Numerical simulation analysis method for the dominant characteristics of aerodynamic forces on aircraft components under shock wave sweep

Abstract

The present invention discloses a method for numerical simulation analysis of the dominant characteristics of aerodynamic forces of aircraft components under shock wave sweeping, which belongs to the technical field of flight safety verification and validation, and includes the following steps: S1, numerical simulation calculation pre-processing; S2, steady-state calculation of the initial flow field of the aircraft flight; S3, storage medium requirement analysis; S4, transient calculation of the wavefront sweeping aircraft; S5, aerodynamic data processing and dominant characteristics analysis. The present invention adopts the above-mentioned method for numerical simulation analysis of the dominant characteristics of aerodynamic forces of aircraft components under shock wave sweeping, which can better adapt to the flight safety verification and validation requirements of extreme environments such as shock wave sweeping.

Description

Technical Field

[0001] The invention relates to the technical field of flight safety verification and validation, and in particular to a numerical simulation analysis method for aerodynamic dominant characteristics of aircraft components under shock wave sweeping. Background Art

[0002] The additional aerodynamic disturbance caused by the shock wave sweeping the aircraft's aerodynamic components is an important factor that needs to be considered in the flight safety verification. When the explosion shock wave sweeps, due to the influence of the shock wave overpressure and dynamic pressure, significant gust effects and overpressure time-varying characteristics will appear in the shock wave propagation airspace. When the aircraft flies through this airspace, these characteristics will act on the various aerodynamic components of the aircraft to produce aerodynamic disturbances with different aerodynamic effect dominant characteristics. The additional aerodynamic dominant characteristics of different components are the aerodynamic load conditions that need to be considered in the flight safety verification of aircraft aerodynamic components under the extreme flight environment of the shock wave sweep.

[0003] There are significant differences between the shock wave sweep and the current flight safety verification conditions. In the current flight safety verification, the main consideration is the impact of the gust of wind on flight safety. The physical parameters of this type of gust of wind have the characteristics of relatively small amplitude, energy dispersion, and long action time. The physical parameters of the shock wave have a large amplitude, short action time, concentrated energy, and obvious transient effect. Therefore, the shock wave sweep has put forward significantly different environmental requirements for the flight safety verification.

[0004] Numerical simulation analysis method is a practical means to study the aerodynamic dominant characteristics of aircraft components under shock wave sweep. When conducting research and experiments on the aerodynamic dominant characteristics of shock wave swept aircraft, if the laboratory test method is used, there will be problems such as difficulty in realizing the physical scene of shock wave loading, low precision in measuring the aerodynamic force of components, and obvious interference from wall rebound; if the flight test method is used, there will be problems such as high flight risk, large differences in environmental condition control, and difficulty in reproducing test results. The numerical simulation calculation method has the advantages of clear research environmental conditions, good reproducibility of shock wave swept environment, simple flight physical scene realization, accurate calculation of component aerodynamic integral, and no shock wave wall rebound interference. Therefore, in order to better meet the flight safety verification requirements of extreme environments such as shock wave sweep, it is necessary to propose a numerical simulation analysis method for the aerodynamic dominant characteristics of aircraft under shock wave sweep. Summary of the invention

[0005] The purpose of the present invention is to provide a numerical simulation analysis method for the dominant characteristics of aerodynamic forces of aircraft components under shock wave sweeping, so as to solve the problems existing in the above-mentioned background technology.

[0006] To achieve the above object, the present invention provides a method for numerical simulation analysis of the dominant characteristics of aerodynamic forces of aircraft components under shock wave sweeping, comprising the following steps:

[0007] S1, numerical simulation calculation pre-processing;

[0008] S2, steady-state calculation of the initial flow field of the aircraft flight;

[0009] S3, storage media requirements analysis;

[0010] S4, transient calculation of wavefront sweeping aircraft;

[0011] S5. Aerodynamic data processing and dominant feature analysis.

[0012] Preferably, step S1 specifically comprises:

[0013] S11. Define the coordinate system of the aircraft geometry model, determine the coordinate origin, complete the point, line and surface cleaning of the aircraft geometry model, and define the aircraft components according to the aerodynamic integral calculation requirements. ,in, is the number of aircraft parts, and , including wings, ailerons, elevators, rudders, horizontal stabilizers and vertical stabilizers;

[0014] S12. According to the requirements of numerical simulation, a calculation domain is given, the inlet, outlet and far-field boundary of the calculation domain are defined, and the mesh encryption area and encryption algorithm are given according to the experience of numerical simulation calculation, and the aircraft calculation model is derived;

[0015] S13, load the geometric model of the aircraft calculation model, set the grid processing parallel calculation method, and Aerodynamic and surface pressure resolution requirements, setting edges, gaps and small component mesh sizes, and dividing all aircraft components Surface mesh;

[0016] S14. Check the quality of the aircraft surface mesh. When the surface mesh quality cannot meet the requirements of volume mesh generation, optimize the mesh quality through several methods. Manually repair the low-quality meshes that cannot be eliminated at the edges or gaps of each component during the optimization process.

[0017] S15. Give the boundary layer grid parameters and growth mode, computational domain grid type, and parallel computing intervention process, complete the numerical simulation calculation of the aircraft under the strong shock wave sweep and calculate the three-dimensional grid and output the grid file.

[0018] Preferably, step S2 specifically comprises:

[0019] S21, read the calculation grid, select the steady-state calculation turbulence model according to the typical flow field of the aircraft flight state, and calculate the boundary condition parameters and atmospheric working fluid parameters;

[0020] S22. According to the calculation requirements, a steady-state calculation solution algorithm and a discrete format are given, residual convergence cutoff conditions and relaxation factors are set, and the steady-state calculation flow field initialization is completed;

[0021] S23, setting convergence monitoring parameters and steady-state calculation iteration steps, and starting the steady-state calculation of the initial flow field of the aircraft;

[0022] S24, monitor the steady-state calculation results. If the monitored parameters diverge, adjust the parameters according to the calculation experience and continue the calculation. If the requirements are still not met, check the mesh quality and adjust the mesh to complete the steady-state numerical simulation calculation and store the initial file of the aircraft flow field.

[0023] Preferably, step S3 specifically comprises:

[0024] S31, calculate the Courant number of the CFL criterion for the three-dimensional grid ( ) to judge the stability of the solution of the NS equation. The Courant number represents the ratio of the kinetic energy of fluid motion to the viscous loss. The calculation method of the Courant number of a three-dimensional grid is as follows:

[0025] ;

[0026] in, is the transient calculation time step. A three-dimensional grid, is the number of the three-dimensional mesh surface, is the volume flux of the three-dimensional grid, is the total surface area of ​​the three-dimensional grid, is the volume of the three-dimensional grid;

[0027] S32, executing a test transient calculation, adjusting the transient calculation time step and the number of transient calculation time steps according to the CFL criterion, monitoring whether the transient calculation meets the convergence requirement, and if not, adjusting the transient calculation parameters, and continuing to iterate until the test calculation meets the convergence requirement;

[0028] S33. Estimate the storage space used for transient calculation results based on the test calculation result file. Insufficient hard disk storage space will cause transient calculation result storage overflow and calculation interruption. Storage space capacity ( ) The estimation formula is as follows:

[0029] ;

[0030] in, To calculate the storage space required for the file, is the number of calculation cases adjusted according to the time step, The space used to store a single calculation result file. is the redundancy, The value is 1.2. To calculate the number of files, To calculate the number of result files, 、 Both represent counting symbols;

[0031] S34. Use a jump server to mount a Mini SAS interface high-speed read-write storage array whose storage space is larger than the storage space capacity, set the data storage method and storage number, and prepare to mount supercomputing resources for transient numerical simulation calculations.

[0032] Preferably, step S4 is specifically:

[0033] S41, reading the flow field initial file in step S24, adjusting the steady-state calculation mode to the transient calculation mode, and adjusting the turbulence model and the corresponding discrete format;

[0034] S42. Calculate the location of monitoring points and monitoring physical parameters in a strong shock wave environment, and clarify the storage format of monitoring parameters;

[0035] S43, given the specific moment, calculate the physical parameters of the shock wave overpressure and dynamic pressure according to the semi-empirical formula of Sadovsky et al.;

[0036] S44, determining the shock wave loading area and sweeping direction, and completing the shock wave loading in the initial flow field through UDF forced initialization;

[0037] S45. Adjust the transient calculation control parameters and storage path according to the transient calculation time step and the number of transient calculation time steps in step S31 and step S32, mount supercomputing resources to perform calculations and save data.

[0038] Preferably, step S5 is specifically:

[0039] S51, read the saved data, set the data step size, for aircraft parts Write post-processing data analysis program to output individual aircraft components Calculation result file , , ;

[0040] S52, for , output the distribution of surface pressure coefficient over time, derive the pressure coefficient variation characteristics of each aircraft component under the shock wave sweep, among which the selected point pressure coefficient The calculation method is as follows:

[0041] ;

[0042] in, is the local pressure variation with time, is the incoming flow pressure, is the dynamic pressure variation with time;

[0043] S53, for The integral calculation of the aerodynamic normal coefficient under the shock wave sweep is calculated using the following formula:

[0044] ;

[0045] in, is the normal coefficient of the aerodynamic force, is the component area, is the lower surface pressure coefficient, is the upper surface pressure coefficient; the drag coefficient , lateral force coefficient and lift coefficient According to the aerodynamic projection relationship, they are projected respectively;

[0046] S54, for , calculate the change of aerodynamic force with time under the shock wave sweep, and the calculation method is as follows:

[0047] ;

[0048] in, are the drag, side force and lift of the component respectively;

[0049] S55, for The calculation method of the proportion of aerodynamic disturbance under shock wave sweep is as follows:

[0050] ;

[0051] ;

[0052] ;

[0053] in, , , They are the percentage of drag, side force and lift increments in aircraft components during the shock wave sweep process; , , They are the time functions of the drag coefficient, side force coefficient and lift coefficient of the aircraft components during the shock wave sweep process; , , are the drag coefficient, side force coefficient and lift coefficient of the aircraft in the initial disturbance state respectively; , They are the initial and end times of the transient calculation, respectively. Since the aerodynamic force symbol only indicates the same or opposite direction as the definition, the absolute value of each data is taken for calculation.

[0054] Therefore, the present invention adopts the above-mentioned numerical simulation and analysis method for the dominant characteristics of aerodynamic forces of aircraft components under shock wave sweeping. The overall calculation process is mainly divided into five parts: numerical simulation calculation pre-processing, steady-state calculation of the initial flow field of aircraft flight, storage medium requirement analysis, transient calculation of wavefront sweeping aircraft, and aerodynamic data processing and dominant characteristics analysis. It solves the problem of aircraft flight safety verification under shock wave sweeping, and can better adapt to the flight safety verification and verification requirements in extreme environments such as shock wave sweeping.

[0055] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0056] Figure 1 This is a numerical simulation calculation flow chart of a strong shock wave sweeping aircraft of the present invention;

[0057] Figure 2 This is a schematic diagram of the time variation of the aerodynamic force of aircraft components under the sweep of the shock wave of the present invention. DETAILED DESCRIPTION

[0058] Example

[0059] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0060] like Figure 1 As shown, a numerical simulation analysis method for the dominant characteristics of aerodynamic forces of aircraft components under shock wave sweeping includes the following steps:

[0061] S1, numerical simulation calculation pre-processing;

[0062] S11. Define the coordinate system of the aircraft geometry model, determine the coordinate origin, complete the point, line and surface cleaning of the aircraft geometry model, and define the aircraft components according to the aerodynamic integral calculation requirements. ,in, is the number of aircraft parts, and , including wings, ailerons, elevators, rudders, horizontal stabilizers and vertical stabilizers;

[0063] S12. According to the requirements of numerical simulation, a calculation domain is given, the inlet, outlet and far-field boundary of the calculation domain are defined, and the mesh encryption area and encryption algorithm are given according to the experience of numerical simulation calculation, and the aircraft calculation model is derived;

[0064] S13, load the geometric model of the aircraft calculation model, set the grid processing parallel calculation method, and Aerodynamic and surface pressure resolution requirements, setting edges, gaps and small component mesh sizes, and dividing all aircraft components Surface mesh;

[0065] S14. Check the quality of the aircraft surface mesh. When the surface mesh quality is low, optimize the mesh quality through various methods. Manually repair the low-quality mesh that cannot be eliminated at the edges or gaps of each component during the optimization process.

[0066] S15. Give the boundary layer grid parameters and growth mode, computational domain grid type, and parallel computing intervention process, complete the numerical simulation calculation of the aircraft under the strong shock wave sweep and calculate the three-dimensional grid and output the grid file.

[0067] S2, steady-state calculation of the initial flow field of the aircraft flight;

[0068] S21. Read the calculation grid, select the steady-state calculation turbulence model according to the typical flow field of the aircraft flight state, and calculate the boundary condition parameters and atmospheric working fluid parameters. The parameters are shown in Table 1.

[0069] Table 1 Initial working conditions for steady-state calculation

[0070] ;

[0071] S22. According to the calculation requirements, a steady-state calculation solution algorithm and a discrete format are given, residual convergence cutoff conditions and relaxation factors are set, and the steady-state calculation flow field initialization is completed;

[0072] S23, setting convergence monitoring parameters and steady-state calculation iteration steps, and starting the steady-state calculation of the initial flow field of the aircraft;

[0073] S24, monitor the steady-state calculation results. If the monitored parameters diverge, adjust the parameters according to the calculation experience and continue the calculation. If the requirements are still not met, check the mesh quality and adjust the mesh to complete the steady-state numerical simulation calculation and store the initial file of the aircraft flow field.

[0074] S3, storage media requirements analysis;

[0075] S31, calculate the Courant number of the CFL criterion for the three-dimensional grid ( ) to judge the stability of the solution of the NS equation. The Courant number represents the ratio of the kinetic energy of fluid motion to the viscous loss. The calculation method of the Courant number of a three-dimensional grid is as follows:

[0076] ;

[0077] in, is the transient calculation time step. A three-dimensional grid, is the number of the three-dimensional mesh surface, is the volume flux of the three-dimensional grid, is the total surface area of ​​the three-dimensional grid, is the volume of the three-dimensional grid;

[0078] S32, executing a test transient calculation, adjusting the transient calculation time step and the number of transient calculation time steps according to the CFL criterion, monitoring whether the transient calculation meets the convergence requirement, and if not, adjusting the transient calculation parameters, and continuing to iterate until the test calculation meets the convergence requirement;

[0079] S33. Estimate the storage space used for transient calculation results based on the test calculation result file. Insufficient hard disk storage space will cause transient calculation result storage overflow and calculation interruption. Storage space capacity ( ) The estimation formula is as follows:

[0080] ;

[0081] in, To calculate the storage space required for the file, is the number of calculation cases adjusted according to the time step, The space used to store a single calculation result file. is the redundancy, The value is 1.2. To calculate the number of files, To calculate the number of result files, 、 Both represent counting symbols;

[0082] S34. Use a jump server to mount a Mini SAS interface high-speed read-write storage array whose storage space is larger than the storage space capacity, set the data storage method and storage number, and prepare to mount supercomputing resources for transient numerical simulation calculations.

[0083] S4, transient calculation of wavefront sweeping aircraft;

[0084] S41, reading the flow field initial file in step S24, adjusting the steady-state calculation mode to the transient calculation mode, and adjusting the turbulence model and the corresponding discrete format;

[0085] S42. Calculate the location of monitoring points and monitoring physical parameters in a strong shock wave environment, and clarify the storage format of monitoring parameters;

[0086] S43, given specific moment (in this embodiment, ), calculate the physical parameters of shock wave overpressure and dynamic pressure according to the semi-empirical formula of Sadovsky et al.;

[0087] S44, determining the shock wave loading area and sweeping direction, and completing the shock wave loading in the initial flow field through UDF forced initialization;

[0088] S45. Adjust the transient calculation control parameters and storage path according to the transient calculation time step and the number of transient calculation time steps in step S31 and step S32, mount supercomputing resources to perform calculations and save data.

[0089] S5. Aerodynamic data processing and dominant feature analysis.

[0090] S51, read the saved data, set the data step size, for aircraft parts Write post-processing data analysis program to output individual aircraft components Calculation result file , , ;

[0091] S52, for , output the distribution of surface pressure coefficient over time, derive the pressure coefficient variation characteristics of each aircraft component under the shock wave sweep, among which the selected point pressure coefficient The calculation method is as follows:

[0092] ;

[0093] in, is the local pressure variation with time, is the incoming flow pressure, is the dynamic pressure variation with time;

[0094] S53, for The integral calculation of the aerodynamic normal coefficient under the shock wave sweep is calculated using the following formula:

[0095] ;

[0096] in, is the normal coefficient of the aerodynamic force, is the component area, is the lower surface pressure coefficient, is the upper surface pressure coefficient; the drag coefficient , lateral force coefficient and lift coefficient According to the aerodynamic projection relationship, they are projected respectively;

[0097] S54, for , calculate the change of aerodynamic force with time under the shock wave sweep, and the calculation method is as follows:

[0098] ;

[0099] in, are the drag, side force and lift of the component respectively;

[0100] S55, for The calculation method of the proportion of aerodynamic disturbance under shock wave sweep is as follows:

[0101] ;

[0102] ;

[0103] ;

[0104] in, , , They are the percentage of drag, side force and lift increments in aircraft components during the shock wave sweep process; , , They are the time functions of the drag coefficient, side force coefficient and lift coefficient of the aircraft components during the shock wave sweep process; , , are the drag coefficient, side force coefficient and lift coefficient of the aircraft in the initial disturbance state respectively; , They are the initial and end times of the transient calculation, respectively. Since the aerodynamic force symbol only indicates the same or opposite direction as the definition, the absolute value of each data is taken for calculation.

[0105] Figure 2 Table 2 shows the temporal variation of aerodynamic forces of various aircraft components under the shock wave sweep. Table 3 shows the proportion of aerodynamic disturbance increments of various aircraft components under the shock wave sweep.

[0106] Table 2 The percentage of aerodynamic disturbance increment of each aircraft component under the shock wave sweep

[0107] ;

[0108] It can be seen that before the shock wave sweeps the aircraft, the aerodynamic forces of the wings and ailerons are dominated by lift, and the aerodynamic forces of the rudder and vertical stabilizer have no typical dominant characteristics; when the shock wave sweeps, the incremental lift disturbance of the wings and ailerons accounts for more than 80%, the incremental side force disturbance of the rudder and vertical stabilizer accounts for more than 80%, and the incremental aerodynamic disturbance of the elevator and horizontal stabilizer does not show obvious dominant characteristics. Therefore, when the shock wave sweeps, the aerodynamic disturbance of the wings and ailerons is dominated by lift, and the aerodynamic disturbance of the rudder and vertical stabilizer is dominated by side force. When conducting safety verification of aircraft components under shock wave sweep, it is necessary to consider them separately according to the above-mentioned dominant aerodynamic characteristics.

[0109] Therefore, the present invention adopts the above-mentioned numerical simulation analysis method of the aerodynamic dominant characteristics of aircraft components under shock wave sweeping, which can better adapt to the flight safety verification and validation requirements in extreme environments such as shock wave sweeping.

[0110] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solution of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solution to deviate from the spirit and scope of the technical solution of the present invention.

Claims

1. A numerical simulation analysis method for the dominant characteristics of aerodynamic forces of aircraft components under shock wave sweep, characterized in that: The following steps are involved: S1, numerical simulation calculation pre-processing; S2, steady-state calculation of the initial flow field of the aircraft flight; S3, storage media requirements analysis; S4, transient calculation of wavefront sweeping aircraft; S5, aerodynamic data processing and dominant feature analysis; Step S1 is specifically as follows: S11. Define the coordinate system of the aircraft geometry model, determine the coordinate origin, complete the points, lines, and surfaces of the aircraft geometry model, and define the aircraft components ,in, is the number of aircraft parts, and , including wings, ailerons, elevators, rudders, horizontal stabilizers and vertical stabilizers; S12. Given a computational domain, define the computational domain entrance, exit and far-field boundary, give the mesh encryption area and encryption algorithm, and derive the aircraft calculation model; S13, load the geometric model of the aircraft calculation model, set the grid processing parallel calculation method, and Aerodynamic and surface pressure resolution, set edges, gaps and small parts mesh size, divide all aircraft parts Surface mesh; S14. Check the quality of the aircraft surface mesh. When the surface mesh quality cannot meet the requirements of volume mesh generation, optimize the mesh quality through several methods. S15, giving boundary layer grid parameters and growth mode, computational domain grid type, giving parallel computing intervention process, completing numerical simulation calculation of three-dimensional grid of aircraft under strong shock wave sweep and outputting grid file; Step S5 is specifically as follows: S51, read the saved data, set the data step size, for aircraft parts Write post-processing data analysis program to output individual aircraft components Calculation result file , , ; S52, for , output the distribution of surface pressure coefficient over time, derive the pressure coefficient variation characteristics of each aircraft component under the shock wave sweep, among which the selected point pressure coefficient The calculation method is as follows: ； in, is the local pressure variation with time, is the incoming flow pressure, is the dynamic pressure variation with time; S53, for The integral calculation of the aerodynamic normal coefficient under the shock wave sweep is calculated using the following formula: ； in, is the normal coefficient of the aerodynamic force, is the component area, is the lower surface pressure coefficient, is the upper surface pressure coefficient; S54, for , calculate the change of aerodynamic force with time under the shock wave sweep, and the calculation method is as follows: ； in, are the drag, side force and lift of the component respectively; S55, for The calculation method of the proportion of aerodynamic disturbance under shock wave sweep is as follows: ； ； ； in, , , They are the percentage of drag, side force and lift increments in aircraft components during the shock wave sweep process; , , They are the time functions of the drag coefficient, side force coefficient and lift coefficient of the aircraft components during the shock wave sweep process; , , are the drag coefficient, side force coefficient and lift coefficient of the aircraft in the initial disturbance state respectively; , are the initial and end times of transient calculation respectively.

2. The numerical simulation analysis method for the dominant characteristics of aerodynamic forces of aircraft components under shock wave sweep according to claim 1 is characterized in that: Step S2 is specifically as follows: S21, read the calculation grid, select the steady-state calculation turbulence model according to the typical flow field of the aircraft flight state, and calculate the boundary condition parameters and atmospheric working fluid parameters; S22, give a steady-state calculation solution algorithm and a discrete format, set the residual convergence truncation condition and relaxation factor, and complete the steady-state calculation flow field initialization; S23, setting convergence monitoring parameters and steady-state calculation iteration steps, and starting the steady-state calculation of the initial flow field of the aircraft; S24, monitor the steady-state calculation results. If the monitored parameters diverge, adjust the parameters to continue the calculation. If the requirements are still not met, check the mesh quality and adjust the mesh to complete the steady-state numerical simulation calculation and store the initial file of the aircraft flow field.

3. The numerical simulation analysis method for the dominant characteristics of aerodynamic forces of aircraft components under shock wave sweep according to claim 2 is characterized in that: Step S3 is specifically as follows: S31. Calculate the Courant number of the three-dimensional grid CFL criterion to judge the stability of the solution of the NS equation. The Courant number represents the ratio of the kinetic energy of the fluid motion to the viscous loss. The calculation method of the Courant number of the three-dimensional grid is as follows: ； in, is the transient calculation time step. A three-dimensional grid, is the number of the three-dimensional mesh surface, is the volume flux of the three-dimensional grid, is the total surface area of ​​the three-dimensional grid, is the volume of the three-dimensional grid; S32, executing a test transient calculation, adjusting the transient calculation time step and the number of transient calculation time steps according to the CFL criterion, monitoring whether the transient calculation meets the convergence requirement, and if not, adjusting the transient calculation parameters, and continuing to iterate until the test calculation meets the convergence requirement; S33. Estimate the storage space used for transient calculation results based on the test calculation result file. The storage space capacity estimation formula is as follows: ； in, To calculate the storage space required for the file, is the number of calculation cases adjusted according to the time step, The space used to store a single calculation result file. is the redundancy, To calculate the number of files, To calculate the number of result files, 、 Both represent counting symbols; S34. Use a jump server to mount a Mini SAS interface high-speed read-write storage array whose storage space is larger than the storage space capacity, set the data storage method and storage number, and prepare to mount supercomputing resources for transient numerical simulation calculations.

4. The numerical simulation analysis method for the dominant characteristics of aerodynamic forces of aircraft components under shock wave sweep according to claim 3 is characterized in that: Step S4 is specifically as follows: S41, reading the flow field initial file in step S24, adjusting the steady-state calculation mode to the transient calculation mode, and adjusting the turbulence model and the corresponding discrete format; S42. Calculate the location of monitoring points and monitoring physical parameters in a strong shock wave environment, and clarify the storage format of monitoring parameters; S43, given the specific moment, calculate the physical parameters of the shock wave overpressure and dynamic pressure according to Sadovsky's semi-empirical formula; S44, determining the shock wave loading area and sweeping direction, and completing the shock wave loading in the initial flow field through UDF forced initialization; S45. Adjust the transient calculation control parameters and storage path according to the transient calculation time step and the number of transient calculation time steps in step S31 and step S32, mount supercomputing resources to perform calculations and save data.

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