This represents the temperature field of the outer surface.

[0075] By solving equations (2) and (3) together, the external surface temperature field under flight conditions is obtained. The outer surface temperature of the highest temperature region on the thin leading edge component is selected as the characteristic temperature. .

[0076] Step 3: Design test conditions for the thin leading edge components and construct an electric arc wind tunnel test track using different test conditions.

[0077] The aerothermal environment parameters of the thin leading edge component are discretized into a design space. Each test state; the aerodynamic thermal environment parameter design space includes leading edge pressure. Value range, leading edge recovery enthalpy Value range, leading edge heat flux density Value range and duration Value range; the experimental state is formed by sampling and combining values ​​from each value range.

[0078] Each experimental state includes a set of durations. Leading edge pressure Enthalpy of recovery at the leading edge and leading edge heat flux density Then all the test conditions form the electric arc wind tunnel test track.

[0079] The leading edge pressure Enthalpy of recovery at the leading edge and leading edge heat flux density , specifically refers to the parameters of the leading edge portion of the thin leading edge assembly.

[0080] Step 4: Using the thin leading edge component as the test object, calculate the thermal response for each test state.

[0081] See Figure 4 First, a two-dimensional Cartesian coordinate system is constructed for the thin-edge component, and a two-dimensional transient heat conduction equation is established:

[0082]

[0083] in, These are the two axes of coordinates in a two-dimensional rectangular coordinate system. The temperature field of the two-dimensional structure of the thin-edge component is represented as a function of two axes and time: .

[0084] In each experimental condition, the temperature field of the two-dimensional structure is obtained by solving the two-dimensional transient heat conduction equation. The leading edge surface temperature of the thin leading edge assembly is extracted as the thermal response. .

[0085] Step 5: Based on the thermal response of each test state, evaluate the deviation of the outer surface temperature in conjunction with the characteristic temperature, and determine whether the test state meets the criteria.

[0086] Calculate the deviation of the outer surface temperature ; Obtain the deviation of the outer surface temperature Then, the experimental status is determined according to the following criteria:

[0087]

[0088] in, This is the preset maximum temperature deviation.

[0089] If the external surface temperature deviation is found in all test states of the electric arc wind tunnel test track... If all the above criteria are met, the current electric arc wind tunnel test track will be output; otherwise, proceed to step 6.

[0090] Step 6: Iteratively update the leading edge pressure in test states that do not meet the criterion using the secant method. and the enthalpy of recovery of the leading edge .

[0091] For leading edge pressure and the enthalpy of recovery of the leading edge Define function Solving using the secant method The iterative formula is:

[0092]

[0093] In the above formula, and These represent the leading edge pressure and the leading edge recovery enthalpy, respectively. The process variables of each iteration; and Indicates the first Leading edge pressure and leading edge recovery enthalpy in the next iteration; To be and Replacement function In and The expression that follows.

[0094] During iteration, for and After setting initial values, the iteration begins; the final output is the value at the end of the iteration. and As the updated leading edge pressure and the updated leading edge recovery enthalpy .

[0095] Step 7: Calculate the test gas parameters for the electric arc wind tunnel test based on the normal shock wave relationship.

[0096] Updated leading edge pressure and the updated leading edge recovery enthalpy Combined with the exit Mach number of the test nozzle determined in step 1 The gas pressure behind the leading edge normal shock wave of the thin-tipped leading edge assembly was calculated using the normal shock wave relation. Gas density after normal shock wave Gas temperature after normal shock wave ;based on , and Calculate the test gas parameters for the electric arc wind tunnel test in front of the normal shock wave, including the test gas density. static temperature of the test gas .

[0097]

[0098] in, The specific heat ratio of the test gas; The leading edge gas temperature of the thin-edge component; The leading edge gas density of the thin leading edge component; The Mach number after the normal shock wave, and the Mach number at the exit. The result was obtained through calculation.

[0099] Step 8: Using the test gas parameters, update the leading-edge heat flux density in test states that do not meet the criteria. .

[0100] Based on the theory of infinitely long swept-back cylinders, the updated leading-edge heat flux density The expression is as follows:

[0101]

[0102] in, The density of the test gas; To test the gas velocity; The leading edge radius of the thin leading edge assembly; The dynamic viscosity of the test gas; The effective sweep angle of the leading edge of the thin leading edge assembly; The heat flux at the stagnation point of a spherical end with the same radius as the leading edge is calculated using the following formula:

[0103]

[0104] in, The parameters are theoretical fitting parameters, and in this embodiment of the invention, they are taken as follows: ; For reference density, the value in this embodiment of the invention is taken as... ; For reference speed, the value used in this embodiment of the invention is [value]. ; The total enthalpy of the incoming flow is expressed as follows: ;in To test the static temperature of the gas, The specific heat capacity at constant pressure of the test gas on the outer surface of the thin leading edge component; This is the preset isothermal wall enthalpy value.

[0105] Step 9: After the leading edge pressure, leading edge recovery enthalpy, and leading edge heat flux density have all been updated, determine again whether the test state meets the criteria.

[0106] For a test state that does not meet the criterion, the leading edge pressure is obtained after all the included aerodynamic and thermal environment parameters have been updated. Enthalpy of recovery at the leading edge and leading edge heat flux density The test conditions are reassessed using the criteria from step 5. Once all test conditions in the arc wind tunnel test track meet the criteria, it is considered the final arc wind tunnel test track. The output will be in the form of the following array:

[0107]

[0108] Taking the last row of parameters in the array as an example, the last row of parameters is the first... There are several experimental states, among which They represent the first Duration, leading edge pressure, leading edge recovery enthalpy, and leading edge heat flux density under each test condition.

[0109] Example:

[0110] In this embodiment, the thin leading edge component is Figure 3 The rudder shown is formed by taking the characteristic structure of its leading edge, as shown. Figure 3The wedge-shaped leading edge test specimen shown; the spacecraft shape and thermal environment parameters of the reference "Shape Design to Minimize the Peak Heat-Flux of Blunt Leading-Edge" (Cui K, Hu SC. Shape Design to Minimize the Peak Heat-Flux of Blunt Leading-Edge[C] / / 51st AIAA aerospace sciences meeting including the new horizons forum and aerospace exposition 2013, vol. 4: 51stAIAA (American Institute of Aeronautics and Astronautics) aerospace sciencesmeeting including the new horizons forum and aerospace exposition, 7-10 January 2013, Grapevine, Texas, USA. 2013.) are as follows. Figure 4 and Figure 5 As shown, in this embodiment, the leading edge radius is taken as... m, and assuming the Mach number and flight altitude range studied in the literature, the aerodynamic thermal environment of an accelerated climb flight condition is obtained as follows: Figure 6 As shown, there is a high heat flux impact.

[0111] Step 1, in this embodiment, the ratio of the exit area to the throat area of ​​the test nozzle is: The specific heat ratio of the test gas According to equation (1), the exit Mach number of the test nozzle is obtained. .

[0112] Step 2: Calculate according to the material parameters of "GH1016" recorded in the "China Aviation Materials Handbook (Volume 2)", such as... Figure 6 The temperature of the leading edge under flight conditions is shown in the figure.

[0113] Step 3: Based on the thermal environment change process and the requirements of the evaluation test, conduct test state design; such as... Figure 2 As shown, in this embodiment, the following is set to There are a total of six experimental states; this step participates in the subsequent iterative design process, providing initial values ​​for the iterative calculation program.

[0114] In this embodiment, the test state and test status The leading-edge pressure, leading-edge recovery enthalpy, and leading-edge heat flux density are set the same, differing only in duration; test conditions and test status The only difference is the duration; by merging similar test states in this way, the workload of electric arc wind tunnel test debugging and design iteration can be effectively reduced, and the test implementation cost can be lowered.

[0115] Step 4: For the arc wind tunnel test track, calculate the two-dimensional structural temperature field and obtain the leading edge surface temperature. See also Figure 6 "Test operating condition leading edge surface temperature"

[0116] Step 5: Based on the results of Steps 3 and 4, calculate the deviation of their outer surface temperatures. See Figure 6 The image shows a deviation in the leading edge surface temperature at a certain moment.

[0117] In terms of the timing of flight condition and test state calculations, this case study selects the flight time period during which the flight condition exhibits a significant thermal effect, and incorporates the test state... Start time and test state Adjustments should be made at the end of the process.

[0118] Deviation of outer surface temperature The criteria in equation (5) are used to determine whether the six test states meet the requirements. In this embodiment, based on the requirements for the highest temperature coverage at the leading edge and the heating / cooling rate, the maximum temperature deviation for different test states is as follows:

[0119] Table 1: Maximum temperature deviation under different test conditions in the examples

[0120]

[0121] Specifically, the experimental state This is the most demanding aerodynamic thermal environment at the leading edge and the highest external surface temperature test condition in this embodiment. The deviation between the flight test condition and the highest temperature is required to be no more than 50°C.

[0122] After evaluation, none of the six experimental states in step 3 met the criteria.

[0123] Step 6, in experimental condition For example, the secant method iterative calculation requires two sets of initial values. In this embodiment, the experimental state... Leading edge pressure Enthalpy of recovery at the leading edge The first set of initial values ​​are the values ​​designed in step 3, denoted as [ , The second set of initial values ​​is taken as 0.8 times that value, i.e. , The selection of initial values ​​does not affect the final calculation result, but only the speed of iteration convergence; the final iteration result is... Approximately 46K, meeting the criterion requirements, stop iteration.

[0124] Step 7: Calculate the gas pressure behind the leading-edge normal shock wave of the wedge-shaped leading-edge specimen using the isentropic flow relation. Gas density after normal shock wave Gas temperature after normal shock wave Thus, the test gas parameters of the electric arc wind tunnel test in front of the normal shock wave can be calculated.

[0125] Step 8: Calculate the updated leading-edge heat flux density; the leading-edge radius of the wedge-shaped leading-edge specimen is calculated during this step. =0.0025m, effective sweep angle of the leading edge of the wedge-shaped leading edge specimen =0°.

[0126] Step 9, for all test states to Repeat steps 4 to 8 in the embodiments to obtain test states that meet the criteria, and combine them in sequence to form the final arc wind tunnel test track. ,like Figure 7 As shown.

[0127] In this embodiment, the arc wind tunnel test track meets the criterion requirements. The calculation was performed in a total of 11 iterations. Figure 8 The diagrams showing the comparison of the leading edge surface temperature of the wedge-shaped leading edge test specimen with the leading edge surface temperature under flight conditions during several typical iteration processes are presented.

[0128] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application 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 of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application, and should all be included within the protection scope of this application.

Claims

1. A data-driven method for designing arc wind tunnel test conditions for thin-edge components, characterized in that, include: Based on the aerodynamic thermal environment parameters of the thin leading edge component, the test nozzle for the electric arc wind tunnel test was set and the exit Mach number was calculated. Based on the three-dimensional heat conduction equation, the temperature field of the outer surface of the thin leading edge component under flight conditions is calculated and the characteristic temperature is determined. Design test conditions for thin-edge components and construct electric arc wind tunnel test tracks using different test conditions; Using a thin leading-edge component as the test object, the thermal response of each test state was calculated; Based on the thermal response of each test state, the deviation of the outer surface temperature is evaluated in conjunction with the characteristic temperature, and it is determined whether the test state meets the criteria. The leading edge pressure and leading edge recovery enthalpy in test states that do not meet the criteria are updated iteratively using the secant method. Based on the normal shock wave relationship, the test gas parameters of the electric arc wind tunnel test are calculated; Using the test gas parameters, update the leading edge heat flux density in test states that do not meet the criteria; After the leading edge pressure, leading edge recovery enthalpy, and leading edge heat flux density are all updated, it is determined again whether the test state meets the criteria. Once all test conditions in the electric arc wind tunnel test track meet the criteria, the electric arc wind tunnel test track is output.

2. The data-driven method for designing arc wind tunnel test conditions for thin-edge components according to claim 1, characterized in that, Based on the three-dimensional heat conduction equation, the outer surface temperature field of the thin-tipped leading-edge assembly under flight conditions is calculated and the characteristic temperature is determined, including: First, a three-dimensional Cartesian coordinate system is constructed for the thin leading edge component, and a three-dimensional heat conduction equation is established; boundary conditions are then set: ； In the formula, Effective heat flow to the outer surface of the thin leading edge component; The surface emissivity of the material for the thin leading-edge component; It is the Stefan-Boltzmann constant; To restore the enthalpy and heat flux density of the outer surface of the thin leading edge component; For wall enthalpy, The specific heat capacity at constant pressure of the test gas on the outer surface of the thin leading edge component; For the outer surface temperature field; The external surface temperature field under flight conditions was obtained by solving the three-dimensional heat conduction equation. and from The outer surface temperature of the highest temperature region on the thin leading edge component is selected as the characteristic temperature. .

3. The data-driven method for designing arc wind tunnel test conditions for thin-edge components according to claim 1, characterized in that, Design test conditions for thin-edge components, and construct arc wind tunnel test tracks using different test conditions, including: The aerothermal environment parameters of the thin leading edge component are discretized into a design space. Each test state consists of a set of durations. Leading edge pressure Enthalpy of recovery at the leading edge and leading edge heat flux density All test conditions form the arc wind tunnel test track.

4. The data-driven method for designing arc wind tunnel test conditions for thin-edge components according to claim 1, characterized in that, Using a thin leading-edge component as the test object, the thermal response of each test state was calculated, including: First, a two-dimensional Cartesian coordinate system is constructed for the thin leading edge component, and a two-dimensional transient heat conduction equation is established; In each test state, the two-dimensional structure temperature field is obtained by solving the two-dimensional transient heat conduction equation, and the leading edge surface temperature of the thin leading edge component is extracted as the thermal response.

5. The data-driven method for designing arc wind tunnel test conditions for thin-edge components according to claim 1, characterized in that, Based on the thermal response of each test state, the deviation of the outer surface temperature is evaluated in conjunction with the characteristic temperature, and it is determined whether the test state meets the criteria, including: Calculate the deviation of the outer surface temperature ,in For thermal response, The characteristic temperature is used for determination; the following criteria are applied: ； in, This is the preset maximum temperature deviation.

6. The data-driven method for designing arc wind tunnel test conditions for thin-edge components according to claim 1, characterized in that, The leading edge pressure and leading edge recovery enthalpy in test states that do not meet the criteria are updated iteratively using the secant method, including: For leading edge pressure and the enthalpy of recovery of the leading edge Define function ,in This refers to the deviation of the outer surface temperature. The maximum temperature deviation is preset; the solution is obtained using the secant method. The iterative formula is: ； ； ； ； In the above formula, and These represent the leading edge pressure and the leading edge recovery enthalpy, respectively. The process variables of each iteration; and Indicates the first Leading edge pressure and leading edge recovery enthalpy in the next iteration; To be and Replacement function In and The expression that follows.

7. The data-driven method for designing arc wind tunnel test conditions for thin-edge components according to claim 1, characterized in that, Based on the normal shock wave relation, the test gas parameters for the electric arc wind tunnel test are calculated, including: Based on the updated leading edge pressure and the updated leading edge recovery enthalpy Combined with the exit Mach number of the test nozzle The gas pressure behind the leading edge normal shock wave of the thin-tipped leading edge assembly was calculated using the normal shock wave relation. Gas density after normal shock wave Gas temperature after normal shock wave ;based on , and Calculate the test gas parameters for the electric arc wind tunnel test in front of the normal shock wave, including the test gas density. static temperature of the test gas .

8. The data-driven method for designing arc wind tunnel test conditions for thin-edge components according to claim 1, characterized in that, Using the test gas parameters, updating the leading-edge heat flux density in test states that do not meet the criteria includes: Updated leading edge heat flux density The expression is as follows: ； in, The density of the test gas; To test the gas velocity; The leading edge radius of the thin-tipped leading edge assembly; The dynamic viscosity of the test gas; The effective sweep angle of the leading edge of the thin leading edge assembly; The heat flux at the stagnation point of a spherical end with the same radius as the leading edge is calculated using the following formula: ； in, These are the theoretical fitting parameters; For reference density; For reference speed; The total enthalpy of the incoming flow is expressed as follows: ;in To test the static temperature of the gas, The specific heat capacity at constant pressure of the test gas on the outer surface of the thin leading edge component; This is the preset isothermal wall enthalpy value.

9. A terminal device, comprising a processor, a memory, and a computer program stored in the memory; characterized in that, When the processor executes the computer program, it implements the data-driven method for designing arc wind tunnel test conditions for thin leading edge components as described in any one of claims 1-8.

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 data-driven method for designing arc wind tunnel test conditions for thin leading edge components as described in any one of claims 1-8.

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